EP2486246B1

EP2486246B1 - Variable geometry turbine

Info

Publication number: EP2486246B1
Application number: EP10776401.1A
Authority: EP
Inventors: John F. Parker; Robert L. Holroyd; Tom J. Roberts; James Alexander Mcewen; Tim Denholm; Simon Moore; Michael Voong; Christopher Normington; Arun Vijayakumar; Stephen Garrett
Original assignee: Cummins Ltd
Current assignee: Cummins Ltd
Priority date: 2009-10-06
Filing date: 2010-10-06
Publication date: 2017-06-28
Anticipated expiration: 2030-10-06
Also published as: WO2011042739A2; WO2011042739A3; IN2012DN02885A; CN102648334A; CN102648334B; WO2011042739A4; EP2486246A2

Description

The present invention relates to a variable geometry turbine. The variable geometry turbine may, for example, form a part of a turbocharger.
This application claims priority from the following British patent applications GB0917513.4 , GB1005680.2 , GB1012382.6 , GB1012389.1 , GB1012488.1 , GB1012474.1 , GB1012536.7 , GB1012734.8 , GB1012557.3 , GB1012767.8 , GB1012769.4 , GB1012463.4 , GB1012471.7 , GB1012475.8 , GB1012479.0 , GB1012492.3 , GB1012774.4 , GB1012715.7 , GB1012538.3 , GB1012658.9 , GB1012486.5 , GB1012768.6 , GB1012779.3 , GB1012380.0 , and GB1012744.7 , which all relate to a variable geometry turbines.
Turbochargers are well known devices for supplying air to an intake of an internal combustion engine at pressures above atmospheric pressure (boost pressures). A conventional turbocharger essentially comprises an exhaust gas driven turbine wheel mounted on a rotatable shaft within a turbine housing connected downstream of an engine outlet manifold. Rotation of the turbine wheel rotates a compressor wheel mounted on the other end of the shaft within a compressor housing. The compressor wheel delivers compressed air to an engine intake manifold. The turbocharger shaft is conventionally supported by journal and thrust bearings, including appropriate lubricating systems, located within a central bearing housing connected between the turbine and compressor wheel housings.
The turbine stage of a typical turbocharger comprises: a turbine chamber within which the turbine wheel is mounted; an annular inlet defined between facing radial walls arranged around the turbine chamber; an inlet volute arranged around the annular inlet; and an outlet passageway extending from the turbine chamber. The passageways and chamber communicate such that pressurised exhaust gas admitted to the inlet volute flows through the inlet to the outlet passageway via the turbine and rotates the turbine wheel. It is also known to improve turbine performance by providing vanes, referred to as nozzle vanes, in the inlet so as to deflect gas flowing through the inlet. That is, gas flowing through the annular inlet flows through inlet passages (defined between adjacent vanes) which induce swirl in the gas flow, turning the flow direction towards the direction of rotation of the turbine wheel.
Turbines may be of a fixed or variable geometry type. Variable geometry turbines differ from fixed geometry turbines in that the size of the inlet can be varied to optimise gas flow velocities over a range of mass flow rates so that the power output of the turbine can be varied to suit varying engine demands. For instance, when the volume of exhaust gas being delivered to the turbine is relatively low, the velocity of the gas reaching the turbine wheel is maintained at a level which ensures efficient turbine operation by reducing the size of the inlet using a variable geometry mechanism. Turbochargers provided with a variable geometry turbine are referred to as variable geometry turbochargers.
Nozzle vane arrangements in variable geometry turbochargers can take different forms. In one type, known as a "sliding nozzle ring", the vanes are fixed to an axially movable wall that slides across the inlet passageway. The axially movable wall moves towards a facing shroud plate in order to close down the inlet passageway and in so doing the vanes pass through apertures in the shroud plate. Alternatively, the nozzle ring is fixed to a wall of the turbine and a shroud plate is moved over the vanes to vary the size of the inlet passageway.
The moving component of the variable geometry mechanism, whether it is the nozzle ring or the shroud plate, is supported for axial movement in a cavity in a part of the turbocharger housing (usually either the turbine housing or the turbocharger bearing housing). It may be sealed with respect to the cavity walls to reduce or prevent leakage flow around the back of the nozzle ring.
The moveable wall of the variable geometry mechanism is axially displaced by a suitable actuator assembly comprising an actuator and a linkage. An example of such a known actuator assembly is for instance disclosed in US 5,868,552 . The linkage comprises a yoke pivotally supported within the bearing housing and having two arms, each of which extends into engagement with an end of a respective push rod on which the moving component (in this instance the nozzle ring) is mounted. The yoke is mounted on a shaft journaled in the bearing housing and supporting a crank external to the bearing housing which may be connected to the actuator in any appropriate manner. The actuator which moves the yoke can take a variety of forms, including pneumatic, hydraulic and electric forms, and can be linked to the yoke in a variety of ways. The actuator will generally adjust the position of the moving wall under the control of an engine control unit (ECU) in order to modify the airflow through the turbine to meet performance requirements.
In use, axial forces are imported on the moveable wall by the air flow through the inlet, which must be accommodated by the actuator assembly. In addition, a torque is imparted to the nozzle ring as a result of gas flow vane passages being deflected towards the direction of rotation of the turbine wheel. If the nozzle ring is the moving wall of the variable geometry mechanism this torque also has to be reacted or otherwise accommodated by the actuator assembly such as by parts of the linkage.
JP H5-133238 relates to an inexpensive variable capacity supercharger with a simplified structure.
FR 2,513,312 relates to a turbine wheel that has independent blades mounted on it and separated from each other.
It is one object of the present invention to obviate or mitigate the aforesaid disadvantages. It is also an object of the present invention to provide an improved or alternative variable geometry mechanism and turbine.

Statements of Invention

According to the present invention there is provided a variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet; the annular inlet being divided into at least two axially offset inlet passages; the inner diameter of the sleeve being greater than the inner diameter of the inlet passages; wherein the axially moveable sleeve is moveable across substantially the full axial width of the annular inlet so as to substantially close or entirely close the gas flow path through the annular inlet.
It will be appreciated that axially offset inlet passages include inlet passages with different axial positions and/or inlet passages with different axial extents. Axially offset inlet passages may be spaced apart, adjacent or axially overlapping. Moreover, it will be appreciated that references to the sleeve as being 'cylindrical' are to be interpreted as encompassing any generally cylindrical or annular shape, and does not exclude sleeves having a structure which lacks a perfectly circular axial cross-section. By way of example, cylindrical sleeves in accordance with the present invention may include sections or segments which are not perfectly arcuate so as to define a continuously circular axial cross-section. Such sections or segments could, for example, be substantially straight in axial cross section provided a sufficient number are provided to define a generally cylindrical sleeve.
The inner diameter of the sleeve may be less than or substantially equal to the outer diameter of the inlet passages. Alternatively, the inner diameter of the sleeve is greater than the outer diameter of the inlet passages.
As a further alternative, the turbine may incorporate a plurality of axially movable sleeves, a first sleeve having an inner diameter that is greater than the inner diameter of the inlet passages, and a second sleeve having an inner diameter that is less than or substantially equal to the outer diameter of the inlet passages or an inner diameter that is greater than the outer diameter of the inlet passages. In a still further embodiment, the turbine may incorporate a plurality of axially movable sleeves, a first sleeve having an inner diameter that is less than or substantially equal to the outer diameter of the inlet passages, and a second sleeve having an inner diameter that is greater than the outer diameter of the inlet passages.
The sleeve may be axially movable across the annular inlet in a direction towards the second inlet sidewall so as reduce the size of the gas flow path through the inlet. At least a portion of an end of the sleeve nearer to the first inlet sidewall than the second inlet sidewall may be configured so as to be exposable to gases flowing through said annular inlet during use. Additionally or alternatively, at least a portion of an end of the sleeve nearer to the first inlet sidewall than the second inlet sidewall may be configured so as to be located in between said first and second inlet sidewall during axial movement of the sleeve across the annular inlet.
The sleeve preferably possesses a small radial thickness or extent, which may, for example, be less than the axial width of the annular inlet. This is intended to reduce aerodynamic load on the sleeve, or actuators thereof. 'Small', may be defined as being less than an axial width of the annular inlet, or less than an axial width of an inlet portion or passage way. The sleeve may be less than 5mm thick, less than 4mm thick, less than 3mm thick, less than 2mm thick, or less than 1mm thick, for example approximately 0.5mm thick.
The annular inlet may be divided into at least two axially offset inlet passages by at least one annular baffle axially spaced from the first and second inlet sidewalls.
Inlet vanes may extend axially across at least one of the axially offset inlet passages.
The minimum distance between a baffle and the turbine wheel may be less than the minimum distance between an adjacent vane and the turbine wheel.
The trailing edges of at least some of the vanes extending across one of the axially offset inlet passages may lie on a different radius to the trailing edges of at least some of the vanes extending across another of the axially offset inlet passages.

Detailed Description

Specific embodiments of the present invention will now be described, with reference to the accompanying drawings.

Fig. 1 is an axial cross-section through a known turbocharger including a variable geometry turbine.
Fig. 2 is a schematic representation of a radial view around a portion of the circumference of the annular inlet of the turbine illustrated in Figure 1.
Fig. 3 is an axial cross-section through part of a turbocharger including a variable geometry turbine in accordance with an embodiment of the present invention.
Figs. 4a and 4b illustrate detail of the nozzle assembly of the turbine of Fig. 3.
Fig. 5 is a schematic representation of a radial view around a portion of the circumference of the annular inlet of the nozzle assembly of Figures 4a and 4b.
Fig. 6 shows the schematic illustration of Fig. 5 modified to show a sleeve forming part of the nozzle assembly of Figs. 4a and 4b.
Figs. 7a to 7g are axial cross-sections through part of a variable geometry turbine in accordance with alternative embodiments of the present invention.
Figs. 8a - 8c are schematic illustrations of further embodiments of the present invention.
Figs. 9a to 9c are schematic illustrations of further embodiments of the present invention.
Figs. 10 to 10e schematically illustrate components of a further embodiment of the present invention.
Figs. 11 a to 11 e schematically illustrate components of a further embodiment of the present invention.
Figs. 12a to 12e schematically illustrate components of a further embodiment of the present invention.
Figs. 13a to 13f, 14a to 14d, 15, 16a to 16d, and 17 to 22 are each schematic illustrations of a radial view around a portion of the circumference of a respective inlet structure in accordance with various embodiments of the present invention
Figs. 23 to 24 are axial cross-sections schematically illustrating embodiments of the present invention.
Fig. 26 is a schematic illustration of a radial view around a portion of the circumference of an annular inlet structure in accordance with a embodiment of the present invention.
Figs. 27a to 27b illustrate portions of a turbine and nozzle assembly in accordance with an embodiment of the present invention.
Figs. 28 and 29 are each schematic illustrations of a radial view around a portion of the circumference of an,annular inlet structure in accordance with respective embodiments of the present invention.
Figs. 30a and 30b illustrate a modification of an embodiment of the present invention.
Fig. 31 a is an axial cross-section through part of a turbocharger including a variable geometry turbine.that is not in accordance with the present invention;
Figs. 31b and 31c illustrate detail of the nozzle assembly of the turbine of Figure 31a;
Figs. 32a to 32b are axial cross-sections through part of a turbine in accordance with another embodiment of the present invention.
Figs. 33a to 33b are axial cross-sections through part of a turbine that is not in accordance with the present invention;
Figs. 34a to 34c illustration a detail of a inlet sleeve in accordance with embodiments of the present invention.
Figs. 35a and 35b schematically illustrate a detail of possible modifications to embodiments of the present invention.
Figure 36 is an axial cross-section through a conventional turbocharger;
Figure 37 is an axial cross-section through a turbine volute and annular inlet of a turbine according to an embodiment of the present invention;
Figures 38 and 39 depict a sleeve construction for the sleeve in the turbine of Figure 37, in accordance with an embodiment of the present invention;
Figure 40 is an end-on view of a sleeve for use in the turbine of Figure 37, in accordance with another embodiment of the present invention; and
Figures 41a-41f are end-on views of sleeves for use in the turbine of Figure 37, in accordance with other embodiments of the present invention.
Figure 42 depicts sleeve sections for use in controlling a gas flow path through an inlet, in accordance with an embodiment of the present invention;
Figure 43 depicts sleeve sections for use in controlling a gas flow path through an inlet, in accordance with another embodiment of the present invention; and
Figure 44 depicts sleeve sections for use in controlling a gas flow path through an inlet, in accordance with an further of the present invention.
Figure 45 is an axial cross-section through a turbine volute and annular inlet of a turbine according to an embodiment of the present invention.
Figure 46 is an axial cross-section through a turbine volute and annular inlet of a turbine according to a first embodiment of the present invention; and
Figure 47 is an axial cross-section through a turbine volute and annular inlet of a turbine according to a second embodiment of the present invention.
Fig. 48 shows a schematic illustration of a further embodiment of the present invention.
Figure 49 is an axial cross-section through a turbine volute and annular inlet of a turbine according to an embodiment of the present invention;
Figure 50 is an axial cross-section through a turbine volute and annular inlet of a turbine according to a further embodiment of the present invention;
Figure 51 is an axial cross-section through a turbine volute and annular inlet of a turbine according to another embodiment of the present invention;
Figure 52 is an axial cross-section through a turbine volute and annular inlet of a turbine according to a still further embodiment of the present invention;
Figure 53 is an axial cross-section through a turbine volute and annular inlet of a turbine according to a yet further embodiment of the present invention;
Figure 54 is a perspective illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 49 composed of an inlet sidewall, baffles, vanes and an axially slidable sleeve;
Figure 55 is an illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 50 composed of an inlet sidewall, baffles, vanes and an axially slidable sleeve - (A) is a perspective view of said section of the nozzle structure, (B) shows radial cross-sectional views of the three arrays of vanes and their respective sidewall or baffle, and (C) shows detail views of a vane in each of said three arrays of vanes;
Figure 56 is an illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 51 composed of an inlet sidewall, baffles, vanes and an axially slidable sleeve - (A) is a perspective view of said section of the nozzle structure, (B) shows radial cross-sectional views of the three arrays of vanes and their respective sidewall or baffle, and (C) shows detail views of a vane in each of said three arrays of vanes;
Figure 57 is an illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 52 composed of an inlet sidewall, baffles, vanes and an axially slidable sleeve - (A) is a perspective view of said section of the nozzle structure, and (B) shows radial cross-sectional views of the three arrays of vanes and their respective sidewall or baffle;
Figure 58 is an illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 53 composed of an inlet sidewall, baffles, vanes and an axially slidable sleeve - (A) is a perspective view of said section of the nozzle structure, and (B) shows radial cross-sectional views of the three arrays of vanes and their respective sidewall or baffle;
Figure 59 is an axial cross-section through a turbine volute and annular inlet of a turbine according to an embodiment of the present invention; and
Figure 60 is a perspective illustration of components of a section of a nozzle structure forming part of a turbine according to an embodiment of the present invention composed of an inlet sidewall, baffles, vanes and an axially slidable sleeve.
Figure 61 is a perspective view of baffles, vanes and a guide for guiding movement of a sleeve, in accordance with an embodiment of the present invention;
Figure 62 is a perspective view of baffles, vanes and a guide for guiding movement of a sleeve, in accordance with another embodiment of the present invention.
Figure 63 is a perspective view of a sleeve in accordance with an embodiment of the present invention;
Figures 64a to 64e depict different examples of inclined surfaces that may be used in accordance with embodiments of the present invention;
Figure 65 is a perspective view of vanes provided with inclined surfaces, in accordance with an embodiment of the present invention;
Figure 66 is a perspective view of baffles provided with inclined surfaces, in accordance with an embodiment of the present invention
Figure 67 is a perspective view of a sleeve assembly in accordance with an embodiment of the present invention;
Figure 68 is a perspective view of a sleeve assembly in accordance with another embodiment of the present invention;
Figure 69 is a perspective view of a sleeve assembly, in different operating positions, in accordance with a further embodiment of the present invention; and
Figure 70 schematically depicts a sleeve structure in accordance with another embodiment of the present invention.
Figure 70a schematically depicts a sleeve structure in accordance with further embodiment of the present invention;
Figure 70b schematically depicts a sleeve structure in accordance with a yet further embodiment of the present invention;
Figure 70c schematically depicts a section of a turbine incorporating the sleeve structure shown in figure 70b.
Figures 71a to 71c each schematically depict a side-on view of different embodiments of a leading end of an axially moveable sleeve;
Figure 72 is a schematic side-on view of the leading end of an axially moveable sleeve according to another embodiment of the present invention; and
Figure 73 is a schematic side-on view of the leading end of an axially moveable sleeve according to a still further embodiment of the present invention.
Fig. 74 schematically illustrates a turbine incorporating an axially sliding sleeve and a baffle/vane arrangement in accordance with a preferred embodiment of the present invention.
Figs. 75a and 75b are perspective and side-on schematic illustrations of a further alternative embodiment of a baffle/vanes structure according to the present invention.
Fig. 76 is a perspective schematic illustration of still another embodiment of a baffle/vane structure according to the present invention.
Fig. 77 is a perspective schematic illustration of still another embodiment of a baffle/vane structure according to the present invention.
Figure 78 is a perspective view of a sleeve which forms part of a turbine in accordance with an embodiment of the invention;
Figures 79 to 82 show axial cross sections through parts of turbines in accordance with further embodiments of the invention
Figure 83 is an axial cross-section through a turbine volute and annular inlet of a turbine according to a yet further embodiment of the present invention.
Figure 84 is a perspective illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 83 composed of an inlet sidewall, baffles, vanes and an axially slidable sleeve.
Figure 85 is a radial cross-sectional illustration of the array of vanes, baffles and cylindrical sleeve according to the embodiment of figures 83 and 84.
Figure 86 is a radial cross-sectional illustration of a generally cylindrical axially slidable sleeve and array of vanes according to an alternative embodiment of the present invention.

Referring to Figure 1, this illustrates a known turbocharger comprising a variable geometry turbine housing 1 and a compressor housing 2 interconnected by a central bearing housing 3. A turbocharger shaft 4 extends from the turbine housing 1 to the compressor housing 2 through the bearing housing 3. A turbine wheel 5 is mounted on one end of the shaft 4 for rotation within the turbine housing 1, and a compressor wheel 6 is mounted on the other end of the shaft 4 for rotation within the compressor housing 2. The shaft 4 rotates about turbocharger axis 4a on bearing assemblies located in the bearing housing.
The turbine housing 1 defines a volute 7 to which gas from an internal combustion engine (not shown) is delivered. The exhaust gas flows from the volute 7 to an axial outlet passageway 8 via an annular inlet 9 and turbine wheel 5. The inlet 9 is defined between sides walls, one side wall being surface 10 of a radial wall of a movable annular nozzle ring wall member 11 and on the opposite side wall being an annular shroud plate 12. The shroud 12 covers the opening of an annular recess 13 in the turbine housing 1.
The nozzle ring 11 supports an array of circumferentially and equally spaced nozzle vanes 14 each of which extends across the full axial width of the inlet 9. The nozzle vanes 14 are orientated to deflect gas flowing through the inlet 9 towards,the direction of rotation of the turbine wheel 5. When the nozzle ring 11 is proximate to the annular shroud 12, the vanes 14 project through suitably configured slots in the shroud 12, into the recess 13.
An actuator (not shown) is operable to control the position of the nozzle ring 11 via an actuator output shaft (not shown), which is linked to a stirrup member 15. The stirrup member 15 in turn engages axially extending guide rods 16 that support the nozzle ring 11. Accordingly, by appropriate control of the actuator (which may for instance be pneumatic or electric or any other suitable type), the axial position of the guide rods 16 and thus of the nozzle ring 11 can be controlled. It will be appreciated that details of the nozzle ring mounting and guide arrangements may differ from those illustrated.
The nozzle ring 11 has axially extending radially inner and outer annular flanges 17 and 18 that extend into an annular cavity 19 provided in the turbine housing 1. Inner and outer sealing rings 20 and 21 are provided to seal the nozzle ring 11 with respect to inner and outer annular surfaces of the annular cavity 19 respectively, whilst allowing the nozzle ring 11 to slide within the annular cavity 19. The inner sealing ring 20 is supported within an annular groove formed in the radially inner annular surface of the cavity 19 and bears against the inner annular flange 17 of the nozzle ring 11. The outer sealing ring 20 is supported within an annular groove formed in the radially outer annular surface of the cavity 19 and bears against the outer annular flange 18 of the nozzle ring 11.
Gas flowing from the inlet volute 7 to the outlet passageway 8 passes over the turbine wheel 5 and as a result torque is applied to the shaft 4 to drive the compressor wheel 6. Rotation of the compressor wheel 6 within the compressor housing 2 pressurises ambient air present in an air inlet 22 and delivers the pressurised air to an air outlet volute 23 from which it is fed to an internal combustion engine (not shown). The speed of the turbine wheel 5 is dependent upon the velocity of the gas passing through the annular inlet 9. For a fixed rate of mass of gas flowing into the inlet 9, the gas velocity is a function of the width of the inlet 9, the width being adjustable by controlling the axial position of the nozzle ring 11. (As the width of the inlet 9 is reduced, the velocity of the gas passing through it increases.) Figure 1 shows the annular inlet 9 fully open. The inlet passageway 9 may be closed to a minimum by moving the nozzle ring 11 towards the shroud 12.
Referring to Fig 2, this is a schematic representation of a radial view around a portion of the circumference of the annular inlet 9 of the turbine of Fig 1, un-rolled and laid flat in the plane of the paper. In this representation the nozzle ring 11 is in a fully open position such that parallel lines 11 and 12 represent the nozzle ring 11 and shroud plate 12 respectively, and parallel lines 14 represent the leading edges of the nozzle vanes 14 which extend across the inlet 9. The dimension c is a portion of the circumference of the inlet 9, and the dimension w is the maximum width of the annular inlet 9. From Fig 2 it can be seen that the vanes 14 divide the annular inlet 9 into an annular array of circumferentially adjacent inlet passages 14a. Each inlet passage 14a extends generally radially, but with a forward sweep (with decreasing radius) resulting from the configuration of the vanes 14 which as mentioned above is designed to deflect the gas flow passing through the inlet 9 towards the direction of rotation off the turbine wheel. The geometry of each of the inlet passages 14a, which extend across the full width w of the inlet 9, is defined by the configuration and spacing of the vanes 14, but as shown have a generally rectangular cross-section.
Fig 3 is a cross-section through part of a turbocharger including a variable geometry turbine in accordance with an embodiment of the present invention. Where appropriate corresponding features of the turbochargers of Fig 1 and Fig 3 are identified with the same reference numbers. References to "axial" and "axially" are to be understood as referring to the axis of rotation of the turbine wheel. Fig 3 shows the bearing housing 3 and turbine housing 4 of the turbocharger, with the compressor (not shown) removed. As with the known turbocharger of Fig 1, a turbocharger shaft 4 extends through the bearing housing 3 to the turbine housing 1 and a turbine wheel 5 is mounted on one end of the shaft 4 within the turbine housing 1. The turbine housing 1 defines a volute 7 from which exhaust gas flow is delivered to an annular inlet 9 which surrounds the turbine wheel 5.
