WO2020039210A1 - Adaptateur - Google Patents

Adaptateur Download PDF

Info

Publication number
WO2020039210A1
WO2020039210A1 PCT/GB2019/052379 GB2019052379W WO2020039210A1 WO 2020039210 A1 WO2020039210 A1 WO 2020039210A1 GB 2019052379 W GB2019052379 W GB 2019052379W WO 2020039210 A1 WO2020039210 A1 WO 2020039210A1
Authority
WO
WIPO (PCT)
Prior art keywords
adapter
primary
turbine
conduit
flow
Prior art date
Application number
PCT/GB2019/052379
Other languages
English (en)
Inventor
Gregory Ashby
Original Assignee
Cummins Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Cummins Ltd filed Critical Cummins Ltd
Priority to CN201980069505.4A priority Critical patent/CN112888842B/zh
Publication of WO2020039210A1 publication Critical patent/WO2020039210A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/16—Control of the pumps by bypassing charging air
    • F02B37/162—Control of the pumps by bypassing charging air by bypassing, e.g. partially, intake air from pump inlet to pump outlet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/16—Control of the pumps by bypassing charging air
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the present invention relates to an adapter for an outlet of a turbine, and in particular to an adapter for an outlet of a turbine in which the adapter comprises a diffuser.
  • Turbines are machines which convert the potential energy of a fluid into mechanical work.
  • Turbines comprise a turbine wheel and a turbine housing defining a turbine inlet and a turbine outlet.
  • fluid enters the turbine through the turbine inlet, where it is passed to the turbine wheel.
  • the fluid impinges upon one or more blades defined by the turbine wheel, thus exerting a force upon the turbine wheel causing the turbine wheel to spin.
  • Such bypass passages are typically fitted with a valve, known as a wastegate, configured to permit or prevent flow through the bypass passage.
  • Wastegated turbines typically comprise an adapter mounted to an outlet of the turbine housing.
  • the turbine outlet typically comprises a turbine wheel portion for receiving fluid from the turbine wheel and a wastegate portion for receiving fluid from the bypass passage.
  • the wastegate portion is normally positioned immediately adjacent to the turbine wheel portion.
  • the adapter functions as an end cap which forces the fluid exiting the wastegate to merge with the fluid exiting the turbine wheel in the region immediately downstream of the turbine wheel.
  • the fluid exiting the wastegate and the fluid exiting the turbine wheel are discharged into a common plenum formed by the adapter immediately downstream of the wastegate and the turbine wheel.
  • Such adapters provide the advantage that they are relatively compact and cheap to manufacture.
  • the region where the two fluid streams merge often becomes highly turbulent.
  • the resulting turbulence often acts as a barrier that restricts the flow of the merged fluid stream. This results in increased fluid pressure downstream of the turbine wheel and reduces the efficiency of the turbine.
  • Some turbines comprise a diffuser positioned at the turbine outlet, downstream of the turbine wheel.
  • a diffuser defines a passage which widens as the fluid travels further downstream of the turbine outlet. As the passage widens the velocity of the fluid in the diffuser will decrease resulting in a corresponding increase in pressure of the fluid in the diffuser.
  • the pressure at the outlet of the diffuser is determined by the downstream components. The pressure increase provided by the diffuser therefore results in a decrease in pressure at the outlet of the turbine wheel. As a result, the difference in pressure across the turbine wheel is increased and therefore more energy can be extracted from the fluid, thus increasing the efficiency of the turbine.
  • an adapter for an outlet of a turbine having a wastegate comprising: a primary conduit configured to receive fluid that has passed through a turbine wheel of the turbine; and a secondary conduit configured to receive fluid that has passed through the wastegate; wherein the primary conduit further comprises a diffuser configured to decelerate fluid as it moves away from the turbine wheel, and a port configured to deliver fluid from the secondary conduit to the primary conduit; and wherein the port is positioned downstream of the diffuser.
  • adapter it is meant a housing for containing fluid that is configured to connect to an outlet of a turbine, such as for example the outlet of a turbine housing.
  • conduit it is meant a ducting or other enclosed space having an inlet for receiving fluid and an outlet for discharging fluid.
  • downstream refers to the direction of travel of fluid within the primary and/or secondary conduits under normal operating conditions (for example, in a direction from an inlet of the primary and/or secondary conduits to an outlet of the primary and/or secondary conduits).
  • port is intended to mean an opening or orifice capable of providing fluid flow communication between the primary conduit and the secondary conduit.