In accordance with the present invention, the size of the inlet 9 is variable by controlling the position of an axially sliding cylindrical sleeve 30 which is supported on guide rods 31 which are slidably mounted within a cavity 19 defined by the bearing housing 3. The guide rods 31 may have a configuration substantially the same as that of the guide rods 16 illustrated in Fig 1, and be actuated in the same way via a yoke (not shown) linked to inboard ends 31 a of the guide rods 31. Outboard ends 31 a of the guide rods 31 are connected to radially extended flanges 30a of the sleeve 30. Respective separate flanges 30a maybe provided for connection to the guide rods 31 as illustrated, or the sleeve 30 may comprise a single annular radially extending flange which is connected to the guide rods 31. The sleeve 30 has a free end which projects into the inlet 9 so that the width of the inlet can be varied in a controlled manner by appropriate movement and positioning of the sleeve 30 via the guide rods 31.
Also in accordance with the present invention the inlet 9 is, at least in part, defined between facing side walls of the turbine housing which in this embodiment comprise nozzle rings 32 and 33 of a nozzle assembly 34. The nozzle assembly 34 is shown in greater detail in Figs 4a and 4b (together with a section of the sleeve 31, and a guide rod 31). The first nozzle ring 32 of the nozzle assembly 34 extends radially across the opening of the cavity 19 of the turbine housing to the sleeve 30. Seal ring 35 seals the nozzle ring 32 with respect to the sleeve 30 to prevent gas leakage between the inlet 9 and the cavity 19. Similarly, a seal ring 36 seals the nozzle ring 32 with respect to the turbine housing adjacent a radial inner periphery of the nozzle ring 32. The second nozzle ring 33 of the nozzle ring assembly 34 is fixed to a radial wall of the turbine housing, within a shallow annual recess defined by the turbine housing and is sealed with respect thereto by seal ring 36 to prevent gas leakage between the nozzle ring 33 and the turbine housing.
An annular array of circumferentially equispaced nozzle vanes 37 extend between the first and second nozzle rings 32 and 33. The nozzle vanes 37 divide the annular inlet into circumferentially spaced inlet portions. Radially extending annular inlet baffles 38a, 38b and 38c are axially equispaced between the nozzle rings 32 and 33 and further divide the annular inlet 9 into axially spaced inlet portions. The baffles 38 are relatively thin rings coaxial with the turbine axis and orientated parallel to the nozzle rings 32 and 33 so that they have radially extending faces. Accordingly, the vanes 37 together with the inlet baffles 38a-38c divide the annular inlet 9 into a plurality of discreet inlet passages 39 (not all of which are individually referenced in the drawings) which is best illustrated in Fig 5 which is a schematic representation of a radial view of an un-rolled portion of the circumference of the nozzle assembly 34 corresponding to the representation of the known inlet structure shown in Fig 2. Again the dimension w is the full width of the inlet 9 and the dimension c is a portion of the circumference of the inlet.
Referring to Fig 5, the vanes 37, and inlet baffles 38a-38c, divide the inlet 9 into four axially spaced annular arrays of circumferentially spaced inlet passages 39a, 39b, 39c and 39d respectively. In contrast, the known arrangement of Fig 2 has a single annular array of circumferentially spaced inlet passages, each of which extends across the full width of the inlet 9. The exact configuration of the inlet passages 39a to 39d is defined by the configuration of the vanes 37 and baffles 38a to 38c, but as illustrated it can be seen that the passages have a generally rectangular (in this case nearly square) cross section. Each of the inlet passages 39a - 39d directs gas flow to the turbine wheel, and due to the sweep of the vanes 37 turns the gas flow in a direction towards to the direction of the rotation of the turbine wheel 5. In this embodiment the inlet passages 39 in each annular array are circumferentially adjacent and each annular array 39a to 39d is axially adjacent to the next.
As described above, the size of the inlet 9 is controlled by adjustment of the axial position of the sleeve 30 which slides over the outside diameter of the vanes and baffles. Depending upon the positioning of the sleeve 30, one or more of the axially spaced annular arrays of inlet passages 39a-39d may therefore be blocked or partially blocked to gas flow through the inlet 9. For instance, Fig 4a illustrates the sleeve 30 in an almost fully open position in which the first annular array of gas flow passages 39a is partially blocked to gas flow, and the second to fourth annular arrays of inlet passages 39b-39d are fully open to gas flow. Fig 4b (and Fig 3), show the sleeve 30 in a fully closed position in which the end of the sleeve 30 bears against the nozzle ring 33 and all four of the axially adjacent annular arrays of inlet passages 39a-39d are closed (subject to the potential for a minimum amount of leakage into the inlet passages 39d between the sleeve 30 and the nozzle ring 33).
By controlling the position of the sleeve 30 between the open and closed positions, a selected number of the axially adjacent annular arrays of inlet passages 39a-39d may be opened or blocked, or partially opened/blocked. For instance, by positioning the sleeve 30 so that the free end of the sleeve is axially aligned with the first inlet baffle 38a, the first annular array of inlet passages 39a is closed and the second to fourth annular arrays of inlet passages 39b-39d are fully opened to gas flow. Similarly, by positioning the free end of the sleeve 30 part way between inlet baffles 38b and 38c the first and second annular arrays of inlet passages 39a and 39b will be fully closed, the fourth annular array of inlet passage 39d will be fully open and the third annular array of inlet passages 39c will be partially open. This is schematically illustrated in Fig 6 which superimposes the sleeve 30 on the view shown in Fig 5.
In the embodiments of the invention described above (and below) the sleeve 30 can fully close the inlet, i.e. block the inlet 9 completely. In other embodiments the sleeve need not necessarily be capable of closing the inlet fully, but might have a "closed" position in which the final array of passages 39 is at least partially open. For instance, the free end of the sleeve could be provided with axially extending lands which provide a hard stop for the closed position of the sleeve, with flow gaps defined between lands around the circumference of the sleeve.
In this embodiment of the invention, the increased acceleration of the gas flow is achieved by reducing the size of the inlet 9 occurs upstream of the inlet passages 39. In the absence of inlet baffles 38, gas accelerating past the end of the sleeve 30 will expand axially across the full width of the inlet 9 before it reaches the turbine wheel 5. This would result in substantial loss of energy in the gas flow as it passes through the inlet which may largely negate the desired effect of constricting the inlet. Accordingly, such a variable geometry turbine could be expect to be very inefficient and thus impractical for many applications, such as for instance for use in a turbocharger turbine. With the present invention, as the sleeve 30 moves beyond the first and subsequent inlet baffles, the volume of the inlet 9 within which the gas can expand is reduced which similarly reduces the potential for loss in energy by expansion of the gas flow within the inlet 9 upstream of the turbine wheel. This in turn significantly improves the efficiency of the inlet. As the free end of the sleeve aligns with a given inlet baffle it is effectively equivalent to a moving radial wall member. Between these locations it is possible there may be a drop off in efficiency but this will not be to the same extent as would be experienced in the absence of any inlet baffles. Surprisingly, simulations suggest that the inlet structure of the present invention has even better efficiency than some known moving wall inlet structures, particularly at smaller inlet widths.
The embodiment of the invention illustrated in Figs 3 to 6 has three inlet baffles 38, but more or less than three baffles could be incorporated in alternative embodiments. For instance, provision of only a single inlet baffle, for example midway between the nozzle rings 32 and 33, may improve efficiency above that attainable in the absence of any inlet baffle to a sufficient extent to provide an effective variable geometry turbine structure for use in a turbocharger and other applications.
Efficiency of the turbine inlet can be expected to vary in a somewhat step-wise function of inlet size corresponding to the location of the or each inlet baffle. This effect can however be smoothed by increasing the number of baffles. Although increasing the number of baffles (which have an axial thickness) may increase aerodynamic drag and reduce the maximum cross-sectional flow area available to gas flow for any given inlet width w, this may, if necessary, be compensated by constructing the annular inlet 9 to have a larger maximum axial width and than would be the case in the absence of baffles.
The turbine according to the present invention also has a number of other advantages over the known moving nozzle ring turbine shown in Fig 1. With the present invention there are considerably reduced pressure and aerodynamic forces on the sleeve compared to those acting on a radial wall. For instance, the axial force imposed on the sleeve 30 by air flow through the inlet is much less than that imposed on a moveable radial wall. This allows the use of a smaller, less robust actuator, and also a less robust linkage between the actuator and the sleeve, as the axial force required to move the sleeve and hold it in position is much less than that required to control the position of a radial wall. The reduction in axial forces on the sleeve compared to those experienced by a radial wall also simplifies accurate control of the size of the inlet.
Employing a cylindrical sleeve as the moving component for varying the inlet size, instead of a moving radial wall, also avoids the need to provide slots to receive the vanes as the inlet width is reduced, which is a requirement of known inlet structures comprising a moving nozzle ring (as illustrated for instance in Fig 1) and also of alternative known structures in which the vanes are fixed and a slotted shroud is moved axially over the vanes to vary the inlet width. The present invention thus eliminates many of the interface requirements between the moving component and the vane array which in turn increases manufacturing tolerances. Absence of such slots also reduces the possibility of gas leakage around the vane array and simplifies sealing requirements.
Known devices comprising a moveable nozzle ring in which the moving wall member includes the vanes, for instance as shown in Fig 1, also experience significant torque as the gas flow is deflected by the vanes. With the present invention there is no such torque on the moving component which further reduces the force on the actuator and actuator linkages.
With the embodiment of the invention illustrated in Figs 3 and 4, the inlet passages 39 are defined by a nozzle assembly 34 comprising the nozzle rings 32 and 33 which support the inlet vanes 37 and baffles 38. The nozzle rings 32 and 33 thus define the sidewalls of the annular inlet 9 of the turbine. This structure may have advantages such as allowing differently configured nozzle assemblies to be fitted to a common turbine housing so that the inlet structure (i.e. configuration of inlet passages 39) may be varied between turbines which are otherwise substantially identical. This (modular) construction may have manufacturing benefits. However, it will be appreciated that the vanes 37 and baffles 38 which define the passages 39 (or any other structure which may define the inlet passages 39 as described below), need not be formed in a separable modular nozzle assembly, but could be cast or machined integrally with the turbocharger housing (e.g. the bearing housing and/or turbine housing in a typical turbine structure). In such embodiments, sidewalls of the inlet 9 need not be formed by discreet nozzle rings as with the embodiments of Figs. 3 and 5. Accordingly, although in the description below reference numerals 32 and 33 are conveniently used to identify sidewalls of a turbine inlet 9, these are not to be considered limited to the nozzle rings 32 and 33.
In the embodiment of the invention illustrated in Figs 3-6, the turbine nozzle comprises three inlet baffles 38, but as mentioned above there may be more or less inlet baffles in alternative embodiments of the invention. For instance, embodiments with only one or two inlet baffles are effective in significantly increasing the efficiency of a turbine inlet in which the moving component used to vary the inlet size is a cylindrical sleeve surrounding the vane array. Similarly, embodiments with more than three baffles may be advantageous in some embodiments. In some applications, such as for instance turbocharger applications, it is expected that 3 to 6 baffles would be appropriate.
The baffles need not be axially equi-spaced across the width of the inlet 9, and in the case of a single baffle this need not be located mid-way between side walls of the inlet 9. For instance, the axial spacing between any two adjacent baffles, or between a baffle and an adjacent side wall of the inlet may increase or decrease from one axial side of the inlet to the other, or may first increase and then decrease, or vice versa. For instance, where there is more than one inlet baffle, the axial space between the adjacent baffles and between any baffle and a side wall of the inlet may reduce/increase across the inlet 9 so that as the inlet is progressively closed by the cylindrical sleeve, the axial width of any exposed inlet passages 39 reduces/increases.
In the embodiment of the invention illustrated in Figs 3-6, each of the inlet baffles comprises a radially extending wall of constant thickness so that opposing surfaces of each baffle lie in a radial plane. In addition, facing surfaces of each baffle are parallel both to one another and to the facing surfaces of the nozzle rings 32 and 33 which defined the side walls of the annular inlet 9. In alternative embodiments of the invention the opposing, surfaces of any given baffle need not be parallel to one another and/or need not lie in a radial plane, and/or need not be parallel to the facing surface of an adjacent baffle or inlet side wall.
For example, one or both of the opposing surfaces of a single inlet baffle may lie on a frusto-conical surface of revolution about the turbine axis. Such surfaces may be parallel with one another, or may angle in opposing directions. In embodiments comprising a plurality of frustoconical baffles, adjacent baffles may have facing surfaces which are parallel to one another or which lie at an angle to one another. Similarly, the inlet side walls, (e.g. nozzle rings 32 and 33) may have surfaces which may be parallel or angled to the facing surfaces of adjacent inlet baffles.
An inlet baffle may have a uniform axial thickness, or may have a thickness which varies across its radius. For instance, a baffle may have a narrowing axial thickness with decreasing radius. For instance, an inlet baffle may taper or may have a radial cross section which is has an aerofoil shape similar to that of a conventional inlet vane.
Examples of some of the possible alternatives described above are shown in Figs 7a to 7g. These Figures are a simplified radial cross-sections through a turbine inlet 9 comprising sidewalls 11 and 12, and baffles 38. Details of inlet vanes 37 are omitted from some of the figures for simplicity.
Fig 7a illustrates an embodiment comprising an annular inlet 9 defined between side walls 32 and 33 and comprising a nozzle having three baffles 38a-38c. In this particular case baffle 38c is much closer to side wall 33 than to the neighbouring baffle 38b. Similarly the spacing of baffles 38a and 38b, and the spacing of side wall 32 and baffle 38a is greater than the spacing between baffle 38c and side wall 33. In this particular embodiment the baffles are radial and parallel to one another as well as to the side walls 32 and 33.
Fig 7b is a modification of the structure shown in Fig 7a, in which the side wall 33 of the turbine housing 1 lies of a frusto-conical surface so is angled with respect to the baffle 38c. In alternative embodiments the side wall 32 could be angled in a similar way, and in some embodiments both side walls 32 and 33 may be angled so that both sides of the annular inlet 9 taper inwardly.
Fig 7c illustrates an embodiment including three inlet baffles 38a-38c which have progressively increased spacing across the inlet 9, so that as the sleeve 30 is moved to close the inlet the axial width of the inlet passages 39 increases.
The embodiment of Fig 7d, the inlet nozzle comprises 5 baffles 38a-38e. As can be seen, in cross-section the baffles have a "fan" arrangement. That is, the central baffle 38c, which is mid way between inlet side walls 32 and 33, lies in a radial plane, but nozzle rings 38a, 38b, and baffles 38d and 38e are inclined so that they each lie on a frusto-conical surface with the effect that the inlet passages 39 tend to converge towards the central inlet baffle 38c. In addition, the effect is to define a tapering nozzle which has a maximum width defined between the nozzle ring 38a and the nozzle ring 38e, and which narrows with decreasing radius. In other words, the nozzle tapers inwardly. A similar effect could be achieved by dispensing with nozzle rings 38a and 38e and inclining the side walls 32 and 33 instead.
In Fig 7e, two inlet baffles 38 are shown which taper inwardly. The tapering of the baffles is exaggerated for clarity, and only two baffles are shown to avoid complication, but it would be appreciated that in alternative embodiments there may be only one, or three or more baffles. The vanes are omitted for clarity.
Fig 7f is a modification of the embodiment shown in Fig 7e, in which the baffles 38 have an airfoil type cross-section.
In the embodiment of Fig 7g, the baffles are again simple uniform thickness annular rings, but in this embodiment each of the rings lies on parallel frusto-conical surface so that the baffles 38 are angled with respect to side walls 32 and 33, but are parallel to one another. In the illustration the baffles angle away from the inboard side wall 32 with decreasing radius. In an alternative embodiment the baffles could be angled in the opposite direction to that shown. If baffles at each axial end of the inlet contact the sidewalls 32 and 33 they may effectively constitute nozzle rings defining the maximum width of the inlet 9.
The inlet vanes may have any suitable configuration, and may for instance have substantially the same aerofoil configuration of conventional inlet vanes or any alternative configuration selected to define a particular arrangement and configuration of inlet passages 39. That is, since the vanes and inlet baffles together define the configuration and orientation of the inlet passages 39, a wide variety of different inlet passage configurations can be achieved by appropriate design of the configuration and orientation of the individual nozzle vanes or inlet baffles, and moreover the designs can be such that there may be a variety of differently configured inlet passages within a single nozzle assembly.
As mentioned above, the efficiency of the turbine inlet may vary as the sleeve moves to different positions, and in particular may be greater at positions in which the free end of the sleeve is aligned with one of the baffles than when it is positioned between baffles. Accordingly, in some embodiments of the invention the actuator and/or control system for the sleeve may be configured so that the sleeve only moves in a step-wise manner between fully open and closed (including any "over-open" or "over-closed") positions and positions corresponding to the location of some or all of the baffles, and does not move to locations between adjacent baffles. The effect of this is to provide an inlet with a plurality of discreet sizes between a maximum and minimum. This may provide efficiency advantages, and may allow a lower cost actuator to be used.
Similarly, in some embodiments of the invention it may be desirable to locate baffles at particular axial positions corresponding to sleeve positions (i.e. inlet sizes) which are optimum for certain pre-determined operating conditions of the turbine. For instance, such positions for a turbocharger turbine might correspond to preferred inlet widths for operation at peak engine torque, rated engine speed and freeway cruise point. In some applications, for instance in turbocharged power generators, the power generating engine may be operated at fixed loads and/or speeds with no need to allow for continuous adjustment of the turbine inlet width. In such embodiments baffles can be placed at positions corresponding to the optimum inlet widths for the particular operating conditions required, and the sleeve operated to move only between positions corresponding to the positions of the or each baffle.
In the embodiments of the invention described above, each inlet vane may be viewed as comprising axially adjacent inlet vane portions separated by the inlet baffles. Thus, in the illustrated embodiment each vane 37 may be considered to comprise portions which are axially aligned so that they are equivalent to a single vane extending across the full width of the inlet 9. However, in alternative embodiments it may for instance be desirable to circumferentially stagger inlet vane portions between adjacent pairs of inlet baffles, and in some embodiments it may no longer be possible to identify the equivalent of a single vane extending across the full width of the inlet 9.
Referring once more to Figure 7a, it can be seen that in this embodiment the sleeve 30 is axially movable between an open position and a closed position. In the open position (not shown, but when the sleeve 30 is retracted in a left direction within the figure) in which there is a gas flow path through the inlet 9, between a free end of the sleeve (the end of the sleeve to the right in the figure) and a first inlet sidewall 33. The gas flow path through the inlet may be through at least one of the axially offset inlet passages. In a closed position (an example of which is shown in the figure) the size of said gas flow path through the inlet 9 between the free end of the sleeve 30 and the inlet sidewall 33 is reduced compared to that when the sleeve is in the open position. The sleeve 30 moves in a direction towards inlet sidewall 33 when the sleeve 30 is moved from the open position towards the closed position.
The sleeve 30 shown in figure 7a is in a closed position. The axial distance between any part of the free end of the sleeve (the end to the right as shown in the figure) and the inlet sidewall 33 is less than each of the respective axial distances between at least one of the inlet passage walls (in this case the baffles 38a, 38b and 38c) and the inlet sidewall 33. It will be appreciated that in this embodiment the nozzle assembly has three inlet passage walls (in this case baffles). In other embodiments the nozzle assembly may have any appropriate number of inlet passage walls. Preferably, the number of inlet passage walls (which define axially adjacent inlet passages) is two or more. In the closed position of the sleeve 30 shown in figure 7a the axial distance between the free end of the sleeve 30 and the inlet sidewall 33 is less than the axial distance between each of baffles 38a and 38b and the inlet sidewall 33. The axial distance between the free end of the sleeve 30 and the inlet sidewall 33 is substantially the same as the axial distance between the baffle 38c and the inlet sidewall 33. This is because in the closed position of the sleeve 30 shown in figure 7a the sleeve is located such that the free end of the sleeve 30 is substantially axially aligned with the position of the baffle 38c. It follows that in the closed position of the sleeve 30 shown in figure 7a the sleeve 30 is said to have moved past baffles 38a and 38b and be aligned with baffle 38c. In other embodiments, a closed position of the sleeve may be such that the sleeve is substantially axially aligned with any of the inlet passage walls (e.g. baffles). Alternatively, in some embodiments a closed position of the sleeve may be such that the sleeve is not axially aligned with an inlet passage wall (e.g. baffle) and instead, the free end of the sleeve partially blocks an inlet passage defined by at least one of the inlet passage walls. As previously mentioned, in the closed position of the sleeve 30 shown in figure 7a, the sleeve 30 is located past two inlet passage walls (baffles 38a and 38b). This is because the axial distance between the free end of the sleeve 30 and the inlet sidewall 33 is less than the axial distance between each of baffles 38a and 38b and the inlet sidewall 33. In other embodiments, in a closed position of the sleeve, the sleeve may be located past any appropriate number of inlet passage walls. For example, the sleeve may be located past one, two, three or more inlet passage walls. In some embodiments, in a closed position of the sleeve, the sleeve may be located past no inlet passage walls (such that the axial distance between the free end of the sleeve and the inlet sidewall is greater than the respective axial distance between each of the inlet passage walls and the inlet sidewall). In other embodiments, in a closed position of the sleeve, the sleeve may be located past all of the inlet passage walls (such that the axial distance between the free end of the sleeve and the inlet sidewall is less than the respective axial distance between each of the inlet passage walls and the inlet sidewall).
In the embodiment shown in figure 7a, the annular sleeve 30 has a free end (that which is to the right in the figure) which has an end face 30f which is generally flat. The end face 30f generally lies on a plane which is perpendicular to the turbine axis. In other words, for a given position of the sleeve 30, the axial distance between any portion of the end face 30f and the inlet sidewall 33 is substantially constant. In other embodiments this need not be the case. For example, the end face 30f may not be generally flat, i.e. for a given position of the sleeve 30, the axial distance between a first portion of the end face 30f and the inlet sidewall 33 is different to the axial distance between a second portion of the end face 30f and the inlet sidewall 33. For example, the end face 30f may have a circumferential profile which is generally wave shaped. In such embodiments where the end face 30f of the sleeve 30 is not flat, when the sleeve is in the closed position, the axial distance between at least a portion of the free end of the sleeve and the first inlet sidewall may be less than each of the respective axial distances between at least one of the inlet passage walls and the first inlet sidewall. In some embodiments, when the sleeve is in the closed position, the axial distance between at least a portion of the free end of the sleeve and the first inlet sidewall may be less than each of the respective axial distances between any number of the inlet passage walls and the first inlet sidewall. For example, when the sleeve is in the closed position, the axial distance between at least a portion of the free end of the sleeve and the first inlet sidewall may be less than each of the respective axial distances between at least two or at least three inlet passage walls and the first inlet sidewall. In an alternative embodiment, when the sleeve is in the closed position, the axial distance between at least a portion of the free end of the sleeve and the first inlet sidewall may be greater than each of the respective axial distances between any of the inlet passage walls and the first inlet sidewall.
In the embodiment shown in figure 7a it can be seen that, whilst in the closed position, the sleeve 30 extends past both of inlet passage walls (baffles) 38a and 38b. Baffle 38b is located within the inlet 9 such that the axial distance between the baffle and inlet sidewall 33 is slightly less than substantially 50% of the axial distance between the inlet sidewalls 32 and 33. In other embodiments, in a closed position, the sleeve may extend past at least one inlet passage wall (for example a baffle) which is located such that the axial distance between the inlet passage wall and inlet sidewall 33 is substantially 50% of the axial distance between the inlet sidewalls 32 and 33. In other embodiments, in a closed position, the sleeve may extend past at least one inlet passage wall (for example a baffle) which is located such that the axial distance between the inlet passage wall and inlet sidewall 33 is substantially between 50% and 40%, between 40% and 30%, between 30% and 20%, between 20% and 10%, between 10% and 5% or between 5% and 0% of the axial distance between the inlet sidewalls 32 and 33. Providing a inlet passage wall which is located such that the axial distance between the inlet passage wall and the inlet sidewall is substantially 50% or less of the axial distance between the inlet sidewalls has been found in some embodiments to increase the performance of the turbine and/or improve control of the gas flow through the inlet.
Another way of considering the relative positioning of the sleeve in a closed position and the inlet passage walls (baffles) as shown in figure 7a is that at least one inlet passage wall (in this case baffle 38b) is closer to the inlet sidewall 33 than it is to inlet sidewall 32. Inlet sidewall 33 is the sidewall towards which the sleeve moves when it moves from the open position to the closed position (i.e. when the sleeve moves to reduce the size of the inlet 9). Furthermore, when the sleeve 30 is in the closed position, the free end of the sleeve 30 is closer to inlet sidewall 33 than the inlet passage wall (baffle 38b) is to the inlet sidewall 33.
The sleeve 30 and inlet passage walls 38a-38c of the embodiment shown in figure 7a are configured such that the sleeve contacts the inlet passage walls. More specifically, a radially inboard surface of the sleeve contacts a radially outboard portion of the inlet passage walls. The sleeve 30 may contact at least one of the inlet passage walls 38a-38c as it moves between open and closed positions, such that the at least on inlet passage wall helps to guide the movement of the sleeve.
In other embodiments, the sleeve may substantially not contact one or more of the inlet passage walls that the sleeve is past when the sleeve is in the closed position. In other words, the sleeve may be mounted such that gas may pass between at least one of inlet passage walls (that the sleeve is past) and the sleeve when the sleeve is in the closed position. In some embodiments the sleeve may not contact any of the inlet passage walls when it is in a closed position.
For example, one possible modification of the embodiment of Figs. 3 to 6 is illustrated in Figs. 8a - 8c, and the same reference numerals are used where appropriate. Referring first to Figure 8a, it can be seen that vanes 37 are not continuous across the full width of the inlet 9, but rather vanes defining each of the annular arrays of inlet passages 39a - 39d have different radial extents. Whilst the leading edges of all of the vanes 37 lie on the same outer radius, the radius of the trailing edges of the vanes differ, in that the radial position of the trailing edge of each annular array of vanes decreases progressively from the first annular array 39a to the fourth annular array 39d. In addition, it can be seen that the inlet baffles 38a- 38c have a greater radial extent than at least some of the vanes 37 (in the illustrated embodiment it is greater than that of any of the vanes). That is, whilst they have substantially the same outer radius as the vanes 37, the inner radius of the baffles 38a - 38c is significantly less than that of the vanes 37, so that the baffles 38a- 38c extend further towards the turbine wheel 5 than the vanes 37. In this particular embodiment each of the baffles 38a - 38c has the same radial dimension but this may not be the case in other embodiments. In addition, embodiments in which the baffles extend closer to the turbine wheel than the vanes may include embodiments in which the vanes all have the same radial extent. To offer a significant turbine efficiency improvement, the baffles preferably have a radial extent greater than 110% of that of at least those vanes that do not extend as close to the wheel as the baffle, more preferably greater than 120%. Where at least some of the gas passages have a relatively radial swirl direction (e.g. at an average angle of greater than 40 degrees to the circumferential direction) the baffles preferably have a radial extent greater than 120% of that of at least those vanes that do not extend as close to the wheel as the baffle , more preferably greater than 140%. Where at least some of the gas passages have a very radial swirl direction (e.g. at an average angle of greater than 60 degrees to the circumferential direction) the baffles preferably have a radial extent greater than 140% of that of at least those vanes that do not extend as close to the wheel as the baffle, more preferably greater than 160%.
Also apparent from Fig. 8a, the axial spacing of the inlet baffles 38a - 38c is irregular so that whilst the width of the annular arrays of inlet passages 39b and 39c is the same, the axial width of the annular array 39a is greater than that of 38b and 38c, and the axial width of annular array 39d is less than that of axial arrays 38b and 38c.
Although not apparent from Fig. 8a, but illustrated in Figs. 8b and 8c, the number of vanes in each of the annular arrays 39a to 39d may differ. For instance Fig. 8b shows an annular array of fifteen vanes and Fig. 8c shows an annular array of only eight vanes which may be included in the same nozzle assembly. Other arrays may have a different number of vanes, greater than fifteen or fewer than eight, or somewhere in between (e.g. twelve). In addition, Figs. 8b and 8c show the vanes having different radial extents, and different swirl angles (that is the vanes visible in 8c are swept forwards to a greater extent than the vanes shown in Fig. 8b, and as such have a greater swirl angle).
The present invention therefore provides a great degree of flexibility in optimising various features of the nozzle to particular requirements and efficiency profiles. For instance, in one embodiment of the invention as illustrated in Figs. 8a to 8c, there may be eight vanes in the array 39d, twelve vanes in each of the arrays 39b and 39c, and 15 vanes in the array 39a. The swirl angle may be greatest in the array 39d and decrease progressively to the array 39a. This is just one example and it will be appreciated that many other variations are possible. Various factors may influence the particular nozzle design, which may include minimising turbine high-cycle fatigue (i.e. minimising the forcing function on the blades), and optimising or otherwise tailoring the efficiency and swallowing capacity of the turbine (e.g. providing low efficiency at wide inlet openings which is useful in some applications such as e.g. EGR engines as described below).
For instance, in an embodiment in which the sleeve 30 is actuated from the turbine housing side of the inlet, so that its free end moves towards the bearing housing side of the inlet 9 as the inlet is closed (this possibility is discussed in more detail further below) the arrays of inlet channels 39c and 39d are less able to stimulate vibration and fatigue in the turbine blades because the hub end of the turbine leading edge is more rigidly connected to the turbine hub (by virtue of it being closer to the turbine wheel back face). In some applications of the invention it may be desirable to maximise turbine efficiency at smaller inlet openings and thus the vane arrays 39c and 39d may have a reduced clearance with respect of the turbine wheel (as illustrated) to boost efficiency given that this may not result in any significant vibration/fatigue problem as the turbine blades are more rigidly supported in this region. In addition, increasing the swirl angle of the vanes in the array 39d can offer a slight efficiency increase when the sleeve is at nearly closed positions (in which the leading edge of the sleeve 30 extends beyond the location of the inlet baffle 38c). This would have the additional effect of reducing the rate that the cross-sectional flow area changes as a function of sleeve motion, when the sleeve is nearly closed, which allows the actuator to control the cross-sectional flow area more precisely.
For certain engine applications (such as for EGR) it may be desirable to reduce the turbine efficiency in one or more of the arrays of inlet channels 39a - 39d. For instance, it may be desirable to reduce efficiency at relatively open inlet widths in some applications. Such reduced efficiency could for instance be achieved by reducing the radial extent of the vanes (as illustrated) and/or by increasing the circumferential width or otherwise configured of the vanes to reduce the effective inlet area. The inlet area could be reduced further by providing other obstacles to flow, for instance posts extending axially into the channel. The axial width of the array can be reduced to increase effective friction losses, and the swirl angle of the vanes could be configured to provide mixed swirl. Other examples (not illustrated) could include a ring of similar and evenly spaced posts, two or more concentric rings of posts, a ring of unevenly and randomly distributed posts, or even a ring of vanes arranged to reverse the swirl angle of the gas (i.e. to rotate gas in the opposite direction to the turbine).
Other possible examples of vane arrays that might define any given annular array of inlet passages are illustrated in Figs. 9a - 9c which are axial sections showing an inlet baffle 38 supporting vanes 37. In Fig. 9a there is a relatively small number of vanes 37 with a relatively high swirl angle. In addition, the vanes are relatively "thick" and extend to a relatively small internal radius to provide a relatively small radial clearance around the turbine wheel. With such an arrangement it is easier for an actuator to achieve high resolution control of the cross-sectional flow area because it varies less for a given sleeve movement The increased swirl may be useful for a vane array positioned to correspond to relatively small inlet widths, which could provide a small efficiency improvement.
In the embodiment of Fig. 9b, relatively small "splitter vanes" 37a are located between adjacent pairs of main vanes 37. In this case there are an increased number of vanes compared with the embodiment of Fig. 9a, but the vanes have a reduced radial extent so that there is a greater radial clearance between the vanes and the turbine wheel. Splitter vanes have a chordal length (i.e. a straight-line length between the leading edge and trailing edge of the vane) which is less than that of the main vanes. The splitter vanes may be advantageous in some embodiments to reduce vibration excited in the turbine blades. Splitter blades may be used to lessen reduction in flow through the inlet caused by skin effect friction. This is because the splitter vanes may have a smaller surface area that is exposed to the flow of gas through the inlet than that of the main vanes. Splitter vanes may also direct gas flow towards the turbine wheel in a similar way to conventional (or main) inlet vanes, as previously discussed. Although in figure 9b a single splitter vane 37a is located between adjacent pairs of main vanes 37 (i.e. such that the splitter vanes and main vanes are circumferentially alternating), this need not be the case. It will be appreciated that any appropriate layout of main vanes and splitter vanes may be used, for example, there may be more than one splitter vane between an adjacent pair of main vanes or the spacing between adjacent splitter vanes and/or main vanes may vary. Furthermore, there may be more than one type of splitter vane, for example splitter vanes with different characteristics, such as size and shape may be used. In some embodiments, splitter vanes may be located radially inboard or radially outboard of the main vanes. In some embodiments the radial distance between the trailing edges of the splitter vanes and the turbine wheel may be greater than the radial distance between the trailing edges of the main vanes and the turbine wheel.
In the embodiment of Fig. 9c, the vanes have a "cut-off" configuration rather than a full airfoil configuration which can be expected to provide reduced efficiency which may be useful in some applications. In addition, obstructions 37b are located between adjacent vanes 37 which can further reduce efficiency.
Further possible embodiments of a nozzle assembly according to the invention illustrated in Figs. 10a - 10e, 11a - 11e, and 12a - 12e. In each case, each of the figures a - d is an axial section showing the vanes of a particular annular array of inlet passages 39 which together constitute 5 adjacent annular arrays of inlet passages in the nozzle assembly as a whole. Each figure e is an illustration of the combined locations of all the vanes from figures a - d.
Referring first to Figs. 10a - 10e, it can be seen that each of the annular arrays 39a - 39d comprise different numbers of vanes, which for some embodiments may have different configurations such as curvature and/or swirl angle and/or radial extent and/or thickness etc. However, in each of the arrays there is a vane with a leading edge at 0° (the top of the vane array is seen in the Figures) and also at 120° and 240°. This provides support edges across the width of the assembly as a whole (and thus across the width of the inlet 9 as a whole) which can be useful for guiding the sleeve used to vary the inlet width. With a conventional nozzle array, in which vanes extend across the full width of the inlet 9 and are equi-spaced around the circumference of the inlet, the turbine blade produces an even pattern of vane wakes as it sweeps past the trailing edges of the vanes and is thus subjected to one or more main frequencies of vibration. Depending upon the turbine speed these frequencies of vibration may match a resident vibration mode of the blade leading to resonant excitation which contributes to metal fatigue. However, with the illustrated embodiment of the present invention, there are several different patterns of vane wakes, each of which could excite blade vibration at certain speeds, but less strongly than if the blades were aligned circumferentially.
Referring now to the embodiments of Figs. 12a to 12e, it can be seen that this is very similar to the embodiment of Figs. 10a to 10e except that the vane at 120° has been moved to 112.5° and the vane at 240° has been moved to 225° (it will be appreciated that these are non-limiting example positions, and other position could be chosen including a reverse arrangement with the angles shifted slightly above 120° / 240°).
Accordingly the positions of some of the vanes (between 0° and 240°) are shifted together slightly, while other vanes are shifted apart (from 240° up to 360°/0°). This can alleviate vibration induced by the turbine blade passing each vane and corresponding wake (i.e. 9^th order excitation for the array in fig 12a, 12 ^th order for that in fig 12b, 15 ^th order in figure 12d). This is because if the first (squeezed) set of vanes are passed at a rate that begin to induce vibration, these will be followed by a second (stretched) set of vanes that are passed at a different frequency which does not excite the vibration. This is then followed by the first (squeezed) set of vanes again that induces vibration at the resonant frequency but at the wrong phase angle and so forth.
The amount of flow obstruction presented by the vanes is now lower in the top left of each of figures 12a, 12b and 12d. This would ordinarily induce considerable 1^st order vibration (1^st order vibration is caused by variation in the gas flow between one side of the turbine and the other, so vibration would be induced if the turbine is rotating at one of the resonant frequencies of it's blades). If this is problematic, one option is to provide at least one of the vane arrays (in this case the third array shown in figure 12c) with an extra vane in the "stretched" region so that in this region the vanes are instead "compressed" together. This will for instance be effective when the sliding sleeve is at one or a small number of positions.
The embodiment of Figs. 11 a to 11e shows a modification which may be provided in addition to or as an alternative to that illustrated in figure 12a to 12e. Here the vanes in the stretched region (240° to 360°) are thickened to compensate for the reduction in the angular density of vanes. Alternatively or in addition the vanes in the compressed region (120° to 240°) may be thinner. Rather than changing the blade thickness, it would be possible to vary other characteristics of the blades, such as for instance the blade length.
Referring to the embodiments discussed above in relation to figures 10 to 12, it will be appreciated that the vanes in each annular array of each embodiment have a circumferential distribution which is uniform in that the vanes are equi-spaced around the annular array. For instance, the circumferential distance between the centre of any vane and the centre of an adjacent vane is the same. In other words, the circumferential distance between the centres of any adjacent vanes is the same. The centre of a vane may be defined as half way along a chord which extends between the trailing and leading edges of the vane. However, the centre of the vane may be considered as a datum point for each vane which may be defined in any other appropriate manner, providing it is defined in the same manner for each vane. In some embodiments the vanes of an annular array may have a circumferential distribution which is non-uniform in that the vanes are not equi-spaced around the annular array. For example, within an annular array, the circumferential distance between the centres of two adjacent vanes (which form a first set of adjacent vanes) may be different to the circumferential distance between the centres of two other adjacent vanes (which form a second set of adjacent vanes). Furthermore, the circumferential distance between the centre of a first vane and the centre of a second vane adjacent the first vane may be different to the circumferential distance between the centre of the first vane and the centre of a third vane adjacent the first vane. In some embodiments the circumferential distribution of the vanes extending into a first annular array may be different to the circumferential distribution of the vanes extending into a second annular array. For instance, in some embodiments the circumferential distribution of vanes extending into a first annular array may be non-uniform, whereas the circumferential distribution of vanes extending into a second annular array may be uniform. Furthermore, in some embodiments the circumferential distribution of vanes extending into both a first annular array and a second annular array may be non-uniform, however the circumferential distribution of vanes extending into the first annular array and the second annular array may be different.
It will be appreciated that these are just some of the many different arrangements made possible by the present invention.
In the embodiments of the invention described above, each inlet baffle is annular and as such extends around the full circumference of the inlet 9. Each inlet baffle may however be considered to comprise an annular array of adjacent baffle . portions defined between adjacent inlet vanes (or vane portions). In the illustrated embodiment of Figs 3-6, the baffle "portions" of each baffle 38 are aligned to define the respective annular baffle. However, in alternative embodiments it may for instance be desirable to effectively omit some baffle portions, and in some embodiments it may no longer be possible to identify the equivalent of a single inlet baffle extending annularly around the full circumference of in the inlet 9.
Non limiting examples of various alternative embodiments are illustrated in Figs 13a to 13f and 14a to 14d. These Figures are schematic radial views of un-rolled portions of the circumference of the respective embodiments corresponding to the views shown in Figs 2 and 5 for example.
Figure 13a illustrates an embodiment in which inlet vane portions 37a-37d extend between adjacent inlet baffles 38 and between in the baffles 38 and side walls 32 and 33. No single inlet vane 37 is continuous across a baffle 38, with the effect that individual inlet passages 39 are arranged in circumferentially staggered annular arrays 39a-39b (there is circumferential overlap between axially adjacent passages 39).
Figure 13b is a modification of the embodiment shown in Figure 8a, in which some vanes 37 do extend across the full width of the inlet 9, whereas other vane portions extend only between neighbouring baffles 38 or between a baffle 38 and enabling inlet wall 32/33. There are again four annular arrays of circumferentially adjacent inlet passages 39a-39d, but in this case each annular array includes inlet passages 39 of different sizes, in this case some have a rectangular cross-section whereas others have a square cross-section.
Fig 13c illustrates an embodiment of the invention in which inlet vanes 37 extend from the side walls 32 and 33 respectively, but in which no single inlet vane 37 extends the full width of the inlet 9. The effect in this case is to create four annular arrays of circumferentially adjacent in the passages 39a-39b, wherein the passages adjacent each side wall 32 and 33 have a rectangular cross-section and the passages 39b and 39c define between the baffles 38 have a generally square cross-section.
Fig 13d illustrates an embodiment in which inlet vanes 37 extend only half way across the full width of the inlet 9, in this case extending from side wall 32 to a central inlet baffle 38b. In this case there only two annular arrays of inlet passages 39a and 39b whereas the "arrays" of 39c and 39d are each replaced by a single annular passage way 39c and 39d respectively.
Although a single 'vaneless' space 39d may be provided without any vanes or other structures crossing it, if two vaneless spaces are provided (as shown in figure 13d) then the baffle separating them will require support. This could for instance be in the form of at least three small axially extending struts spaced around the turbine inlet between that central baffle and a neighbouring baffle or a side wall.
A single vaneless space 19c between one of the side walls 32 or 33 and the annular arrays of passages (i.e. at one axial end of the turbine inlet) may be very beneficial. By including a vaneless space to be exposed when the sleeve is fully open, the flow range of the variable geometry turbine can be considerably increased. Optionally the radially outboard inlet of the vaneless space may be axially wider than the radially inboard outlet (not illustrated).
The embodiments of Figures 13e and 13f also comprise at least one annular inlet passage absent any vanes. In the embodiment of Fig 13e, there is a single inlet baffle 38 and vanes 37 extend from side wall 32 to the inlet baffle 38, but do not extend from the inlet baffle 38 to the side wall 33. This creates a first annular array of adjacent inlet passages 39a and a single annular inlet passage 39b. Figure 13f is an extreme example of the embodiments shown in Fig 13e, in which there is only a single vane 37 shown which extends from side wall 32 to the single inlet baffle 38. Where the Figure shows only a single vane 37 it is to be understood that there is a diametrically opposed vane 37 so that there are two adjacent semi-circular inlet portions 39a in a first annular array, and a axially adjacent single annular inlet passageway 39b. In practice, there are unlikely to be any applications to the present invention which will require only a single pair of diametrically opposed vanes 37.
In some embodiments there may be at least 6 vanes to help ensure the ends of the vanes are close enough together without being impractically long and inducing excessive gas friction. This may also help the gas to swirl in relatively homogenously (e.g. constant swirl angle around the circumference) which may be difficult to achieve with fewer than 6 vanes. In some embodiments there may be at least 9 vanes, preferably at least 12 and normally at least 14. For instance, such a turbine inlet could have 9-18 vanes, with very small turbocharger turbines suiting perhaps 13-16 vanes and very large automotive ones suiting perhaps 15-18 vanes.
In some embodiments of the invention the skin friction induced by the baffles may be reduced by reducing the radial extent of the baffles and vanes, and hence reducing the vane length. If necessary or desired the number of vanes can be increased to increase the "vane solidity".
With the materials available at present, and the gas pulsations and temperature variations expected, as many as 30 circumferentially distributed gas passages may for instance be appropriate for some applications of the invention, such as for instance heavy duty engine turbocharger applications. In other embodiments as many as 40 circumferentially distributed gas passages perhaps be appropriate, for instance for light duty engine turbocharger applications. For fuel cell turbocharger applications 75 or more circumferentially distributed gas passages may be desirable (due to the lower exhaust temperatures and absence of gas pulsations). For very large turbines operated at low temperatures, low turbine pressure differentials, low gas speeds, and in the absence of gas pulsations and temperature variations, 100 circumferentially distributed gas passages may appropriate.
Therefore the number of circumferentially distributed gas passages (which may all be at least partially axially overlapping) may generally be between 8 and 100. In other embodiments there may be between 12 and 100, or between 18 and 100 (perhaps 23 and 100, possibly 26 and 100 or conceivably 30 to 100). According to one embodiment of the invention, there may be provided two axially divided annular arrays of gas passages, each annular array having between 12 and 100 circumferentially distributed gas passages.
Such structures with large numbers of circumferentially distributed gas passages are not shown for simplicity, but it should be understood that the structures described herein are examples and the principles described may be implemented with large numbers of circumferentially distributed gas passages.optionally between 18 and 100.
It will thus be appreciated that the number of vanes can vary from those illustrated in Figs. 13a-13f.
Figures 14a to 14d show embodiments in which vanes 37 extend across the full width of the inlet 9, but at least one or more inlet baffles extend only a part way around the circumference of the inlet.
Fig 14a illustrates an embodiment of the invention comprising a single inlet baffle 38 which extends around the full circumference of the inlet 9 (in this case midway between the side walls 32 and 33), and inlet baffle portions 38a and 38c which extend between other pairs of vanes 37 (which extend across the full width of the inlet 9).
The embodiment of Fig 14b differs from the embodiment of Fig 14a in that there are two baffles 38a and 38d which extend around the full circumference of the inlet 9, but where baffle 38c is split into discontinuous baffle portions extending between every other pair of vanes 37.
Figure 14c is an embodiment in which there is no single inlet baffle extending the full circumference of the annular inlet 9, rather inlet baffles 38a-38c comprise baffle portions extending between respective pairs of inlet vanes 37. In the particular embodiment illustrated, the inlet baffle portions 38b are circumferentially staggered relative to the inlet baffle portions 38a and 38c. The individual inlet passages 39 are axially staggered, in that there is axial overlap between circumferentially adjacent passages 39.
The embodiment of Fig 14d shows another example of a nozzle which has no single inlet baffle extending the full circumference of the annular inlet 9. Moreover, this embodiment shows how the spacing between inlet baffle portions extending between one pair of vanes may differ to that between the baffle portions extending between an adjacent pair of vanes.
The embodiments of Figs 13 and 14 have generally regular arrays of inlet passages 39. However, this need not necessarily be the case. For example, Fig 15 schematically illustrates an embodiment in which there is no single inlet baffle extending around the full circumference of the inlet, and no single inlet vane extending across the full width of the inlet. In this case the passage array is very irregular. In practice this specific pattern may not be particularly desirable, but it is included to illustrate the extent of variation that can be achieved (subject to manufacturing suitability) with some embodiments of the present invention.
It will be appreciated that the vanes or vane portions of the various embodiments of the invention described above may have any suitable cross-sections or configurations. For instance, the vanes may have a relatively conventional airfoil configuration. In general, it may be advantageous to ensure that the leading edge of each vane has an increased thickness compared with the trailing edge of each vane. Increasing the thickness of the leading edge of the vanes offers higher tolerance to any variations in the incident angle of gas flow impinging on the vanes. That is, depending on the flow/pressure in the turbine volute the direction that gas will impinge on the vanes can vary. If gas hits a simple sheet structure at an angle it may cause the gas flow on the lee-side to separate off from the sheet leaving a vortex/turbulent area which greatly reduces efficiency.
In addition, it will be appreciated that the configuration and/or arrangement of the vanes may vary in order to produce inlet flow passages 39 of a desired configuration. For example, it is generally beneficial for the passages 39 to curve rather than follow a substantially straight path.
In view of the wide variety of possible alternative structures according to the present invention, it may not therefore always be possible to view the inlet nozzle structures as comprising discernable inlet vanes in the conventional sense or even vane portions. Similarly, it may not be possible to identify individual inlet baffles or baffle portions as such. Rather, in more general terms it may be more appropriate to consider the invention as relating to an inlet nozzle structure which defines a plurality of discrete inlet passages which may take a variety of configurations and be arranged in a variety of different ways. Common to all of the embodiments of the invention illustrated in Figures 3 to 15, the turbine nozzle comprises at least two axial spaced annular arrays of inlet passages. In some embodiments a single axial "array" may in fact comprise only one circumferential inlet passage. However, in most embodiments it is envisaged that each annular array will comprise many inlet passages circumferentially spaced (e.g. adjacent) around the annular inlet.
In any given embodiment of the invention it may be possible to identify annular arrays of circumferentially spaced inlet passages 39 in different ways. For instance, Figs 16a to 16d show the embodiment of Fig 9d, but with axially spaced annular arrays of circumferentially spaced in the passages 39 identified in different ways. For instance, referring first to Fig 16a, four annular arrays of inlet passages 39a-39d are identified. In this case, the inlet passages of the first array 39a have differing axial widths, but are adjacent one another. The inlet passages 39b of a second array each have the same axial width but are staggered relative to one another, and are not always adjacent one another. A third annular array of circumferentially spaced inlet passages 39c is identified which have the same axial width and position, but are not adjacent one another. Finally, a fourth annual array of circumferentially spaced inlet passages 39d corresponds to the first array 39a.
For any particular embodiment of the present invention it may not be necessary to identify more than two distinct axially spaced annular arrays of inlet passages, even when more than two such arrays may exist. For instance, Fig 16b identifies only two annular arrays of spaced inlet passages 39a and 39b. In this case, the inlet passages in each annular array are neither circumferentially nor axially adjacent one another. In Fig 16c two different annular arrays of circumferentially spaced inlet passages 39a and 39b are identified. In this case the inlet passages 39a of the first array are actually circumferentially adjacent inlet passages 39b of the second array, the axial spacing being achieved by an overlap in the axial dimension of the passages of each array. That is to say, the inlet passages 39b have a greater axial width than the inlet passages 39a so that at least a portion of each inlet passages 39b is axially spaced from the inlet passages 39a. Finally, Fig 16d shows another approach to identifying two axially spaced annular arrays of inlet passages 39a and 39b. In this case the passages 39a and 39b are axially adjacent one another, but the passages 39 of each array are not circumferentially adjacent.
It will be understood that further possible distinct annular arrays of inlet passages according to the present invention can be identified with the embodiment of the invention illustrated in Fig 16a-16d, and that similarly in other embodiments of the invention it will be possible to define distinct axially spaced annular arrays of inlet passages in different ways.
With all embodiments of the invention illustrated in Figs 3 to 16, each inlet passage 39 has a generally rectilinear cross section. However, alternative cross sections are possible, such as for instance diamond shaped or hexagonal cross-sections as shown in Figs 17 and 18 defined by inlet walls 50. These are examples of embodiments wherein it is not necessarily appropriate to consider any single inlet wall 50 as constituting either a vane in the conventional sense or an inlet baffle distinct from inlet vanes. However, in each case the nozzle structure clearly comprises a plurality of inlet passages 39. In Figs 17 or 18 one approach to identifying two distinct axially spaced annular arrays of circumferentially spaced passages, 39a and 39b is shown. In each of these embodiments the inlet passages in each annular array identified are circumferentially adjacent one another. Another feature of these embodiments is that adjacent annular arrays which are spaced axially across the inlet overlap one another to a degree. That is, a portion of each individual inlet passage 39b of the second annular array axially overlaps a portion of each inlet passage 39a of the first annular arrays. It is believed that such nozzle structures will further smooth any tendency for the turbine efficiency to have a "stepped" characteristic with varying inlet size.
Figs 19 and 20 show the same embodiments as Figs 17 and 18 but illustrate a different approach to identifying axially spaced annular arrays of inlet passages 39a and 39b. In this case, in each embodiment two annular arrays of inlet passages which are axially spaced but which do not axially overlap are identified.
It will once again be appreciated that the precise configuration of the inlet passages is governed by the configuration of the walls defining them, and that the nozzle structure may be designed such that there are individual inlet passages within the nozzle structure with a different configuration to that of other inlet passages within the same nozzle. A variation of the "honeycomb" embodiment of Figs 17 and 18 is for instance illustrated in Fig 21. With this embodiment inlet walls 50 again define generally hexagonal inlet passages 39 but in this case the array is somewhat irregular. One particular approach to identifying examples of two axially spaced annular arrays of inlet passages 30a and 39b is illustrated. It will be appreciated that alternative spaced annular arrays of inlet passages may be identified by taking a similar approach to that described above in relation to Figs 16a to 16d for example.
In all of the embodiments of the invention illustrated in Figures 3 to 21, and described above, the inlet nozzle structure comprises a plurality of inlet passages including at least one inlet passage spaced circumferentially and axially respectively from two other inlet passages, or indeed spaced both circumferentially and axially from each of the other two inlet passages. The spacing may be such that at least some of the passages are adjacent one another, and there may be axial and/or circumferential overlap between at least some of the passages. One other way to express this relationship is that in each of the embodiments of the invention illustrated it is possible to identify a first pair of inlet passages that are circumferentially spaced - and possibly adjacent and/or circumferentially overlapping (or staggered), and a second pair of inlet passages which are axially spaced - and possibly adjacent and/or overlapping (or staggered). Depending on how the pairs are identified, in some cases only three passages may be required to define the two pairs, with one inlet passage common to both the first and second pairs.
For example, Fig 22 shows the embodiment of Figs. 18 and 20 described above. Referring to Fig 17, a first inlet passage 60 is circumferentially spaced from a second inlet passage 61 and is axially spaced from a third inlet passage 62. In this case the passages are adjacent to one another. Similarly, a single inlet passage 63 is circumferentially spaced from an inlet passage 64 and axially spaced from an inlet passage 65. Here the passages are not adjacent. Inlet passages 60 and 61 can for instance be considered to comprise a first pair of circumferentially spaced inlet passages (as well as axially spaced by virtue of their axial overlap), and inlet passages 60 and 62 can be considered to comprise a second pair of inlet passages that are axially spaced, with the single inlet passage 60 common to both pairs. Likewise, inlet passage 63 and 64 can be considered to comprise a first pair of inlet passages which are circumferentially spaced but not adjacent and inlet passages 63 and 65 can be considered to comprise a second pair of inlet passages which are axially spaced (and in this case also circumferentially spaced), in this case a single inlet passage 63 being common to both pairs. Alternatively, inlet passages 60 and 63 can for instance be considered to comprise a first pair of circumferentially spaced inlet passages, and inlet passages 64 and 65 can be considered to comprise a second pair of axially spaced inlet passages.
Referring to figures 23 to 25, these illustrate embodiments of the invention in views comprising an array of "diamond shaped" inlet passages 39 in axial-cross section corresponding generally to figures 7a, 7b and 7d respectively. This illustrates that the nozzle may taper inwardly, comprising individual inlet passages 39 which narrow with decreasing radius. It will be appreciated that the same approach could be taken with the hexagonal inlet passage array as illustrated in Figs 18 and 20 for example.
More generally it will be appreciated that the configuration of inlet passages 39 may vary considerably between embodiments of the invention. For instance, inlet passages 39 may have a greater or lesser forward sweep relative to the direction of rotation of the turbine blade 5 to induce more or less swirl in the inlet gas flow. The degree of sweep (or swirl angle) may vary along the length of the inlet passages. Different inlet passages may have different swirl angles. For instance, one annular array of inlet passages may all have the same swirl angle but this may differ from the swirl angle of another (e.g. adjacent) annular array of inlet passages.
Also, individual inlet passages 39 may have a cross sectional area which is constant along its length, or which tapers, or which for instance narrows and then widens again between its upstream to downstream ends. For example the cross-sectional area may change from one size and/or shape at the inlet of the passage to another size and/or shape at its outlet. For instance the cross-sectional shape may be diamond shaped or hexagonal at the inlet and change gradually to a more rectangular or square shape at its outlet.
In some embodiments of the invention it may be appropriate to have inlet passages 39 that are restricted to the radial plane, broadly equivalent for instance to known turbocharger nozzle designs comprising straight vanes, i.e. vanes which lie in a plane containing the axis of the turbocharger.
Although in one sense the "diamond" and "honeycomb" structures shown in Figs 17 and 18 for example can not necessarily be considered to comprise vanes in the conventional sense, or clearly discernable baffles, it is in fact possible to construct such nozzle structures from discrete inlet baffles of an appropriate configuration. For example, Fig 26 shows how the structure shown schematically in Fig 18 can be constructed by pressing together axially adjacent baffles, four of which 78a-78d are identified in the figure. Each of these baffles is an annular ring but is circumferentially corrugated along the lines of a "wavy washer" and are aligned "out of phase" (circumferentially staggered) so that hexagonal inlet passages 39 are defined between adjacent baffles.
If the corrugations of each baffle extend strictly radially, each of the inlet passages 39 will extend along a radius. However, by sweeping the corrugations forward relative to the circumferential direction of each baffle, inlet passages 39 which similarly sweep forwards can be defined. This is illustrated in Figs 27a to 27d. Fig 27a shows seven baffles in the baffles 80 provided with spiral corrugations prior to assembly into a nozzle structure. To complete the nozzle the baffles 80 are pressed together and joined by any suitable means. Fig 27b is a cross section through a part of a turbocharger with the resultant nozzle structure in situ. Fig 27c is an end view of the nozzle structure surrounding the turbine wheel 5, looking along the axis of the turbocharger shaft 4m, and Fig 27d is an axial cross section corresponding for instance to Fig 23.
It will be appreciated that various modifications can be made to the embodiment of the invention illustrated in Figs 26 and 27a to 27d. For example, the corrugations or waves could take a variety of forms including for instance sinusoidal and diagonal or "V" shapes, or any other shape appropriate to define the required configuration of inlet passages 39. Furthermore, whereas with the illustrated embodiment each of the baffles 80 is corrugated, in other embodiments it may be desirable to place non-corrugated (e.g. strictly radial) baffles between one or more pairs of corrugated baffles to modify the configuration of the inlet passages 39 and certain axial locations across the inlet. Similarly, individual corrugated baffles 80 need not have the same depth of corrugation. Moreover, in some embodiments the baffles 80 can be pressed together in such a way as to have greater or smaller areas of contact between baffles 80 to that illustrated in figures 21 to 22 to again vary the configuration of the inlet passages. Indeed, the contact area may vary across the radius of the nozzle structure to define individual inlet passages 39 which have a corresponding varying cross sectional area.
Various possibilities exist for joining the baffles together. For instance the baffles may be brazed together (for example using silver brazing or other brazing appropriate for the high temperatures encountered in a turbine inlet) or adjacent baffles may be provided with mating formations, such as complimentary projections and indentations. Alternatively, baffles may be spot welded together. Other appropriate manufacturing methods will be apparent to the appropriately skilled person.
With the embodiment of the invention illustrated in Figs 26 and 27a to 27d, adjacent baffles are aligned in anti-phase so that every other baffle 70 is directly aligned. This creates a honeycomb like structure in which axially adjacent inlet passages 39 are precisely aligned along the axis of the turbocharger. However, by introducing a slight circumferential offset into each successive baffle as shown in Fig 28 it is possible to circumferentially stagger axially adjacent inlet passages 39 as illustrated by the lines 90 shown skewed at an angle to the dotted line 91 which is parallel to the turbocharger axis. This could for instance be used to partially alleviate high cycle fatigue in turbine blades when the sleeve is at the open position.
In some embodiments the baffles may be generally annular and have a generally hyperbolic paraboloidal surface (i.e. have a surface which is generally defined in part by the surface of a hyperbolic paraboloid). A hyperbolic paraboloid may be commonly referred to as having a saddle shape. One type of hyperbolic paraboloid may be defined in Cartesian geometry by the equation $z = \frac{x^{2}}{a^{2}} - \frac{y^{2}}{b^{2}} .$
where x, y and z are Cartesian co-ordinates in three dimensions and a and b are constants. In some cases a and b may have substantially the same value. The hyperbolic paraboloidal or 'saddle' shaped baffle may include any number of corners, edges or vertices which are located above or below the major plane of the baffle. While such a baffle may conveniently incorporate four such corners, edges or vertices, it may incorporate any other number as desired, such as six, eight or more.
Figure 29 illustrates an alternative approach to producing a honeycomb structure substantially the same as that shown in 26 but formed from a single helical baffle structure 100 rather than individual annular baffles as illustrated for instance in Fig 26.
A structure such as that shown for instance in Fig 21 could also be fabricated from corrugated baffles, but with the corrugations defined in order to produce the more "irregular" honeycomb array illustrated. In this case, and referring back to Fig 21, the walls 50 could for instance be provided by pressing or otherwise joining together annular baffles of three different configurations (two of which are mirror images of each other) as illustrated in bold line, which shown three baffle plates pressed adjacent one another and a fourth baffle plate adjacent the wall 33 of the inlet 9.
As illustrated in Figs. 30a and 30b, some of the flow channels may be blocked to tailor efficiency in regions corresponding to certain inlet widths. For instance in Figs. 30a and 30b part-hexagonal channels at the axial ends of the nozzle are shown blocked out. In the case of Fig. 30b, the axial width of the channels in these regions is reduced which may be beneficial in reducing vibration on the blade when these channels are exposed to the inlet flow.
Whatever the configuration, or method of construction, of the nozzle assembly (e.g. assemblies comprising vanes/baffles or "honeycomb" structures), the surfaces defining the inlet passages and/or the sleeve which varies the size of the gas flow path through the inlet may be at least partially coated with a suitable catalyst for oxidising soot at the high operating temperatures of the turbine in order to help prevent deposition and accumulation of soot on surfaces of the nozzle.
It will be appreciated by the skilled person that there are a variety of different ways in which the nozzle assembly and other details of the inlet structures in accordance with the present invention can be constructed.
Embodiments of the invention illustrated for example in Figs 3, 4a-4b, 7a-7g, 23-25 and 27a-27d each show an turbine inlet structure in which the sleeve 30 slides around the outside diameter of the nozzle structure, so that the sleeve acts to block/unblock inlet passages 39 at their upstream ends. Although not in accordance with the present invention and described herein for the purposes of reference only, in alternative variable geometry turbines the cylindrical sleeve may be located on the inside diameter of the nozzle so that it opens and closes inlet passages 39 at their downstream ends adjacent the turbine wheel. For example, Figs 31a to 31c show a modification of the embodiment of the invention illustrated in Figs 3 and 4a-4b that is not in accordance with the present invention, wherein a modified sleeve 130 slides across the inlet passage 9 downstream of inlet passages 39 so that it slides between the nozzle and turbine wheel. Other details of this variable geometry turbine are substantially the same as those shown and described in relation to Figs 3 and 4a-4b and like reference numerals are used where appropriate. The only significant differences are those necessary to accommodate the reduced diameter sleeve 130, namely repositioning of one of the two nozzle rings, identified as nozzle ring 132, and flanges 130a to which support rods 31 are connected. In particular, it will be appreciated that each of the various nozzle structures illustrated and described above, and all variations as described above, can be included in variable geometry turbochargers that are not in accordance with the present invention in which the sleeve 130 is positioned around the turbine wheel at the internal diameter of the inlet nozzle.
In some embodiments of the invention it may be advantageous to provide two axially slideable sleeves, comprising a first sleeve located around the outside diameter of the inlet passages and a second cylindrical sleeve located at the inside diameter of the inlet passages. In such cases the first and second sleeves may have the same axial extent across the width of the inlet 9, or one of the two sleeves may extend further than the other at least some positions, so that in such positions the overall axial width of the annular inlets differs from its upstream to its downstream openings. The two sleeves could be coupled together (or integral) for actuation as a unit, or may be independently arranged and actuated.
Embodiments of the invention described above show the sleeve 30 and 130 extending across the annular inlet 9 from the bearing housing side of the turbine wheel. In alternative embodiments of the invention the sleeve may extend across the annular inlet 9 from the turbine housing side of the wheel. In other words, the sleeve and actuating mechanism can be housed in the turbine housing rather than in the bearing housing. Examples of such embodiments of the invention are shown in Figs 32a and 32b. Although not in accordance with the present invention this is also shown in Figs 33a and 33b.
Actuating the sleeve from the turbine side can be beneficial for mitigating high cycle fatigue of the turbine blades, because when the sleeve is nearly closed, exposing just one ring of inlet passages. When the sleeve is closed from the turbine side, then ordinarily it closes towards the bearing housing side, and towards the rear of the turbine wheel - which is where the blade is most robustly supported by the turbine back face.
It should also be noted however that it is possible to provide the actuator on one side, arranged to pull the sleeve from the other side via one or more struts (generally at least two and usually three will be necessary). Therefore the actuator could be in the bearing housing, and connected by some "pull-rods" (not shown) to a sleeve in the turbine housing. The "pull-rods" pull the sleeve towards the bearing housing to block the gas inlets. Alternatively the actuator could be in the turbine housing connected by "pull-rods" to a sleeve that is pulled from the bearing housing towards the turbine housing so as to block the gas inlets. These embodiments are not illustrated, partly for brevity and partly because it will typically be preferable to provide the actuator and the sleeve on the same side of the annular turbine inlet.
If pull rods are desired, it may be desirable to align them circumferentially with vanes, for example along the edges (e.g. the radially outer edges) of some of the vanes (e.g. of three sets of axially divided vanes), which may be circumferentially aligned (i.e. non-staggered) vanes.
One possible advantage of the pull rod system (not shown) is that it might assist with aligning the sleeve around the nozzle (due to the extra axial length of the sleeve system) and thus preventing it from tilting and jamming. Another reason to implement a pull rod system would be to gain the benefits of bearing housing actuation while also the mitigation of turbine blade high cycle fatigue that can result from sliding the sleeve from the turbine side.
Referring first to Figs 32a and 32b, a nozzle assembly is indicated generally by reference 34 and may take any of the variety of forms described above and alternatives thereto. The significant difference between the embodiment of Figs 32a and 32b and for instance the embodiment of Fig 3 for example, is that a cylindrical sleeve 230 is mounted within a cavity 240 defined in a turbine housing 1 rather than in the bearing housing 3. Notwithstanding this different location of the sleeve 230, so that it slides across the inlet 9 from the turbine side to the bearing housing side, the manner of mounting and actuating the sleeve is very similar to that illustrated in Fig 3. That is, sleeve 230 is mounted on guide rods 241 which are linked to an actuator yoke 243, which may be in turn actuated by a variety of different forms of actuator including pneumatic, hydraulic and electric. In the illustrated example the guide rods 241 are slidably supported within bushes 244. The nozzle assembly 34 comprises a first nozzle ring 232 which defines a first side wall of the inlet 9, and a second nozzle ring 233 which closes the annular recess 240 to the inlet 9, and as such defines a second side wall of the inlet 9. An annular seal ring 107 is provided to seal the sleeve 230 with respect to the nozzle ring 233. It will be appreciated that other aspects of operation in this embodiment of the invention will be substantially the same as those of the embodiments in the invention described above in which the sleeve 30 is actuated from the bearing housing side. In particular, the inlet passages 39 will function in substantially the same way.
Although not in accordance with the present invention and described herein for the purposes of reference only, referring to Figures 33a and 33b, these show modification of the embodiment shown in Figs 32a and 32b in which the sleeve 330 is positioned on the inside diameter of the nozzle assembly 34 rather than on the outside diameter. In this variable geometry turbine, the nozzle assembly 34 is located between a side wall 332 of the housing 1, and a facing side wall 332 on the opposite side of annular inlet 9 and which closes annular cavity 240 within which guide rods 241 are slidingly supported. Here again, sleeves 330 may be actuated by any suitable actuator linked to the sleeves by a yoke 243. In this embodiment the cavity 240 is sealed with respect to the inlet 9 by a seal ring 334 supported on the inside diameter of an annular member 335.
As mentioned above, alternative embodiments of the invention may comprise two parallel sleeves, one on the inside diameter and one on the outside diameter, which may be arranged and controlled to move together or independently of one another, and may have different lengths.
Various modifications may be made to the structure of the sleeve. For instance, Figures 34a and 34c show three different possibilities for the profiling of the free end of the sleeve 30. Whereas the sleeve 30 of Fig. 34a has a squared-off end, the free end of the sleeve 30 could be curved or otherwise streamlines as shown in Figs. 34b and 34c. This may improve aerodynamic efficiency as gas flows past the sleeve through the open portion of the inlet 9.
Figs. 35a and 35b show two possible arrangements for a sleeve 30 including a piston ring seal 100 adjacent the free end of the sleeve 30 to prevent gas flow between the sleeve 30 and a nozzle array in the accordance with the invention, indicated generally by reference 101. It will be appreciated that the nozzle assembly 101 may have any of the possible configurations according to the present invention described above. It will also be appreciated that the free end of the sleeve 30 could be profiled as for instance shown in Figs. 34b and 34c (and if at the nozzle inner diameter, could be oppositely profiled i.e. on its outer diameter). This, and other shapes, such as a radial ridge (not shown) may be implemented to modify the aerodynamic efficiency of the turbine or to modify the axial or radial aerodynamic forces experienced by the sleeve.
Alternatively, in some embodiments of the invention (which may have any a nozzle assembly with any of the possible configurations described above, e.g. a plurality of baffles) there may be no piston ring seal adjacent the free end of the sleeve. In this manner, the sleeve may be mounted such that gas may pass between the sleeve and the nozzle assembly. For example, in a case where the nozzle assembly comprises a plurality of annular baffles and the sleeve is mounted beyond the outer diameter of the annular baffles, the sleeve may be mounted such that there is a gap between the sleeve and at least one of the annular baffles. In this case the sleeve may have an inner diameter which is greater than the outer diameter of at least one of the annular baffles. An example of a gas flow path 38g between a sleeve 30 and a nozzle assembly 34 can be seen in Figure 7c. The flow path 38g passes through a radial gap between the sleeve 30 and baffle 38b of the nozzle assembly 34. The flow path 38g is such that once the gas has passed through the gap between the sleeve 30 and baffle 38b, the gas flows through the inlet 9 towards the turbine wheel. In other embodiments, any other appropriate gap between the sleeve and the nozzle assembly (which defines a gas flow path between the nozzle assembly and the sleeve) may be used. Within Figure 7c the gap between the sleeve and the baffles 38a-38c has been exaggerated for clarity. In the case where the sleeve moves axially towards an inlet sidewall so as to reduce the size of the inlet through which gas may flow, the gap between the sleeve and the nozzle assembly may be such that it permits gas to flow between the nozzle assembly and the sleeve in a direction which is generally opposite to the direction in which the sleeve moves when it moves towards the inlet sidewall so as to reduce the size of the inlet. Furthermore, the gap between the sleeve and the nozzle assembly may be such that it permits gas to flow between the nozzle assembly and the sleeve in a direction which is generally radially inwards, towards the turbine wheel. In some embodiments, the nozzle assembly and sleeve may be configured such that there is a gap between all of the baffles and the sleeve (e.g. the baffles all have an outer diameter which is less than the inner diameter of the sleeve). However, in other embodiments, the nozzle assembly and sleeve may be configured such that there is a gap between only some of the baffles and the sleeve. For example, those baffles for which there is not a gap between the nozzle and the sleeve may be such that they generally contact the sleeve. In this case, such baffles which abut the sleeve may guide the movement of the sleeve as it varies the size of the inlet. It has been found that in some embodiments, provision of a gap (and hence a gas flow path) between the sleeve and the nozzle assembly may improve the performance of the turbine.
It is also possible to profile or chamfer the opposite side of the sleeve (i.e. the edge that contacts the nozzle) to facilitate smooth running and mitigate the possibility of the sleeve jamming for example against a baffle.
Furthermore, it will be appreciated that these possibilities, including those shown in Figs. 34a - 34c, 30a and 30b are applicable to the sleeve regardless of whether it is mounted on the bearing housing or turbine housing side of the nozzle, and regardless of whether it is mounted on the inner diameter of the nozzle (although it will be appreciated that this is not in accordance with the present invention) or outer diameter of the nozzle or both.
Referring to Figure 36, the turbocharger comprises a turbine 1w joined to a compressor 2w via a central bearing housing 3w. The turbine 1w comprises a turbine wheel 4w for rotation within a turbine housing 5w. Similarly, the compressor 2w comprises a compressor wheel 6w which can rotate within a compressor housing 7w. The turbine wheel 4w and compressor wheel 6 are mounted on opposite ends of a common turbocharger shaft 8w which extends through the central bearing housing 3w.
The turbine housing 5w has an exhaust gas inlet volute 9w located annularly around the turbine wheel 4w and an axial exhaust gas outlet 10w. The compressor housing 7w has an axial air intake passage 11w and a compressed air outlet volute 12w arranged annularly around the compressor wheel 6w. The turbocharger shaft 8w rotates on journal bearings 13w and 14w housed towards the turbine end and compressor end respectively of the bearing housing 3w. The compressor end bearing 14w further includes a thrust bearing 15w which interacts with an oil seal assembly including an oil slinger 16w. Oil is supplied to the bearing housing from the oil system of the internal combustion engine via oil inlet 17w and is fed to the bearing assemblies by oil passageways 18w.
In use, the turbine wheel 4w is rotated by the passage of exhaust gas from the annular exhaust gas inlet 9w to the exhaust gas outlet 10w, which in turn rotates the compressor wheel 6w which thereby draws intake air through the compressor inlet 11w and delivers boost air to the intake of an internal combustion engine (not shown) via the compressor outlet volute 12w.
In Figure 37 there is shown a turbine volute 20w and an annular inlet 21w of a turbine 22w according to an embodiment of the present invention. Equiaxially spaced across the inlet 21w are two annular baffles 23aw, 23bw which, together with inner and outer sidewalls 24w, 25w of the inlet, define three axially offset annular inlet portions 26aw 26bw, 26cw of equal axial width. Extending axially across each of the three inlet portions 26aw, 26bw, 26cw are respective annular arrays of vanes 27aw, 27bw, 27cw. The vanes 27aw, 27bw, 27cw are optional, and in other embodiments may not be present in all inlet portions 26aw, 26bw, 26cw. The vanes 27aw, 27bw, 27cw divide each respective inlet portion 26aw, 26bw, 26cw to form inlet passages in each inlet portion 26aw, 26bw, 26cw. A cylindrical sleeve 28w is provided that is axially movable across the annular inlet 21w to vary the size of a gas flow path through the inlet 21w (i.e. to vary the geometry of the turbine). Movement of the cylindrical sleeve 28w may be undertaken, for example, to close or at least partially close, or open, or at least partially open, one or more of the inlet portions 26aw, 26bw, 26cw.
The turbine 22w is also shown as comprising a turbine wheel 29w mounted on a turbine shaft 30w for rotation about a turbine axis.
The sleeve 28w of Figure 37 may be formed, for example, from casting. However, a more accurate, cheaper or simpler way of making the sleeve 28w is shown in Figures 38 and 39.
Figure 38 shows a sheet of material 40w. The sheet 40w may be formed from any material suitable for withstanding the conditions within a turbine. For example, the sheet 40w may be formed from a metal, or an alloy.
Figure 39 shows that the sheet has been rolled into a sleeve like shape 28w. Opposing faces of the rolled sheet are welded, brazed or otherwise attached to each other 42w to form the sleeve 28w.
In a different but related embodiment, the opposing faces of the rolled sheet are not attached to each other. Such an embodiment is shown in Figure 40. In Figure 40, and end-on view of a sleeve 50w in accordance with another embodiment of the present invention is shown. The sleeve 50w is, again, formed by rolling a sheet of material, which may be formed from any material suitable for withstanding the conditions within a turbine. For example, the sheet may be formed from a metal, or an alloy. In contrast with the sleeve of Figure 39, in Figure 40 the opposing faces of the sheet (or ends that carry those faces) are not attached to one another, but instead overlap 52w one another. Such overlap 52w may allow, accommodate or facilitate expansion or contraction of the sleeve during operation of the turbine, for example due to temperature changes that the sleeve is subjected to. Such allowance, accommodation or facilitation may reduce or prevent jamming of the sleeve on vanes or baffles discussed above. For instance, without such allowance, accommodation or facilitation for expansion, the sleeve may abut against baffles or vanes that have expanded, in use, due to heating, which could cause jamming.
The degree of overlap, and/or the material of the sleeve, may be selected such that expansion and/or contraction is undertaken at a rate (e.g. a radial rate) which matches a rate (e.g. a radial rate) of expansion of the baffles or vanes which the sleeve surrounds (or, in other embodiments - not shown - that surround the sleeve).
An axially extending step may be provided in the sleeve, and/or the baffle, vanes or other structure defining the inlet portions. The step is a step up or down in the circumferential direction, and may have a helical component. The step may accommodate the overlap discussed above, and/or may ensure that the overlap does not leave a gap through which gas might otherwise flow, reducing efficiency of the turbine as a while. Figures 41 a to 41f depict end-on views of different sleeves 60w, 70w, 80w, 90w, 100w, 110w and inlet structures 65w, 75w, 85w, 95w, 105w, 115w, one of both of which is or are provided with such a step. More than one step may be provided in a given sleeve, for example an inner and outer diameter step. The sleeve may overlap to such an extent that the sleeve forms a roll. The sleeve may be formed from two or more portions or section, e.g. half or quarter sleeve sections, that are joined together.
In Figure 37, a single sleeve section is provided. A single sleeve section may be sufficient. However, greater functionality may be desirable, or in some instances, required. For example, it may be desirable to ensure that gas flows through only a single inlet portion, or through a plurality, but not all, of adjacent inlet portions. This may be desirable to ensure that gas flows through an inlet portion with a certain vane configuration, or through inlet portions with certain vane configurations.
A variable geometry turbine may comprise a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The annular inlet is divided into at least two axially offset inlet portions. The preceding features are shown in Figure 37. In contrast to the arrangement of Figure 37, and in accordance with the present invention, the turbine further comprises a first cylindrical sleeve section axially movable across the annular inlet to vary the size of a gas flow path through the inlet, and a second cylindrical sleeve section axially movable across the annular inlet to vary the size of a gas flow path through the inlet. By providing two sleeve sections, greater control of the gas flow may be achieved.
Figure 42 shows a view of a sub-section of the turbine shown in and described with reference to Figure 37. In addition to the features shown in Figure 37, Figure 42 shows that a second cylindrical sleeve section 40x is provided. The (first) cylindrical sleeve section 28w and the second sleeve section 40x are independently moveable with respect to one another. This allows, for example, improved control of the gas flow through the inlet, so that for example gas may flow through only a single inlet portion 27bw (e.g. with a certain or desired vane configuration, which may include an absence of vanes). Because two independently moveable sleeves sections 28w, 40x are provided, the inlet portion 27bw or portions that is or are exposed does/do not need to be adjacent to a sidewall 24w, 25w, but can be an inlet portion or portions located away from (e.g. separated by one or more other inlet portions 27aw, 27bw) from the sidewalls 24w, 25w.
In Figure 42, the first cylindrical sleeve section 28w and the second cylindrical sleeve section 40x both have an inner diameter that is greater than an outer diameter of the inlet portions (i.e. the sleeve sections 28w, 40x surround the inlet portions 27aw, 27bw, 27cw). This arrangement may improve turbine operation, for example reducing turbulence or improving properties of gas flow through or past the inlet.
Although not in accordance with the present invention and described herein for the purposes of reference only, in another variable geometry turbine, the first cylindrical sleeve section and the second cylindrical sleeve section may both have an outer diameter that is less than an inner diameter of the inlet portions (i.e. the sleeve sections are surrounded by the inlet portions).
Figure 43 shows a further embodiment, where the first cylindrical sleeve section 28w has an inner diameter that is greater than an outer diameter of the inlet portions 27aw, 27bw, 27cw (i.e. the first sleeve section 28w surrounds the inlet portions 27aw, 27bw, 27cw). In contrast, a second cylindrical sleeve section 50x has an outer diameter that is less than an inner diameter of the inlet portions 27aw, 27bw, 27cw (i.e. the second sleeve section 50x is surrounded by the inlet portions 27aw, 27bw, 27cw). This arrangement may be advantageous, since now both sleeve sections 28w, 50x can, if required, extend across the inlet, and at the same time.
Figure 44 shows a similar arrangement to that shown in Figure 42. However, in Figure 44 (and in contrast to Figure 42) the sleeve sections 28w, 40x are connected to one another via a bridge connection 60x. The sleeve sections 28w, 40x are thus no longer independently moveable, due their attachment to one another. However, suitable exposure of one or more inlet portions 27aw, 27bw, 27cw (depending on the degree of separation of the sleeve section 28w, 40x and the axial width of the inlet portions 27aw, 27bw, 27cw) may still be achieved via appropriate movement of the sleeve sections 28w, 40x in unison.
The sleeve sections 28w, 40x may be formed from a single sleeve, with an opening (e.g. an annular opening) in the sleeve being provided to form the two sleeve sections. A remaining portion of the sleeve may form the aforementioned bridge connection.
In the embodiments discussed, the sleeves have been shown as being moved from within, or relative to, opposing sidewalls of the inlet. In all embodiments discussed, a variation might include the sleeve sections being moved from, or relative to, the same sidewall. However, such an arrangement might restrict the ability to expose inlet portions located away from the sidewalls of the inlet.
The sleeve sections may be moved by appropriate actuation and interaction with a trailing end of the sleeve sections (e.g. an end not located or locatable within the inlet). Alternatively or additionally, the sleeve sections may be moved by appropriate actuation and interaction with one or more guides (e.g. moveable rods or wires or cables) that extend across the inlet.
Different inlet portions may have different vane configurations (which may include an inlet portion with no vanes). These configurations may be selected, via appropriate inlet portion selection, by movement of the two sleeve sections.
The variable geometry turbine may further comprise a third cylindrical sleeve section, moveable to open or close a passage between the inlet, or a volume upstream of the inlet, and a turbine outlet.
A potentially viable alternative to the arrangement shown in Figure 37 is shown in Figure 45. In Figure 45 there is shown a turbine volute 120w and an annular inlet 121w of a turbine 122w according to an embodiment of the present invention. The inlet is at least partially define by sidewalls 124w, 125w. Equiaxially spaced across the inlet 121w are two annular baffles 123aw, 123bw which, together with end-walls 123cw, 123dw, define three axially offset annular inlet portions 126aw, 126bw, 126cw of equal axial width. Extending axially across each of the three inlet portions 126aw,' 126bw, 126cw are respective annular arrays of vanes 127aw, 127bw, 127cw. The vanes 127aw, 127bw, 127cw are optional, and in other embodiments may not be present in all inlet portions 126aw, 126bw, 126cw. The vanes 127aw, 127bw, 127cw divide each respective inlet portion 126aw, 126bw, 126cw to form inlet passages in each inlet portion 126aw, 126bw, 126cw.
In contrast to the arrangement shown in Figure 37, the baffles 123aw, 123bw and vanes 127aw, 127bw, 127cw in Figure 45 are part of a substantially annular baffle structure 200w that is axially moveable across the inlet 121w to vary a configuration of a gas flow path through the inlet 121w (i.e. to vary the geometry of the turbine). Figure 45 shows that the baffle structure 200w comprises at least two axial offset inlet portions126aw, 126bw, 126cw, at least (and perhaps only) two of which may be located fully (i.e. not partially) within the annular inlet 121w. If at least two inlet portions 126aw, 126bw, 126cw were only partially locatable in the inlet 121w, performance may be reduced due to, for example, an increase in turbulence or decrease in gas flow.
The baffle structure 200w may be provided in or on (e.g. at the end of) an axially moveable sleeve. The sleeve may comprise a solid portion 201w (i.e. not an inlet portion) which may be at least partially locatable within the inlet 121w, for example to at least partially block or close the inlet.
As shown in the Figure, at least one inlet portion 126aw, 126bw, 126cw may comprise vanes 127aw, 127bw, 127cw, dividing an inlet portion 126aw, 126bw, 126cw into inlet passageways. Again as shown in the Figure, at least two inlet portions 126aw, 126bw, 126cw may comprise vanes, dividing the respective inlet portions 126aw, 126bw, 126cw into inlet passageways. A configuration of vanes in a first inlet portion may be different from a configuration of vanes in a second inlet portion (not shown in the Figure). A configuration of vanes in a second inlet portion may be the same as a configuration of vanes in a second inlet portion, as for example schematically depicted in the Figure.
As shown in the Figure the baffle 200w structure may comprise at least three axial offset inlet portions 126aw, 126bw, 126cw, all three of which portions 126aw, 126bw, 126cw may be located fully within the annular inlet.
In other embodiments, it may be preferable to be able to locate (only) a whole number of inlet portions within the inlet (i.e. not a partial inlet, or partial inlets). If one or more inlet portions were only partially locatable in the inlet, performance may be reduced due to, for example, an increase in turbulence or decrease in gas flow.
Referring back to the Figure, for completeness the turbine 122w is also shown as comprising a turbine wheel 129w mounted on a turbine shaft 130w for rotation about a turbine axis.
In figure 46 there is shown a turbine volute 20w and annular inlet 21 w of a turbine 22w according to an embodiment of the present invention. Located within the inlet 21w is an annular baffle 23w which, together with inner and outer sidewalls 24w, 25w of the inlet, define two axially offset annular inlet portions 26aw, 26bw of equal axial width. Extending axially across each of the two inlet portions 26aw-bw are respective annular arrays of vanes 27aw, 27bw of equivalent maximum axial thickness. As can be seen in figure 46, the axial thickness 'TB' of the baffle 23w is significantly lower than the maximum axial thickness 'Tv' of each of the vanes 27aw-bw. Moreover, the axial thickness TB of the baffle 23w is also much lower than the diameter 'D' of the turbine wheel 29w. In the specific embodiment shown, TB is around 2.25 % of D.
Figure 47 shows an alternative embodiment of the present invention in which a turbine 32y incorporates a turbine volute 30w and an annular inlet 31 y. Equiaxially spaced across the inlet 31y are three annular baffles 33ay, 33by, 33cy which, together with inner and outer sidewalls 34y, 35y of the inlet, define four axially offset annular inlet portions 36ay, 36by, 36cy, 36dy of equal axial width. Extending axially across each of the four inlet portions 36ay-dy are respective annular arrays of vanes 37ay, 37by, 37cy, 37dy of equivalent maximum axial thickness. The axial thickness 'TB' of each of the baffles 33ay-cy is significantly lower than the maximum axial thickness 'Tv' of each of the vanes 37ay-dy and is also much lower than the diameter 'D' of the turbine wheel 39y. In this embodiment shown, TB is around 2.25 % of D.
It will be appreciated that in alternative embodiments the number and/or profile of vanes in an array may vary from one array to another, and/or the swirl angle defined by vanes in an array may vary from that defined by vanes in other arrays in the same nozzle structure.
Typically, exhaust gas flows to the annular inlet from a surrounding volute or chamber. The annular inlet is therefore defined downstream of the volute, with the downstream end of the volute terminating at the upstream end of the annular inlet. As such, the volute transmits the gas to the annular inlet, while the gas inlet passages of the present invention receive gas from the volute. In some embodiments, the first and second inlet sidewalls which define the annular inlet are continuations of walls which define the volute. The annular inlet may be divided into at least two axially offset inlet passages by one or more baffles located in the annular inlet, and which are therefore positioned downstream of the volute.
The turbine of the present invention has been illustrated in the figures using a single flow volute, however it is applicable to housings that are split axially, whereby gas from one or more of the cylinders of an engine is directed to one of the divided volutes, and gas from one or more of the other cylinders is directed to a different volute. It is also possible to split a turbine housing circumferentially to provide multiple circumferentially divided volutes, or even to split the turbine housing both circumferentially and axially. It should be appreciated, however, that an axially or circumferentially divided volute is distinguished from the multiple gas inlet passages present in the turbine of the present invention. For example, the gas inlet passages relate to a nozzle structure arranged to accelerate exhaust gas received from the volute towards the turbine, and optionally to adjust or control the swirl angle of the gas as it accelerates. The multiple gas inlet passages forming part of the present invention may be further distinguished from a divided volute arrangement in that, while the gas inlet passages receive gas from the volute (or divided volute), and split the gas into an array of paths directed on to the turbine, a divided volute receives gas from the exhaust manifold so as to retain the gas velocity in gas pulses resulting from individual engine cylinder opening events.
It will be appreciated that axially offset inlet passages include inlet passages with different axial positions and/or inlet passages with different axial extents. Axially offset inlet passages may be spaced apart, adjacent or axially overlapping.
Figure 48 shows a possible modification of the embodiment illustrated in Figs. 8a - 8c, and the same reference numerals are used where appropriate. As with the embodiment illustrated in Figs. 8a - 8c, it can be seen that vanes 37wv-37zv are not continuous across the full width of the inlet, but rather vanes defining each of the annular arrays of inlet passages 39wv - 39zv have various configurations. The various configurations of vanes defining each of the annular arrays of inlet passages may be advantageous because in some embodiments it may be desirable for gas passing through the different annular arrays to have different flow characteristics and/or efficiencies depending on the axial location of the annular array.
The leading edges of vanes 37xv-37zv lie on the same outer radius, whereas the leading edge of vane 37wv lies on a different outer radius. The trailing edges of the vanes 37wv, 37xv and 37zv lie on the same inner radius, whereas the trailing edge of vane 37yv lies on a different inner radius. The radial extent of vanes 37wv and 37yv is the same, but different to that of the vanes 37xv and 37zv. In addition, it can be seen that the inlet baffles 38xv - 38zv have a greater radial extent than at least some of the vanes 37v (in the illustrated embodiment it is greater than that of any of the vanes). That is, whilst they have substantially the same outer radius as the vanes 37v, the inner radius of the baffles 38av - 38cv is significantly less than that of the vanes 37v, so that the baffles 38xv - 38zv extend further towards the turbine wheel 5v than the vanes 37v (i.e. the baffles extend radially inboard of the vanes). In particular, each baffle extends radially inboard of the vanes in the inlet portions axially either side of it. For example, the baffle 38xv extends radially inboard of the vanes 37wv and 37xv. In some embodiments the baffle may extend radially inboard of vanes in only one adjacent inlet portion. The vanes in the other adjacent inlet portion may have a trailing edge which has the same radius (or diameter) as the inner radius (or diameter) of the baffle. It may be advantageous in some embodiments for the baffle to extend radially inboard of vanes in at least one of the adjacent inlet portions, because this limits flow communication and turbulence between axially adjacent inlet portions upstream of the turbine wheel.
In this particular embodiment each of the baffles 38xv - 38zv has the same outer radial dimension (or outer diameter). In other embodiments at least one of the baffles may have a different outer radial dimension. In this particular embodiment each of the baffles 38xv - 38zv has a different inner radial dimension (or inner diameter). In other embodiments only some of the baffles may have a different inner radial dimension. The inner radial dimensions (or inner diameters) of the baffles 38xv-38zv form a trend whereby the relative inner diameters of the baffles 38xv-38zv increase in an axial direction from inlet sidewall 32v to inlet sidewall 33v. It will be appreciated that in other embodiments, the inner radial dimensions (or inner diameters) of the baffles may form a trend whereby the relative inner diameters of the baffles decrease in an axial direction from inlet sidewall 32v to inlet sidewall 33v. In some embodiments the trend whereby the relative inner radial dimensions (or inner diameters) of the baffles increase / decrease in an axial direction between the inlet sidewalls may only be a general trend. For example, the relative inner radial dimensions (or inner diameters) of the baffles may generally increase in an axial direction between the inlet sidewalls, but at least one of the baffles may have a relative inner radial dimension which falls outside of the trend. A trend whereby the relative inner radial dimensions (or inner diameters) of the baffles increase / decrease in an axial direction between the inlet sidewalls may be advantageous in some embodiments as it may enable the flow characteristics of the gas passing through each inlet potion and being incident on the turbine wheel to vary across the inlet.
In this embodiment, the axial profile formed by the inner radial dimensions (or inner diameters) of the baffles 38xv-38zv generally corresponds to the axial profile of the surface 5pv swept by the rotation of the turbine wheel. In this embodiment, the radial separation between each of the baffles 38xv-38zv and the respective radially adjacent portion of the surface 5pv swept by the rotation of the turbine wheel is generally constant. It will be appreciated that in other embodiments the axial profile of the surface swept by the rotation of the turbine wheel may be different. It will also be appreciated that in some embodiments, only some of the baffles may have inner radial dimensions that form an axial profile which generally corresponds to the axial profile of the surface swept by the rotation of the turbine wheel. Embodiments where the axial profile formed by the inner radial dimensions (or inner diameters) of the baffles generally correspond to the axial profile of the surface swept by the rotation of the turbine wheel may be advantageous in that it enables the characteristics of gas flow through the inlet portions to the turbine wheel which are defined by the separation between the baffle and the turbine wheel to be kept constant across different inlet portions.
In this embodiment it can be seen that each of the baffles 38xv-38zv has an inner radial dimension (inner diameter) such that the radial distance relative to the turbine axis between the inner diameter of each baffle and the trailing edge of a vane of an inlet portion adjacent the baffle (which in the case where the vanes have different radial positions, may be a radially innermost vane) is more than generally 50% of the radial distance between the trailing edge of said vane and the outer diameter of the turbine wheel at the axial position of the baffle. For example, referring to baffle 38yv and adjacent vane 37yv, the baffle 38yv has an inner radial dimension (inner diameter) such that the radial distance db relative to the turbine axis between the inner diameter of the baffle and the trailing edge of the adjacent vane 37yv is more than generally 50% of the radial distance dt between the trailing edge of said vane and the outer diameter of the turbine wheel at the axial position of the baffle. In some embodiments the radial distance relative to the turbine axis between the inner diameter of a baffle and the trailing edge of a vane of an inlet portion adjacent the baffle may be generally 60%, generally 70%, generally 80%, generally 90% or generally 95% of the radial distance between the trailing edge of said vane and the outer diameter of the turbine wheel at the axial position of the baffle. That is to say that the radial distance relative to the turbine axis between the inner diameter of a baffle and the trailing edge of a vane of an inlet portion adjacent the baffle may be generally between 50% and 100%, between 50% and 60%, between 60% and 70%, between 80% and 90%, between 90% and 95% or between 95% and 100% of the radial distance between the trailing edge of said vane and the outer diameter of the turbine wheel at the axial position of the baffle. By ensuring that the radial distance relative to the turbine axis between the inner diameter of a baffle and the trailing edge of a vane of an inlet portion adjacent the baffle is a large proportion of the radial distance between the trailing edge of said vane and the outer diameter of the turbine wheel at the axial position of the baffle, this may help to prevent unwanted expansion of gas passing through the inlet portions before thy pass the turbine wheel. This feature may also help to prevent flow communication and turbulence between adjacent inlet portions upstream of the turbine wheel. Furthermore it may be advantageous in helping to prevent gas flowing from the inlet portions around the turbine wheel, without exerting significant force on the turbine wheel. A practical limit as to how close the baffles can extend towards the outer surface of the turbine wheel may be provided by when the skin effect (due to skin friction caused by the proximity of the turbine wheel to the baffles) negatively affects performance of the turbine wheel.
In figure 49 there is shown a turbine volute 20u and annular inlet 21u of a turbine 22u according to an embodiment of the present invention. Equiaxially spaced across the inlet 21u are two annular baffles 23au, 23bu which, together with inner and outer sidewalls 24u, 25u of the inlet, define three axially offset annular inlet portions 26au, 26bu, 26cu of equal axial width. Extending axially across each of the three inlet portions 26au-cu are respective annular arrays of vanes 27au, 27bu, 27cu having differing arrangements so as to constrict the area accessible to gas flowing through the annular arrays 27au-cu to differing extents.
Figure 54 is an illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 49. A perspective view of the nozzle structure is shown which comprises of an inlet sidewall 30u, first and second axially spaced baffles 31 au, 31bu, three annular arrays of axially extending vanes 32au, 32bu, 32cu and an axially slidable sleeve 33u. Each array of vanes 32au-cu is comprised of a plurality of vanes 34au, 34bu, 34cu. Of the three arrays 32au-cu, the array 32cu furthest from the "closed position" of the sleeve 33u, i.e. when the sleeve 33u covers the entire turbine inlet and overlies the sidewall 30u, includes the smallest number of vanes 34cu. The middle array 32bu contains more vanes 32bu, while the array 32au closest to the "closed position" of the sleeve 33u, i.e. the array 32au which lies in the annular inlet portion which is bordered on one side by the inlet sidewall 30u, contains the largest number of vanes 34au. In this way, the array 32au closest to the "closed position" of the sleeve 33u presents the greatest constriction to gas flowing through the annular inlet, while the array 32cu lying furthest away from the "closed position" of the sleeve 33u presents the least constriction to gas flow through the annular inlet.
In figure 50 there is shown a turbine volute 120u and annular inlet 121u of a turbine 122u according to an embodiment of the present invention. Equiaxially spaced across the inlet 121u are two annular baffles 123au, 123bu which, together with inner and outer sidewalls 124u, 125u of the inlet, define three axially offset annular inlet portions 126au, 126bu, 126cu of equal axial width. Extending axially across each of the three inlet portions 126au-cu are respective annular arrays of vanes 127au, 127bu, 127cu of differing maximum circumferential thickness, i.e. width in radial cross-section, for instance as viewed in figure 55B or 55C.
Figure 55 is an illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 50. A perspective view of the nozzle structure is shown in Figure 55(A) and comprises of an inlet sidewall 130u, first and second axially spaced baffles 131au, 131bu, three annular arrays of axially extending vanes 132au, 132bu, 132cu and an axially slidable sleeve 133u. Figure 55(B) shows radial cross-sectional views of the three annular arrays of vanes 132au-cu comprised in the nozzle structure shown in Figure 55(A). Figure 55(C) shows a detailed radial cross-sectional view of a respective vane 134au, 134bu, 134cu in each of the three arrays of vanes 132au-cu. The circumferential thickness of each vane 134au-cu in each array 132au-cu is indicated by a double headed arrow within each vane 134au-cu in figure 55(C).
As can be observed from figures 55(B) and 55(C) the vanes 134cu in the array 132cu furthest from the "closed position" of the sleeve 133u, i.e. when the sleeve 133u covers the entire turbine inlet and overlies the sidewall 130u, are circumferentially thinner and thereby define a smaller radial cross-sectional area than the vanes 134bu in the middle array 132bu, which are in turn, circumferentially thinner than the vanes 134au in the array 132au closest to the "closed position" of the sleeve 133u, i.e. the vanes 134au which lie in the annular inlet portion which is bordered on one side by the inlet sidewall 130u. In the embodiment illustrated in figure 55 the three arrays of vanes 132au-cu each contain the same total number of vanes 134au-cu and each define a similar swirl angle. It will be appreciated however that in alternative embodiments the number of vanes in an array may vary from one array to another, and/or the swirl angle defined by vanes in an array may vary from that defined by vanes in other arrays in the same nozzle structure.
In figure 51 there is shown a turbine volute 220u and annular inlet 221 u of a turbine 222u according to an embodiment of the present invention. Equiaxially spaced across the inlet 221u are two annular baffles 223au, 223bu which, together with inner and outer sidewalls 224u, 225u of the inlet, define three axially offset annular inlet portions 226au, 226bu, 226cu of equal axial width. Extending axially across each of the three inlet portions 226au-cu are respective annular arrays of vanes 227au, 227bu, 227cu of differing maximum circumferential thickness, i.e. width in radial cross-section, for instance as viewed in figure 56B or 56C.
Figure 56 is an illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 51. A perspective view of the nozzle structure is shown in Figure 56(A) and comprises of an inlet sidewall 230u, first and second axially spaced baffles 231 au, 231bu, three annular arrays of axially extending vanes 232au, 232bu, 232cu and an axially slidable sleeve 233u. Figure 56(B) shows radial cross-sectional views of the three annular arrays of vanes 232au-cu comprised in the nozzle structure shown in Figure 56(A). Figure 56(C) shows a detailed radial cross-sectional view of a respective vane 234au, 234bu, 234cu in each of the three arrays of vanes 232au-cu. The thickness of each respective leading edge 235au, 235bu, 235cu of each vane 234au-cu in each array 232au-cu is directly related to a respective angle 236au, 236cu, 236cu defined as shown in figure 56(C). The maximum circumferential thickness of each vane 234au-cu in each array 232au-cu is indicated by a double headed arrow within each vane 234au-cu in figure 56(C).
As can be observed from figures 56(B) and 56(C) the vanes 234cu in the array 232cu furthest from the "closed position" of the sleeve 233u, i.e. when the sleeve 233u covers the entire turbine inlet and overlies the sidewall 230u, have thinner leading edges 235cu, which in turn have thinner leading edges 235bu than the vanes 234au in the array 232au closest to the "closed position" of the sleeve 233u, i.e. the vanes 234au which lie in the annular inlet portion which is bordered on one side by the inlet sidewall 230u. In spite of the difference in leading edge thickness, the vanes 234au-cu in the three arrays of vanes 232au-cu all possess substantially the same circumferential thickness (indicated by a double headed arrow within each vane in figure 56(C). In an alternative embodiment, the vanes 234au-cu in the three arrays 232au-cu may have different maximum circumferential thicknesses, for instance, the array of vanes 232au with the thickest leading edges 235au may also possess the largest maximum circumferential thickness as compared to the other two arrays 232bu-cu. In the embodiment illustrated in figure 56 the three arrays of vanes 232au-cu each contain the same total number of vanes 234au-cu and each define a similar swirl angle. It will be appreciated however that in alternative embodiments the number of vanes in an array may vary from one array to another, and/or the swirl angle defined by vanes in an array may vary from that defined by vanes in other arrays in the same nozzle structure.
In figure 52 there is shown a turbine volute 320u and annular inlet 321u of a turbine 322u according to an embodiment of the present invention. Equiaxially spaced across the inlet 321u are two annular baffles 323au, 323bu which, together with inner and outer sidewalls 324u, 325u of the inlet, define three axially offset annular inlet portions 326au, 326bu, 326uc of equal axial width. Extending axially across each of the three inlet portions 326au-cu are respective annular arrays of vanes 327au, 327bu, 327cu of differing maximum outer diameter, i.e. width in radial cross-section. As can be seen in figure 52, the vane 327au has a smaller radial extent and thus defines a smaller maximum outer diameter than the two other vanes 327bu-cu. This is further described below in relation to figure 57.
Figure 57 is an illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 52. A perspective view of the nozzle structure is shown in Figure 57(A) and comprises of an inlet sidewall 330u, first and second axially spaced baffles 331au, 331bu, three annular arrays of axially extending vanes 332au, 332bu, 332cu and an axially slidable sleeve 333u. Figure 57(B) shows radial cross-sectional views of the three annular arrays of vanes 332au-cu comprised in the nozzle structure shown in figure 57(A). Each array of vanes 332au-cu is comprised of a plurality of equiangularly spaced vanes 334au, 334bu; 334cu of similar radial cross-sectional profile in that the leading edge of each vane 334au-cu is the same thickness, the maximum circumferential thickness of each vane 334au-cu is the same, and the radial cross-sectional area of each vane 334au-cu is the same.
As can be observed from figure 57(B) the vanes 334bu-cu in the arrays 332bu-cu furthest from the "closed position" of the sleeve 333u, i.e. when the sleeve 333u covers the entire turbine inlet and overlies the sidewall 330u, extend radially outwards to a greater extent and thereby define a greater maximum outer diameter than the vanes 334au in the array 332au closest to the "closed position" of the sleeve 333u, i.e. the vanes 334au which lie in the annular inlet portion which is bordered on one side by the inlet sidewall 330u. In the embodiment shown in figure 57 the vanes 334au-cu in the three arrays 332au-cu all possess trailing edges lying on the same inner radius, i.e. defining the same maximum inner diameter. This does not have to be the case, however. One or more arrays 332au-cu may define a greater maximum inner diameter than one or more other arrays 332au-cu. Moreover, in a further alternative embodiment the arrays of vanes 332au-cu may each define a different maximum outer diameter.
In the embodiment illustrated in figure 57 the three arrays of vanes 332au-cu each contain the same total number of vanes 334au-cu and each define a similar swirl angle. It will be appreciated however that in alternative embodiments the number of vanes in an array may vary from one array to another, and/or the swirl angle defined by vanes in an array may vary from that defined by vanes in other arrays in the same nozzle structure.
In figure 53 there is shown a turbine volute 420u and annular inlet 421u of a turbine 422u according to an embodiment of the present invention. Equiaxially spaced across the inlet 421u are two annular baffles 423au, 423bu which, together with inner and outer sidewalls 424u, 425u of the inlet, define three axially offset annular inlet portions 426au, 426bu, 426cu of equal axial width. Extending axially across each of the three inlet portions 426au-cu are respective annular arrays of vanes 427au, 427bu, 427cu of differing maximum inner diameter, i.e. width in radial cross-section. As can be seen in figure 53, the array of vanes 427au has a smaller radial extent and defines a greater maximum inner diameter and a greater radial clearance between the vanes 427au and the turbine wheel 428u than the middle vanes 427bu. In a similar way, the middle array of vanes 427bu has a smaller radial extent and defines a greater maximum inner diameter and a greater radial clearance between the vanes 427bu and the turbine wheel 428u than the vanes 427cu. This is further described below in relation to figure 58.
Figure 58 is an illustration of components of a section of a nozzle structure forming part of a turbine according to the embodiment of figure 53. A perspective view of the nozzle structure is shown in Figure 58(A) and comprises of an inlet sidewall 430u, first and second axially spaced baffles 431 au, 431bu, three annular arrays of axially extending vanes 432au, 432bu, 432cu and an axially slidable sleeve 433u. Figure 58(B) shows radial cross-sectional views of the three annular arrays of vanes 432au-cu comprised in the nozzle structure shown in Figure 58(A). Each array of vanes 432au-cu is comprised of a plurality of equiangularly spaced vanes 434au, 434bu, 434cu of similar radial cross-sectional profile in that the leading edge of each vane 434au-cu is the same thickness, the maximum circumferential thickness of each vane 434au-cu is the same, and the radial cross-sectional area of each vane 434au-cu is the same.
As can be observed from figure 58(B) the vanes 434cu in the array 432cu furthest from the "closed position" of the sleeve 433u, i.e. when the sleeve 433u covers the entire turbine inlet and overlies the sidewall 430u, extend radially inwards to a greater extent and thereby define a smaller maximum inner diameter than the vanes 434bu in the middle array 432bu, which, in turn, define a smaller maximum inner diameter than the vanes 434au in the array 432au closest to the "closed position" of the sleeve 433u, i.e. the vanes 434au which lie in the annular inlet portion which is bordered on one side by the inlet sidewall 430u. Moreover, the radial clearance defined between the trailing edges of the vanes 434au-cu and the turbine wheel (not shown in figure 58) increases progressively from the array 434cu furthest from the closed, position of the sleeve to the array 434au closest to the closed position of the sleeve. By virtue of the different orientation of the vanes 432au-cu within each array 434au-cu the swirl angle generated by the arrays of vanes 434au-uc also increases progressively from the array 434cu furthest from the closed position to the array 434au closest to the closed position.
In the embodiment shown in figure 58 the vanes 434au-cu in the three arrays 432au-cu all possess leading edges lying on the same outer radius, i.e. defining the same maximum outer diameter. This does not have to be the case, however. One or more arrays 432au-cu may define a greater maximum outer diameter than one or more other arrays 432au-cu. Moreover, in a further alternative embodiment two of the arrays of vanes 432au-cu may define a first maximum inner diameter which is different to that of the other of the arrays 432au-cu.
In the embodiment illustrated in figure 58 the three arrays of vanes 432au-cu each contain the same total number of vanes 434au-cu. It will be appreciated however that in alternative embodiments the number of vanes in an array may vary from one array to another in the same nozzle structure.
In figure 59 there is shown a turbine volute 20w and annular inlet 21w of a turbine 22w according to an embodiment of the present invention. Equiaxially spaced across the inlet 21w are two annular baffles 23aw, 23bw which, together with inner and outer sidewalls 24w, 25w of the inlet, define three axially offset annular inlet portions 26aw, 26bw, 26cw of equal axial width. Extending axially across each of the three inlet portions 26aw-cw are respective annular arrays of vanes 27aw, 27bw, 27cw. The baffles 23aw-bw and vanes 27aw-cw together represent a nozzle assembly located within the annular inlet 21w which directs exhaust gases flowing from the turbine volute 20 on to the blades of turbine 22w in the most appropriate manner to suit the operating requirements of the turbine 22w. While not visible in figure 59, each vane in the outer arrays vanes 27aw, 27cw incorporates a finger which extends axially inwards from the inner edge of the vane towards the adjacent inner baffle 23aw, 23bw respectively, while each vane in the middle array of vanes 27bw incorporates a pair of fingers one extending axially outwards from each of the opposite edges of the vane which are received in complementary depressions defined by each of the baffles 23aw-bw. In an alternative embodiment, the baffle 23aw supports the vanes 27aw and the baffle 23bw supports the vanes 27bw. The vanes 27cw are supported by the inlet sidewall 25w. The two baffles 23aw-bw and their respective arrays of vanes 27aw-bw are substantially identical in size and shape and as such represent modular components that have been assembled, together with the vanes 27cw to provide the nozzle assembly shown within the turbine inlet 21w.
Figure 60 is an illustration of components of a section of a nozzle assembly forming part of a turbine according to an embodiment of the present invention. A perspective view of the nozzle assembly is shown in combination with an inlet sidewall 30w of a turbine inlet passageway. The nozzle assembly comprises first and second axially spaced baffles 31 at, 31 bt and three annular arrays of axially extending vanes 32at, 32bt, 32ct. An axially slidable sleeve 33t is disposed around the outer diameter of the vane arrays 32at-bt and is actuated to vary the axial width of the turbine inlet passageway and in doing so, the "throat" of the turbine. Each array of vanes 32at-ct is comprised of a plurality of vanes 34at, 34bt, 34ct. While not visible in figure 60, each vane 34at, 34ct in the outer arrays vanes 32at, 32ct incorporates an axially inwardly extending projection which is received in a set of complementary depression formed in the axially adjacent baffle 31 at, 31 bt respectively, and each vane 34bt in the middle array of vanes 32bt incorporates a pair of projections extending axially from the opposite edges of the vane 34bt which are received in complementary depressions defined by each of the baffles 31at-bt. In an alternative embodiment, the baffle 31 at supports the vane array 32bt and the baffle 31b supports the vane array 32ct. The vane array 32at is supported by the inlet sidewall 30w. The two baffles 31at-tb and their respective arrays of vanes 32bt-ct are of modular design and have been produced from the same casting. As such, the nozzle assembly can be manufactured in a more cost-effective manner than if the two baffles 31 at-bt and three arrays of vanes 32at-ct had been produced separately.
While both of the embodiments shown in figures 59 and 60 employ vanes it will be appreciated that one or more of said vanes or arrays of vanes could be replaced with an alternative form of axially extending formation, such as material having a honeycomb-like internal structure. Moreover, in alternative embodiments the cooperating features may both be defined on the baffles or both on vanes or other axially extending formations.
Referring once again to Figure 37, movement of the sleeve 28w in the axial direction may result in the sleeve 28w impacting one or more of the baffles 23aw, 23bw or vanes' 27aw, 27bw, 27cw. Such impact may result in jamming or sticking of the sleeve 28w, which is undesirable. According to an embodiment of the present invention, this problem may be at least partially overcome by providing a guide (which may be referred to as a running guide) for guiding the axial movement of the cylindrical sleeve 28. The guide is at least partially located within the annular inlet at a radially extent of the inlet portions 26aw, 26bw, 26cw, and extends in a substantially axial direction, parallel to the turbine axis. The guide may be located at a radially outer or inner extent of the inlet portions 26aw, 26bw, 26cw, depending on the configuration of the sleeve 28w. The arrangement shown in Figure 37 comprises such a guide, although this guide is not visible in the Figure. Figure 61 is used to describe the guide.
Figure 61 is a perspective view of baffles 23aw, 23bw and vanes 27bw, 27cw. A guide 40r is shown as comprising leading edges of the vanes 27bw, 27cw, the edges being at an outer radial extent of inlet portions defined by the baffles 23aw, 23bw. The leading edges of the vanes 27bw, 27cw extend in a linear, substantially continuous manner, parallel to the turbine axis. The continuity is only broken by the presence of the baffles 23aw, 23bw, the radially outer extent of which is preferably flush with the edges of the vanes 27bw, 27cw that form the guide 40r. In use, the sleeve may be moved along the guide 40r.
In this embodiment, the sleeve has an inner diameter greater than an outer diameter of the inlet portion - i.e. the sleeve surrounds the inlet portions. Although not in accordance with the present invention and described herein for the purposes of reference only if, in for example another variable geometry turbine, the sleeve has an outer diameter that is less than an inner diameter of the inlet portions - i.e. the inlet portions surround the sleeve - the one or more vane edges may be trailing edges, for example defining a guide at an inner radial extent of the vanes and/or inlet portions.
Figure 62 schematically depicts another embodiment of the present invention. Figure 62 is a perspective view of baffles 50ar, 50br and vanes 52ar, 52br. A guide is shown as comprising elongate members 54r. The elongate members 54r are located at an outer radially extent of the inlet portions defined by the baffles 50ar, 50br. A plurality of elongate members 54r are provided which are aligned in a linear, substantially continuous manner in between baffles 50ar, 50br, extending parallel to the turbine axis. The continuity is only broken by the presence of the baffles 50ar, 50br, the radially outer extent of which is preferably flush with an outer radial extent of the elongate members 54r that form the guide. In use, the sleeve may be moved along the guide.
The guide or guides in the form of elongate members (which are, in generally axially extending) may undesirably affect the flow of gas through the inlet. To minimise this undesirable effect, the guide or guides may be aligned with leading or trailing edges of vanes or other structures (preferably axially extending) provided in one or both inlet portions or passages in those portions.
In another, related embodiment, an elongate member, or a plurality of elongate members may not extend between baffles. Instead, the members may extend across one or more baffles, so that the radially outer extent of the baffles does not need to be flush with an outer radial extent of the elongate members that form the guide.
In the embodiment shown in Figure 62, the sleeve has an inner diameter greater than an outer diameter of the inlet portions - i.e. the sleeve surrounds the inlet portions Although not in accordance with the present invention and described herein for the purpose of reference only if, in for example another variable geometry turbine, the sleeve has an outer diameter that is less than an inner diameter of the inlet portions - i.e. the inlet portions surround the sleeve - the one or more elongate members may be located at an inner radially extent of the inlet portions.
Locating the guide of the present invention at least partially within the inlet ensures that the sleeve is properly guided within the inlet itself, where forces due to gas flow are greatest and where impact of the sleeve with vanes or baffles might otherwise occur. The sleeve might also be guided by a channel or the like in a housing of the turbine, for example. However, a guide in the housing might, alone, be insufficient to prevent impact of the sleeve with vanes or baffles in the inlet.
In any embodiment, a single guide extending in an axial direction may be provided. More than one guide may be provided, for example diametrically opposed guides, or guides located at certain locations around the inlet (e.g. three, four, five or more equally space locations, or at the location of a leading edge of a vane, at the location of each vane, or at the location of a group of vanes). A single guide may, instead, be understood as comprising sub-guides or guide parts or the like, which for example may be diametrically opposed sub-guides or guide parts, or sub-guides or guide parts that are located at certain locations around the inlet (e.g. three, four, five or more equally space locations, or at the location of a leading edge of a vane, at the location of each vane, or at the location of a group of vanes).
Although not visible in Figure 37, one, more or all of a portion of an extremity of the baffles 23aw, 23bw, a portion of an extremity of the vanes 27aw, 27bw, 27cw and/or a leading end of the sleeve 28w may be provided with an inclined surface for facilitating movement of the sleeve 28w across the baffle 23aw, 23bw and/or vane 27aw, 27bw, 27cw. The inclined surface is provided on a surface which might contact with the sleeve 28w, vane 27aw, 27bw, 27cw and/or baffle 23aw, 23bw.
Without such an inclined surface, the sleeve 28w might be more likely to come up against a more readily opposable surface (e.g. two flat faces or edges coming together), which might cause the sleeve 28w to jam, or which might at least cause sticking of the sleeve 28w, or excessive wear of the sleeve 28w, baffles 23aw, 23bw, or vanes 27aw, 27bw, 27cw.
Figure 63 shows an embodiment of a sleeve 60r. In this embodiment, an inner diameter of the sleeve 60r is greater than an outer diameter of the inlet portions discussed above - i.e. the sleeve 60r surrounds the inlet portions. A radially inner portion of a leading end 62r of the sleeve 60r is provided with an inclined surface 64r in the form of a chamfer for facilitating movement of the sleeve 60r across the baffles and/or vanes that form the inlet portions or passages. An outer radially portion 66r of the leading end 62r of the sleeve need not comprise an inclined surface, since the outer radially extent is remote from, and will thus not come into contact with, the vanes or baffles.
Figures 64a, 64b and 64c depict different examples of inclined surfaces that may be used in accordance with embodiments of the present invention. Figure 64a depicts a portion of an object 70r (e.g. a portion of a sleeve, baffle or vane) provided with a chamfer 72r. Figure 64b depicts a portion of an object 80r (e.g. a portion of a sleeve, baffle or vane) provided with a bevel 82r. Figure 64c depicts a portion of an object 90r (e.g. a portion of a sleeve, baffle or vane) provided with a rounded edge 92r.
Figure 64d shows that the inclined surface of Figure 64a, for example, could be extended by the provision of a further structure 100r (e.g. a lip, a cap or the like) having or providing a further inclined surface 102r.
Figure 64e shows an object 110r with no inclined surface. The object 110r can be provided with an inclined surface by the provision of a further structure 112r (e.g. a lip, a cap or the like) having or providing a further inclined surface 114r.
Due to manufacturing tolerances, or by deliberate design (e.g. for performance reasons), the baffles and vanes may not have an identical outer radial extent. Figures 65 and 66 depict examples where the baffles and vanes do not have the same outer radial extent.
Figure 65 shows vanes 120r extending, in a radially direction, slightly beyond a radially extent of baffles 122r. Because the vanes 120r extend slightly beyond a radially extent of baffles 122r, the vanes 120r are more likely to be impacted by, and potentially cause jamming of, a sleeve moving across those vanes 120r. For this reason, an extremity of the vanes 120r (at least) is provided with an inclined surface 124r for facilitating movement of the sleeve across vanes 120r.
In another embodiment (not shown), and alternatively or additionally, the problem identified in the preceding paragraph may be obviated or mitigated by providing a leading end of the sleeve with one or more discrete (i.e. not extending around the entire circumference of the sleeve) inclined surfaces distributed around a circumference of the sleeve, the location or locations of which coincide with a location of a vane. For example, a plurality or an array of such discrete inclined surfaces may be distributed around a circumference of the leading end of the sleeve to coincide with a plurality or an array of vanes circumferentially distributed around the inlet (e.g. within the inlet portions).
Figure 66 shows baffles 130r extending, in a radially direction, slightly beyond a radially extent of vanes 132r. Because the baffles 130 extend slightly beyond a radially extent of baffles 130r, the baffles 130r are more likely to be impacted by, and potentially cause jamming of, a sleeve moving across those baffles 130r. For this reason, an extremity of the baffles 130r (at least) is provided with an inclined surface 134r for facilitating movement of the sleeve across baffles 130r.
Although not in accordance with the present invention and described herein for the purpose of reference only, in a different but related variable geometry turbine, or sets of variable geometry turbines, an outer diameter of the sleeve is less than an inner diameter of the inlet portions discussed above - i.e. the sleeve is surrounded by the inlet portions. A radially outer portion of a leading end of the sleeve may be provided with an inclined surface in the form of a chamfer or the like (e.g. any inclined surface) for facilitating movement of the sleeve across the baffles and/or vanes that form the inlet portions or passages. In this variable geometry turbocharger, or set of variable geometry turbochargers, a portion of the radially inner (as opposed to outer) extremities of the baffles or vanes that are provided with the inclined surfaces, since in these embodiments the sleeve will move over these portions.
The inclined surface may not extend around an entire circumference of the sleeve, or along an entire circumference of an annular baffle, or be provided on each and every vane. Instead, the inclined surface or surfaces may be discrete, and located at appropriate parts or sections of the sleeve and/or baffle, or only on certain vanes. For example, the inclined surface may only need to be provided where there is likely to be (or would otherwise likely to be) opposed (e.g. potentially jamming) contact between the sleeve and baffles and/or vanes.
The inclined surface or surfaces of the vanes or baffles will, in general, be located and/or oriented to face toward a leading end of the sleeve, such that the sleeve is able to ride along and over the inclined surface.
The sleeve 28w in Figure 37 may form part of a sleeve assembly. The sleeve assembly comprises the sleeve 28w and an actuator for affecting movement of the sleeve 28w. The actuator may affect the movement by moving the sleeve 28w in a certain way, or constraining or controlling movement in a certain way. The actuator, or a part thereof, may form a part of, or be provided in or on, the sleeve 28w. In accordance with an embodiment of the present invention, a helical interface is present in the sleeve assembly. The helical interface is arranged to induce, in use, helical movement of a part of the sleeve assembly. The helical movement of a part of the assembly (which may be a part of or all of the actuator, or of the sleeve) ensures, or at least promotes, a more uniform distribution of forces on the sleeve during movement of the sleeve, which may assist in ensuring or promoting coaxial movement of the sleeve. Such coaxial movement may reduce the chances of the sleeve abutting against one or more baffles or vanes, which could otherwise result in sticking or jamming of the sleeve. Such sticking or jamming is undesirable.
The sleeve assembly used in Figure 37 is shown in more detail in Figure 67. Figure 67 shows an expanded view of the sleeve assembly. The sleeve assembly comprises the sleeve 28r and an actuator part in the form of a rotatable collar 140r. In practice, the rotatable collar 140r completely surrounds the sleeve 28r. However, this is not shown in the Figure, for reasons of clarity.
The sleeve 28r is provided with one or more helical ribs 142r. An inner surface of the rotatable collar is provided with one or more bearings 144 for engaging with opposing sides of the one or more helical ribs 142r. The rotatable collar 140r is fixed in position axially.
In use, the rotatable collar 140r is rotated, for example by another part of the actuator (not shown). Rotation of the rotatable collar 140r causes the one or more helical ribs 144r to move between bearings 144r. Because the rotatable collar 140r is fixed in position axially, and because the one or more ribs 142r are helical, rotation of the rotatable collar 140r causes helical movement of the sleeve 28r.
Figure 68 depicts an expanded view of another embodiment of a sleeve assembly. The sleeve assembly comprises a sleeve 150r and a first actuator part in the form of a rotatable collar 152r that is fixed in position axially. The rotatable collar 152r is provided with one or more helical grooves or slits 154r. The sleeve 150r is also provided with one or more helical grooves or slits 156r. The helical grooves or slits 154r of the rotatable collar 152r have the same handedness as those helical grooves or slits 156r of the sleeve 150r.
Disposed in-between the rotatable collar 152r and the sleeve 150r is a second part of the actuator in the form of an annulus 158r. The annulus 158r houses one or more bearings 160r configured to sit in the one or more helical grooves or slits 154r of the rotatable collar 152r, and to also sit in the helical grooves or slits 156r provided in the sleeve 150r.
In use, the rotatable collar 152r is rotated, for example by another part of the actuator (not shown). Rotation of the rotatable collar 152r causes the annulus 158r to move in a helical and/or axial direction, due to the bearings 160r moving in the helical grooves or slits 154r of the collar 152r. Such movement of the annulus 158r, in turn, causes movement of the sleeve 150r, due to the bearings 160r moving in the helical grooves or slits 156r of the sleeve 150r and the same handedness of the helical grooves or slits 154r, 156r. If movement of the sleeve 150r is not guided in some way, the sleeve 150r may simply rotate with the annulus 158r. Thus, the sleeve assembly may further comprise a guide for guiding (which includes restraining) movement of the sleeve 150r in an axial and/or helical manner.
In practice, the rotatable collar 152r completely surrounds the annulus 158r, which completely surrounds the sleeve 50r. However, this is not shown in the Figure, for reasons of clarity.
Figure 69 depicts expanded views of another embodiment of a sleeve assembly, in three stages of operation. The sleeve assembly comprises a sleeve 170r and a first actuator part in the form of a collar 172r that is fixed in position. The collar 172r is provided with one or more helical grooves or slits 174r. The sleeve 170r is also provided with one or more helical grooves or slits 176r. The helical grooves or slits 174r of the collar 172r have a different handedness to those helical grooves or slits 176r of the sleeve 170r.
Disposed in-between the collar 172r and the sleeve 170r is a second part of the actuator in the form of an annulus 178r. The annulus 178r houses one or more bearings 180r configured to sit in the one or more helical grooves or slits 174r of the collar 172r, and to also sit in the helical grooves or slits 176r provided in the sleeve 170r.
In use, the sleeve 170r is driven axially, for example by another part of the actuator, e.g. push rods or the like (not shown). Movement of the sleeve 170r causes the annulus 178r to move in a helical and/or axial direction, due to the bearings 180r moving in the helical grooves or slits 174r of the collar 172r and the helical grooves or slits 176r of the sleeve 170r itself. Movement of the bearings with the annulus, together with the different handedness of the helical grooves or slits 174r of the collar 172r and the helical grooves or slits 176r of the sleeve 170r, causes a driving force applied to the sleeve 170r to be uniformly distributed around the sleeve 170r.
In practice, the collar 172r completely surrounds the annulus 178r, which completely surrounds the sleeve 170r. However, this is not shown in the Figure, for reasons of clarity.
In any of the embodiment, one or more of the collar, rotatable collar and/or sleeve may be provided with a plurality of helical grooves or slits, disposed (e.g. equally) around a circumference of the respective collar, rotatable collar and/or sleeve. This may improve, or further improve, the equalisation of the distribution of driving or movement related forces around the sleeve.
Various apparatus, and components thereof, have been described for reducing or eliminating contact between structures defining axially offset inlet portions (e.g. baffles, vanes, or other structures). Figure 70 shows an alternative or additional way in which this result may be achieved.
Figure 70 schematically depicts a cylindrical sleeve structure 190r in accordance with an embodiment of the present invention. The cylindrical sleeve structure 190r is axially movable across the annular inlet discussed above to vary the size of a gas flow path through the inlet. The cylindrical sleeve structure 190r extends across the entire width of the inlet, such that a first end of the sleeve structure 192r is supported within or by the first inlet side wall, or a body defining that wall, and a second opposite end of the sleeve structure 194r is supported within or by the second sidewall, or a body defining that wall. Supporting the sleeve structure 190r at both sides of the inlet limits or reduced the chances of the sleeve structure coming into contact with a structure in the inlet.
The sleeve structure 190r comprises one or more apertures 196r (e.g. apertures with an axial extent) locatable within the inlet to, upon movement of the sleeve structure 190r, vary the size of a gas flow path through the inlet. This may include moving the sleeve structure 190r to align the apertures 196r with inlet portions or passageways defined in the inlet.
The sleeve structure 190r may be alternatively or additionally described as comprising a sleeve structure that has been provided with, of formed with the one, or more apertures.
The sleeve structure 190r may be alternatively or additionally described as comprising a first sleeve section 192r, and a second sleeve section 194r, the first and second sleeve sections being joined and axially separated by one or more (e.g. axially extending) support struts 198r. The one or more support struts 198r may be attached to the sleeve sections 192r, 194r. However, if the one or more support struts 198r are integral to (e.g. formed integrally with) the sleeve sections 192r, 194r, the overall sleeve structure may be more rigid and mechanically robust.
In alternative embodiments (see Figures 70a to 70c) a single sleeve section 200r, 204r may be provided with one or more support struts 202r, 206r. The sleeve section 200r, 204r may be supported within or by the first inlet side wall, or a body defining that wall, and the struts 202r, 206r, whose ends directed towards the second sidewall may be free (as in Figure 70a) or may be linked via a ring 208r (see Figures 70b and 70c), may be supported within or by the second sidewall, or a body defining that wall. Two axially separated sleeve sections may, however, be preferable, so that the size of the inlet can be controlled by bringing either of the sleeve sections into the inlet to control the size thereof. This may facilitate the control of the size of the inlet from either side thereof, which may provide additional functionality. Alternatively or additionally, the use of two sleeve sections, with an appropriate spacing defined therebetween, may allow for a particular inlet portion or passage thereof to be opened or closed in a selective manner by movement of the sleeve structure as a whole.
It will be appreciated that if struts are employed, apertures may be defined between the struts, or within and/or through the struts.
Struts, or any structure surrounding or defining the aforementioned apertures, may undesirably affect the flow of gas through the inlet: To minimise this undesirable effect, the struts or structures may be aligned with (or more generally, alignable with) leading or trailing edges of vanes or other structures (preferably axially extending) provided in one or both inlet portions or passages in those portions.
A vane may be any structure that divides an inlet portion into one or more inlet passages. The vane may preferably be defined as any structure that can direct gas flow in a particular direction, for example in accordance with a desired swirl angle or angle of attack or the like.
Preferentially, the sleeve surrounds the inlet portions, which has been found to give an improved aerodynamic performance. In other words, the inner diameter of the sleeve is greater than an outer diameter (or outer radial extent) of the inlet portion or portions. Although not in accordance with the present invention and described herein for the purpose of reference only, in another variable geometry turbine, the sleeve may be surrounded by the inlet portions. In other words, although it is not in accordance with the present invention the outer diameter of the sleeve may be less than inner diameter of the inlet portion or portions. In another embodiment, the sleeve may be moveable through the inlet portion or portions. In other words, the diameter (e.g. inner or outer, or average diameter) of the sleeve may be less than an outer diameter of the inlet portion or portions, and greater than an inner diameter of the inlet portion or portions.
Although not visible in Figure 37 an axial extent of a leading end (which includes a leading edge or face) of the sleeve 28w varies in magnitude around a circumference of the sleeve 28w. Figures 71a to 71c depict different examples of such variation.
Figure 71 a shows an embodiment of a sleeve 40q. The axial extent of a leading end 42q of the sleeve 40q varies in magnitude around a circumference of the sleeve 40q. The variation has a castellated configuration. The castellation might alternatively or additionally be described as axial variation in a square-wave like manner.
Figure 71b shows another embodiment of a sleeve 50q. The axial extent of a leading end 52q of the sleeve 50q varies in magnitude around a circumference of the sleeve 50q. The variation has a castellated-like configuration. In this embodiment, the castellation is not strictly angular, but involves a degree of curvature of side and base edges of the castellation. The castellation might alternatively or additionally be described as axial variation in a wave like manner.
Figure 71c shows another embodiment of a sleeve 60q. The axial extent of a leading end 62q of the sleeve 60q varies in magnitude around a circumference of the sleeve 60q. The variation has a wave-like property, for example varying in a sinusoidal manner. Because the axial extent of a leading end of the sleeve varies in magnitude around a circumference of the sleeve, the opening or closing of the inlet portions is not undertaken in a harsh step-wise manner, as might be the case if the axial extent exhibited no variation. This might result in associated or related step-wise characteristic in the performance of the turbine as a whole. Instead, the axial variation ensures that the opening or closing of the inlet portions is undertaken more gradually, which obviates or mitigates such a step-wise characteristic.
Referring to Figures 71 a to 71 c, a maximum 70q in the variation in magnitude of the axial extent may be substantially equal to: an axial width of an inlet portion; or an axial width of an inlet portion plus an axial width of a baffle that divides the inlet; or an axial width of an inlet passage through an inlet portion. This may facilitate a smooth change or transition in gas flow through the inlet portion as the sleeve is axially moved.
An inlet portion may comprise one or more vanes or other structures dividing the inlet portion into one or more inlet passages. The variation in magnitude of the axial extent in the circumferential direction (e.g. a pitch or wavelength 72q) may be synchronised in some way with a location of the one or more vanes or other structures, or a spacing between the one or more vanes or other structures. The synchronization may extend or continue around the circumference of the sleeve. For example, the synchronisation may be such that the variation in magnitude is in phase with the location of the vanes or other structures. Alternatively or additionally, an area defined between a maximum and minimum axial extent may be equal to an area defined between vanes or other structures in the vicinity of the variation. In other words, an area defined by recesses (or in other words between protrusions) of the leading end of the sleeve may be equal to an area of the opening or opening of inlet portions or inlet passages through those inlet portions. This may ensure that when a leading edge of the leading end of the sleeve is aligned with a baffle that divides the inlet, gas flow through an inlet portion which the sleeve has partially closed is optimised. The synchronisation may be used in combination with the concept described above relating to the maximum in the variation in magnitude of the axial extent.
Referring to figure 72, there is shown another embodiment of a sleeve 80q incorporating cut out areas A and B, only two of which are visible in figure 72. The total area of the cut out sections A and B has been designed to be substantially equal to the area of the throat defined by the vanes located radially inboard of the sleeve (not shown in figure 72). In this way, the axial location of the sleeve primarily controls the flow of gas through the turbine inlet rather than the vane throat. The axial depth of each area A is substantially equal to the distance between adjacent baffles within the turbine inlet. The purpose of each area B is to filter out or reduce the undesirable effect the baffle as far as possible by allowing more circumferential area to be exposed to the gas. flow at the point at which area A starts to be concealed by a baffle, for this reason the axial depth of area B is equal to the axial thickness of each baffle.
Alignment of a single vane throat area with a radially overlying cut-away section of the sleeve may only be important if the number of cutaways is effectively equal to the number of vanes. It will be appreciated that this does not necessarily need to be the case in all embodiments. In alternative embodiments, more cutaways may be desired for example. In this case, the same basic theory can be applied, i.e. the total flow area defined by the sleeve cut-aways should be substantially similar or equal to the total flow area defined by the combination of all of the vane throats. The shape of the profile of the end of the sleeve defined by one or more cut-away sections can be tailored to meet a specific requirement. For example, a sleeve may be provided with a saw tooth, sinusoidal or semicircular prolife.
Referring to figure 73, a sleeve 90q with semicircular cut-aways 92q may be particularly desirable because semicircular cut-aways offer a good compromise between flow characteristic and design for manufacture. A semicircle profile can be machined relatively easily in comparison to some more complex profiles, but still offers a circumferential increase in flow area with respect to axial position, to filter out the baffle.
It is advantageous in certain embodiments for the axial depth of the cut-away sections of the sleeve to be substantially equal to the spacing between adjacent baffles within the turbine inlet (including the width of one baffle). In such embodiments, it may also be advantageous that at least one or more, more preferably most, or all, of the baffles should have substantially equal axial spacing.
In some embodiments the cut-away sections at the end of the sleeve need not all be the same shape, size or have equal spacing, however it is generally preferred that their combined cross-sectional area relative to gas flow through the turbine inlet should be substantially equal to the cross-sectional area of the throat area of at least one annular array of inlet gas passages defined by the vanes.
The invention may be alternatively or additionally described or defined in many as will now be discussed.
An axial extent of a leading end of the sleeve varies in magnitude around a circumference of the sleeve. This results in a plurality of recesses and/or protrusions being defined around the circumference of the leading end of the sleeve. The recesses (which may be defined as spaces between protrusions) extend through the entire thickness or the sleeve. The recesses and/or protrusions are present to, upon movement of the sleeve, selectively block or expose (e.g. close or open) inlet portions, or inlet passages provided in those portions by other structures.
It will be apparent that the sleeve is free of vanes. It is known in the prior art to provide a sleeve with vanes, for example to affect the angle of attack of gas flowing past the vanes. However, it is important to note that such a prior art sleeve is cylindrical, and this cylinder is then provided with vanes. In other words, an axial extent of a leading end of the prior art sleeve does not vary in magnitude around a circumference of the sleeve. In this prior art sleeve, a plurality of recesses and/or protrusions are not defined around the circumference of the leading end of the sleeve. Instead, vanes protrude from a circular face of that sleeve.
In another prior art sleeve, a leading portion (i.e. not end) of the sleeve extends further in an axial direction that another, adjacent portion (e.g. an outer diameter portion) to accommodate a vane structure upon appropriate movement of the sleeve. However, and again, an axial extent of a leading end of the prior art sleeve does not vary in magnitude around a circumference of the sleeve. Instead, the axial extent defines a circular structure. In this prior art sleeve, a plurality of recesses and/or protrusions are not defined around the circumference of the leading end of the sleeve.
Preferentially, the sleeve surrounds the inlet portions, which has been found to give an improved aerodynamic performance. In other words, the inner diameter of the sleeve is greater than an outer diameter (or outer radial extent) of the inlet portion or portions. Although not in accordance with the present invention and described herein for the purpose of reference only, in another variable geometry turbine, the sleeve may be surrounded by the inlet portions. In other words, although not in accordance with the present invention the outer diameter of the sleeve may be less than inner diameter of the inlet portion or portions. In another embodiment, the sleeve may be moveable through the inlet portion or portions. In other words, the diameter (e.g. inner or outer, or average diameter) of the sleeve may be less than an outer diameter of the inlet portion or portions, and greater than an inner diameter of the inlet portion or portions.
The extent of the sleeve in the radial direction (which may be described as a thickness of the sleeve) may be small, to reduce aerodynamic load on the sleeve, or actuators thereof. 'Small', may be defined as being less than an axial width of the annular inlet, or less than an axial width of an inlet portion or passage way. The sleeve may be less than 5mm thick, less than 4mm thick, less than 3mm thick, less than 2mm thick, or less than 1mm thick, for example approximately 0.5mm thick.
Referring now to Fig. 74, there is shown a cross-sectional view of a turbine incorporating an axially sliding sleeve 401 and a baffle/vane arrangement in accordance with a preferred embodiment of the present invention in which the vanes 402 are configured so that their radially inner edges 403, i.e. the vane surfaces defining the gas outlets of the baffle/vane structure, have less (or minimal) axial overlap that their radially outer edges 404, i.e. the vane surfaces defining the inlets to the baffle/vane structure.
Figs. 75a and 75b are perspective and side-on views of a further alternative embodiment of a baffle/vanes structure according to the present invention which, when mounted within the annular inlet to the turbine, divides the inlet into at least two axially offset inlet passages which axially overlap.
Figs. 76 and 77 are perspective views of still further embodiments of baffle/vane structures according to the present invention which, when mounted within the annular inlet to the turbine, divides the inlet into at least two axially offset inlet passages which axially overlap.
Figure 78 is a perspective view of a sleeve 30n which forms part of a turbine in accordance with an embodiment of the invention. The sleeve 30n is generally cylindrical and has a first, free end 30an which may be used to define the size of an inlet when the sleeve 30n is installed in a turbine according to an embodiment of the present invention. A second end 30bn of the sleeve 30n is linked to a pair of guide rods 16n by respective thermal expansion tolerant structures 16an. When the sleeve 30n is installed in the turbine, the guide rods 16n extend axially and support the sleeve 30n. The guide rods 16n are also linked to an actuator. Accordingly, by appropriate control of the actuator (which may for instance be pneumatic or electric or any other suitable type), the axial position of the guide rods 16n and thus of the sleeve 30n can be controlled.
The thermal expansion tolerant structures 16an shown in figure 78 each have a pair of spring arms 16bn which mounted at one end to the sleeve 30n via a mounting portion 16cn. The spring arms 16bn are made of a material (such as sheet metal) which is flexible and can therefore tolerate relative movement which may occur between the sleeve 30n and the guide rods 16n due to thermal expansion of the sleeve 30n, guide rods 16n and/or any other part of the turbine (not shown) including the turbine housing. The spring arms 16bn and/or mounting portions 16cn may be constructed from a material which has a coefficient of thermal expansion which is different to that of the material from which the sleeve 30n and/or guide rods 16n is constructed. It will be appreciated that any other appropriate thermal expansion tolerant structure may be used. For example, any of the thermal expansion tolerant structures disclosed in British patent GB2468871 may be appropriately adapted for use within embodiments of the present invention. The entire contents of British patent application GB2468871 is hereby incorporated by reference.
Figure 79 shows a schematic axial cross-section of part of a turbine in accordance with the present invention. The turbine has a turbine wheel 5k mounted for rotation about an axis within a turbine housing 1 ak. A nozzle assembly 1k is mounted within an annular inlet 9k which is upstream of the turbine wheel 5k and downstream of an inlet volute 7k. A sleeve 30k is mounted to guide rods 16k (only one of which is shown in the figure) within a turbine housing 1ak, such that the guide rods 16k (and hence the sleeve 30k) can move axially control the size of the inlet 9. The guide rods 16k are located within a chamber 4k. Annular seals 2k and 3k are located between the turbine housing 1 ak and sleeve 30k at locations which are radially outboard of the sleeve 30k and radially inboard of the sleeve 30k respectively. The annular seals 2k and 3k define, at least in part, the chamber 4k by separating the chamber 4k from the inlet 9k and hence the inlet volute 7k. A first portion of the sleeve 30k extends into the inlet 9k (and is hence exposed to gas in the inlet which is at an inlet pressure), whereas a second portion of the sleeve 30k is received within the chamber 4k. Axial movement of the sleeve 30k causes the relative size of the first and second portions of the sleeve 30k to change. The annular seals 2k and 3k substantially seal between the sleeve 30k and the turbine housing 1 ak both radially outboard and radially inboard of the sleeve 30k. It follows that the flow of gas from the inlet 9k (and hence the inlet volute 7k) into the chamber 4k is substantially prevented. In this manner, the guide rods 16k and the portion of the sleeve 30k which are within the chamber 4k are isolated from, and hence not exposed to the gas in the inlet 9k. Gas in the inlet 9k may be at a relatively high pressure compared to the pressure of gas within the chamber 4k.
It will be appreciated that in some embodiments the seals 2k and 3k may totally prevent gas from flowing from the inlet 9k into the chamber 4k. In other embodiments, some degree of gas flow may be permitted by at least one of the seals 2k and 3k from the inlet 9k into the chamber 4k.
Figure 80 shows an alternative embodiment of the present invention which is similar to that show in figure 79. The embodiment shown in figure 80 differs from that shown in figure 79 in that the seal (2k within figure 79) which is radially outboard of the sleeve 30k has been omitted. The omission of the seal means that there is a gas flow path 6k between the inlet 9k (and hence the inlet volute 7k) and the chamber 4k. It follows that the pressure of the gas in the chamber 4k is substantially equal to the pressure of the gas in the inlet 9k (and hence the inlet volute 7k). It follows that substantially the entire sleeve 30k (and also the guide rods 16k) is exposed to gas which is at substantially the same pressure (in this case the pressure of the inlet 9k and hence the inlet volute 7k). Exposing substantially the entire sleeve to gas which is at substantially the same pressure may in some embodiments of the invention minimise the aerodynamic force which exerted by the gas on the sleeve. It follows that a reduction in the aerodynamic force which exerted by the gas on the sleeve may lead to a reduction in the aerodynamic force transmitted to the actuator and any actuator linkage from sleeve and the guide rods. A reduction in the aerodynamic force transmitted to the actuator and any actuator linkage may mean that a less powerful actuator and/or a less resilient actuator may be used. This may lead to a reduction in the cost, weight and or size of the turbine, which may be desirable in certain applications of the turbine.
The embodiment shown in figure 80 further differs from that shown in figure 79 in that there is a gas flow passage 8k between the inlet volute 7k and the chamber 4k. The gas flow passage 8k creates a further gas flow path 10k between the inlet volute 7k (and hence the inlet 9k) and the chamber 4k. The effect of the gas flow path 10k is substantially identical to that of gas flow path 6k in that the pressure of the gas in the inlet volute 7k (and hence that of the inlet 9k) is substantially equalised. Thus, substantially the entire sleeve 30k (and also the guide rods 16k) is exposed to gas which is at substantially the same pressure (in this case the pressure of the inlet 9k and hence the inlet volute 7k).
It will be appreciated that although the embodiment shown in figure 80 has both gas flow path 6k and gas flow path 10k to substantially equalise the pressure of the gas in the chamber 4k and in the inlet 9k (and hence the inlet volute 7k). In other embodiments, only one of the gas flow paths 6k or 10k may be provided.
Figure 81 shows an alternative embodiment in which there is a gas flow path 11k which enables substantially the entire of a relatively thin sleeve 30ak (for example, one with a small radial extent) to be exposed to gas which is at substantially the same pressure as that within the inlet 9k. Furthermore, a rear face 31k of the sleeve is exposed to gas which is at substantially the same pressure as that within the inlet 9k. The force which is exerted on the rear face 31k of the sleeve 30ak by the gas it is exposed to will urge the sleeve 30k in an opposite direction to that which is a result of a force exerted on a portion of the sleeve 30k which is in the inlet 9k. Only a portion of the guide rods 16k is received within the chamber 4k and hence exposed to gas which is at substantially the same pressure as that within the inlet 9k. Chamber 17k which contains a separate portion of the guide roads may be isolated (i.e. such that gas cannot flow between the two) from chamber 4k.
Figure 82 shows a further embodiment in which a relatively thick sleeve 30bk is received in chamber 4k. Gas flow path 11 k ensures that the chamber 4k contains gas which is at substantially the same pressure as that within the inlet 9k. Because the sleeve 30bk is thicker (i.e. has a greater radial extent) than sleeve 30ak the area of back face 31k will be greater than that of sleeve 30ak. As a result, the force exerted by the gas on the back face 31 k of the sleeve 30bk will be greater than that exerted on the back face 31k of the sleeve 30ak.
The embodiment shown in Figure 82 differs from that in figure 81 in that a protrusion 18k in the turbine housing 1 ak shown in figure 82 extends axially less towards the inlet 9k compared to a protrusion 19k in the turbine housing 1 ak shown in figure 81. This has the effect that, when the sleeve 30bk is in a closed position (as shown in figure 82) the sleeve is more exposed to a generally radial force exerted by gas flowing through the inlet 9k than sleeve 30ak in a closed position (as shown in figure 81). Minimising the generally radial force exerted on the sleeve 30ak may reduce wear on the sleeve 30ak in some embodiments of the invention.
Referring to figures 83 to 85 there is shown a turbine volute 1j incorporating an annular inlet defined between first and second inlet sidewalls 2j, 3j. Within the inlet is mounted a nozzle structure comprised of three axially offset annular arrays of axially extending vanes 4j interposed by first and second annular baffles 5j, 6j so as to define inlet passages through which exhaust gases flow towards the turbine wheel (not shown) during operation. There is also provided an axially slidable sleeve 7j which can be moved between the first and second sidewalls 2j, 3j so as to vary the axial width of the inlet.
As can be observed in figures 83 to 85, the sleeve 7j is located on a radius which is intermediate the inner and outer diameters of the baffles 5j, 6j. As a result, to facilitate axial movement of the sleeve 7j, the vanes 4j and baffles 5j, 6j define radially extending slits centred on the same radius and having a similar or greater radial thickness to that of the sleeve 7j. Locating the sleeve 7j within the 'throat' area of the vanes 4j reduces or may substantially remove any step response in mass flow of the exhaust gases as the sleeve 7j is displaced axially across the inlet.
Figure 86 is a radial cross-sectional illustration of an axially slidable sleeve 9j and array of vanes 8j according to an alternative embodiment of the present invention. The arrangement depicted in figure 86 is similar to that shown in figure 85 except for the fact that the sleeve 9j, while still clearly generally cylindrical, is composed of a plurality of sections or segments 10j, 11 j which are substantially straight in axial cross section. Such an embodiment may be advantageous, for example, to better align the sleeve 9j with the position of minimum cross-sectional area, i.e. the throat defined by the vanes 8j.
Nozzle structures in accordance with the present invention may be configured to provide varying efficiency for different inlet widths (i.e. corresponding to different positions of the sleeve or sleeves). For instance, it is mentioned above in relation to the embodiment of Figs. 3 to 6 that baffles may be unequally spaced across the axial width of the inlet. Where the sleeve is capable of moving to positions between the location of baffles, there may be greater inefficiency at such an intermediate position between two relatively widely spaced baffles than between two relatively closely spaced baffles. The ability to tailor the efficiency of the nozzle in this way may have a number of applications.
For instance, turbocharged engines may have an exhaust flow path for returning exhaust gas into the engine inlet. Such systems are generally referred to as "exhaust gas re-circulation" systems, or EGR systems. EGR systems are designed to reduce particulate emissions from the engine by re-circulating a portion of exhaust gas for re-combustion which may often be necessary to meet increasingly stringent emissions legislation. Introduction of re-circulating exhaust gas into the boosted inlet air flow can require a raised exhaust manifold pressure in "short route" EGR systems in which the re-circulating exhaust gas passes from the exhaust to the engine inlet without reaching the turbocharger turbine.
Variable geometry turbochargers can be used to assist in raising the exhaust gas to the required pressure for re-circulation to increase the "back pressure" in the exhaust gas flow upstream of the turbine. When using a variable geometry turbocharger in such a way it has been found that it can be advantageous to reduce the operating efficiency of the turbine at certain inlet widths. In accordance with the present invention this can be achieved by constructing the nozzle e.g. spacing of the inlet baffles, so that the inlet passages 39 are particularly wide (axially) in the region of the mid-stroke position of the sleeve. For instance, between two suitably widely positioned baffles, there will be a range of relatively inefficient positions for the sleeve, typically corresponding to the pair of baffles being a third to a two-thirds open, and the baffle positions may be chosen to provide inefficient operation when the whole inlet is more than half open. Such deliberately produced inefficiency may not have any significant effect on the efficiency of the nozzle when the sleeve is fully open, or indeed fully or nearly fully closed.
It would be possible to achieve a similar effect from "honeycomb" type nozzle structures in accordance with the invention, by ensuring that the inlet passages 39 have a greater maximum axial width around the mid-point of the nozzle assembly or any other axial location of the nozzle corresponding to inlet widths at which reduced efficiency is desired.
In some embodiments of the invention it might be advantageous to decrease the baffle spacing (or otherwise increase the axial size of the inlet passages 39) in regions of the inlet corresponding to closed or relatively closed positions of the sleeve. That is, using a given number of baffles there may be advantages in arranging the baffles closer together near to the fully closed position. For any given number of baffles, this may increase efficiency in relatively closed positions of the sleeve.
Various other modifications may be made to certain embodiments of the invention. For instance, the sleeve could be provided with one or more bypass apertures which are only exposed to gas flow through the inlet when the sleeve is in a closed or "over-closed" position. An "over-closed" position may be regarded as a position in which the sleeve moves axially beyond a position necessary to fully block the inlet. A bypass aperture could for instance allow exhaust gas to bleed through the sleeve towards the turbine inlet, towards the turbine downstream of it's inlet (e.g. via the turbine shroud) or even downstream of the turbine to bypass it entirely in order to increase the temperature of exhaust gas downstream of the turbine which might be useful in order to oxidise soot collected in a downstream particulate filter, in order to regenerate the filter. In other applications there may be other advantageous aerodynamic effects to be achieved by allowing the sleeve to move into an "over-closed" position, and thereby open an alternative gas flow path.
Similarly, in some embodiments of the invention it may be advantageous for the sleeve to be movable to an "over-open" position to expose a bypass gas passage which is not normally open as the sleeve moves through its normal operating range to control the size of the inlet. Such a bypass passage could for instance provide wastegate functionality which may extend the effective flow range of the turbine. The bypass passage could for instance comprise one or more bypass apertures formed in a cylindrical surface extending inboard of the sliding sleeve (e.g. as an extension to the sleeve). This arrangement may be particularly suitable for a turbine-side mounted sleeve. In an alternative arrangement movement of the sleeve into an "over-open" position may expose apertures provided in the turbine housing thereby opening a bypass flow path. This arrangement may be particularly suitable for a sleeve mounted on the bearing housing side of the inlet. Bypass arrangements such as that disclosed in US 7,207,176 could for instance be adapted for application to embodiments of the present invention.
It will be understood that whereas embodiments of the present invention have been described in relation to the turbine of a turbocharger, the invention is not limited in application to turbochargers but could be incorporated in turbines of other apparatus. Non-limiting examples of such alternatives include power turbines, steam turbines and gas turbines. In embodiments in which the turbine is part of a turbocharger, the turbocharger might be part of a turbocharged combustion engine, such as a compression ignition (diesel) engine, or a gasoline direction injection (GDi) engine for example. Such applications could include more than one turbocharger including a turbine according to the present invention. Other possible applications include fuel cell turbochargers or turbines.
Turbines in accordance with the present invention may include a wastegate, which may be a controllable independently of the sleeve (or sleeves). Wastegates of conventional design might be used.
The present invention may be used in one or more turbines of a multi-stage turbine arrangement. For instance, a radial inflow turbine according to the present invention may be combined with a second turbine stage which could be radial or axial. The multi-stage turbines may be mounted to a common turbine shaft. Turbines according to the present invention may similarly be included in turbochargers of a multi-turbocharger system. For instance, turbochargers in a series or parallel arrangement may include turbines according to the present invention.
Turbines according to the present invention may also be used for generating electrical energy (for instance in an automotive system) or in waste heat recovery systems (again particularly for automotive applications, e.g. where a secondary fluid such as water or a refrigerant fluid is boiled by low grade engine/exhaust heat, and expands to drive the turbine). The secondary fluid could even be compressed air as described by the Brayton cycle.
The turbine inlet volute may be a divided volute. For instance, it is known to provide a turbocharger turbine with a volute divided into more than one chamber, each volute chamber being connected to a different set of engine cylinders. In this case, the division is usually an annular wall within the volute separating the volute into axially adjacent portions. It may also be possible to divide the volute circumferentially so that different arcuate portions of the volute deliver gas to different arcuate portions of the turbine inlet.
The turbine of the present invention has been illustrated in the figures using a single flow volute, however it is applicable to housings that are split axially, whereby gas from one or more of the cylinders of an engine are directed to one of the divided volutes, and gas from one or more of the other cylinders is directed to a different volute of the turbine housing. It is also possible to split a turbine housing circumferentially to provide multiple circumferentially divided volutes, or even to split the turbine housing both circumferentially and axially.
However an axially or circumferentially split volute can for instance be distinguished from the axially and circumferentially spaced gas inlet passages of the present invention. For example, the latter relate to a nozzle structure arranged to accelerate exhaust gas from the volute towards the turbine, and also possibly to adjust or control the swirl angle of the gas as it accelerates. Although straight inlet gas passages are in principle possible, generally they are curved so as to control the gas swirl angle efficiently. The gas inlet passages may also distinguished from divided volutes in that the former receive gas from the volute (or divided volute), and split the gas into an array of paths. By contrast divided volutes receive gas from the exhaust manifold, and generally from differing cylinders of an engine so as to retain the gas velocity in gas pulses resulting from individual engine cylinder opening events. As such, a divided volute transmits the gas to the annular inlet, while the gas inlet passages of the present invention accept gas from the volute.
It would be possible to provide the present invention in conjunction with an axially divided volute. In such embodiments the baffle(s) axially dividing the gas inlet passages would generally be distinct from the wall(s) axially dividing the volutes.
It would also be possible to provide the present invention in conjunction with a circumferentially divided volute. A wall dividing two circumferentially spaced volutes could extend radially inwards to further serve as one of the vanes (again provided that the sliding sleeve operates at the inner diameter of the gas inlet passages). Alternatively such a volute dividing wall could extend radially inward and adjacent to the sliding sleeve, so the sleeve is radially inboard of the volute dividing wall, but outboard of the gas inlet passages. Such an arrangement could beneficially mitigate the loss of gas velocity in gas pulses experienced in a single volute turbine, and might also assist in guiding the sliding sleeve to mitigate the possibility of it becoming misaligned and consequently jamming.
The present invention has been described generally in relation to radial inflow turbines. However it is not necessary for the flow to be fully restricted to the radial plane, and a moderately conical inlet may be implemented instead. Furthermore the invention may be applied to "mixed-flow" turbines, whereby the conical inlet has a cone angle in the region of up to 45 degrees or where the turbine housing is axially split into more than one volute, each having a different degree of mixed flow direction. For example one volute might have an inlet substantially in the radial plane while a second volute might have an inlet extending backward in the region of 45 degrees. The present invention could be applied to either one or both of the volutes in such an embodiment.
The invention described in the present could be applied in the case of an axially divided turbine housing, where one volute directs gas axially to the turbine, and another volute directs gas radially or at an intermediate angle to the turbine.
The invention is also applicable to dual (or multi) stage turbines. Therefore it might be applied to the first stage of a multi-stage turbine where the first stage is a radial-inflow turbine stage (or mixed flow turbine stage) and there are one or more additional stages such as axial turbines stage and/or a radial-outlet turbine stage.
As indicated above, the present invention may be implemented to vary the geometry of only one or some of the volutes of an axially divided volute turbine. Indeed it would be possible to provide two variable geometry mechanisms as described herein, utilising two sliding sleeves so as to vary the flow of two axially divided volutes independently.

Claims

A variable geometry turbine comprising
a turbine wheel (5) mounted for rotation about a turbine axis within a housing (1), the housing (1) defining an annular inlet (9) surrounding the turbine wheel (5) and defined between first (32) and second (33) inlet sidewalls; and
a cylindrical sleeve (30) axially movable across the annular inlet (9) to vary the size of a gas flow path through the inlet (9);
the annular inlet (9) being divided into at least two axially offset inlet passages (39);
the inner diameter of the sleeve (30) being greater than the inner diameter of the inlet passages (39);
wherein the axially movable sleeve (30) is movable across substantially the full axial width of the annular inlet (9) so as to substantially close or entirely close the gas flow path through the annular inlet (9).
A variable geometry turbine according to claim 1, wherein the inner diameter of the sleeve (30) is less than or substantially equal to the outer diameter of the inlet passages (39).
A variable geometry turbine according to claim 1, wherein the inner diameter of the sleeve (30) is greater than the outer diameter of the inlet passages (39).
A variable geometry turbine according to any preceding claim, wherein the sleeve (30) is axially movable across the annular inlet (9) in a direction towards the second inlet sidewall (33) so as reduce the size of the gas flow path through the inlet (9), and wherein at least a portion of an end of the sleeve (30) nearer to the first inlet sidewall (32) than the second inlet sidewall (33) is configured so as to be exposable to gases flowing through said annular inlet (9) during use.
A variable geometry turbine according to any one of claims 1 to 3, wherein the sleeve (30) is axially movable across the annular inlet (9) in a direction towards the second inlet sidewall (33) so as reduce the size of the gas flow path through the inlet (9), and wherein at least a portion of an end of the sleeve (30) nearer to the first inlet sidewall (32) than the second inlet sidewall (33) is configured so as to be located in between said first (32) and second (33) inlet sidewall during axial movement of the sleeve (30) across the annular inlet (9).
A variable geometry turbine according to any preceding claim, wherein the sleeve (30) possesses a small radial thickness.
A variable geometry turbine according to claim 1, wherein the sleeve (30) possesses a radial thickness which is less than the axial width of the annular inlet (9).
A variable geometry turbine according to any one of claims 1 to 6, wherein the annular inlet (9) is divided into at least two axially offset inlet passages (39) by at least one annular baffle (38) axially spaced from the first (32) and second (33) inlet sidewalls.
A variable geometry turbine according to claim 8, wherein inlet vanes (37) extend axially across at least one of the axially offset inlet passages (39), and optionally wherein the minimum distance between a baffle (38) and the turbine wheel (5) is less than the minimum distance between an adjacent vane (37) and the turbine wheel (5).
A variable geometry turbine according to claim 9, wherein the trailing edges of at least some of the vanes (37) extending across one of the axially offset inlet passages (39) lie on a different radius to the trailing edges of at least some of the vanes (37) extending across another of the axially offset inlet passages (39).
A variable geometry turbine according to any one of claims 1 to 7, wherein the annular inlet (9) is divided into an annular array of substantially tubular inlet passages (39) extending generally towards the turbine wheel (5), wherein the annular array of inlet passages (39) comprises at least three axially offset inlet passages (39).