  • the term“diffuser” means a portion of the primary conduit which increases in cross-sectional area relative to the direction of travel of the fluid received from the turbine wheel.
  • the diffuser imparts a decelerating force upon the fluid within the primary conduit due to the Bernoulli Effect.
  • the fluid which has passed through the turbine wheel may be referred to as the turbine flow and the fluid which has passed through the wastegate may be referred to as the bypass flow.
  • downstream of the diffuser is intended to mean that the port is positioned downstream of the point at which the diffuser defines its maximum cross- sectional area. That is to say, the port does not overlap with or form part of the diffuser, and is positioned at a point in the flow after the diffuser has decelerated the fluid.
  • the port is positioned downstream of the diffuser, the presence of the port does not interfere with the turbine flow as it passes through the diffuser.
  • the diffuser is able to impart the maximum amount of deceleration upon the turbine flow before the turbine flow is subjected to any other influences. This is particularly advantageous, for example, when the wastegate is closed. In such circumstances, no fluid passes through the secondary conduit and there is no bypass flow.
  • the secondary conduit acts as plenum which contains generally stationary fluid. When the turbine flow passes the port, the turbine flow will interfere with the stationary fluid in the secondary conduit.
  • the port is positioned downstream of the diffuser, the interference between the stationary fluid in the secondary conduit and the turbine flow does not affect the ability of the diffuser to decelerate the turbine flow (since the turbine flow has already been decelerated). Furthermore, when the wastegate is open, the turbine flow and the bypass flow will merge downstream of the port. Merging of the turbine flow and bypass flow will cause interference between the two flows. However, because the port is positioned downstream of the diffuser, such interference only occurs after the turbine flow has been decelerated by the diffuser. As such, the introduction of the bypass flow to the turbine flow does not detrimentally affect the diffuser.
  • the use of a port ensures that the primary conduit connects to the secondary conduit at a single concentrated location, for example on one side of the primary conduit.
  • the geometry of the adapter is relatively compact, thus making the adapter easier to accommodate for applications with tight spatial constraints, such as within vehicle engines.
  • such arrangements more costly to manufacture are not suitable for applications with tight spatial constraints.
  • the primary conduit may define a primary flow axis and the secondary conduit defines a secondary flow axis, and wherein, at the port, the secondary flow axis is inclined at an acute angle relative to the primary flow axis.
  • flow axis it is meant the centreline of a conduit. That is to say, the flow axis is the line which follows the centre of the primary or secondary conduits long the entire length of the conduit. For example, for a conduit which is a straight pipe, the flow axis of the conduit will be the central axis of the pipe. However, for non-straight conduits the flow axis will bend in conformance with the shape of the conduit.
  • the incline between the secondary flow axis and the primary flow axis refers to the smallest angle subtended between the primary flow axis and the secondary flow axis at the port. This angle may alternatively be referred to as the “confluence angle”. By“acute angle” it is meant an angle less than 90 °.
  • the secondary axis may be inclined relative to the primary flow axis at an angle in the range of around 35 ° to around 55 °, in the range of around 40 ° to around 50 ° or at an angle of around 45 °.
  • the confluence angle is too high, merging of the bypass flow and the turbine flow may cause turbulence which acts to restrict the flow of fluid through the adapter. If the flow becomes too restricted, the deceleration provided by the diffuser will be reduced or cancelled entirely.
  • the size of the port will increase. For example, typically the shape of the port is determined by projecting the cross-section of the secondary conduit onto the primary conduit at the confluence angle. The larger the area of the port, the more interference the port will cause with the turbine flow when the wastegate is closed, and the larger the primary conduit needs to be to accommodate the port area.
  • the adapter may comprise an outer wall defining a generally hollow interior and a dividing wall extending across at least part of the hollow interior, and wherein the dividing wall separates the primary conduit from the secondary conduit.
  • outer wall it is meant a wall delimiting the outermost boundary of the adapter.
  • the outer wall is the wall seen by the user from the exterior of the adapter, and at least partially defines the geometry of the primary and secondary conduits.
  • dividing wall it is meant a wall extending across at least part of the interior of the adapter. Because a dividing wall is used to separate the primary conduit from the secondary conduit, the adapter is more compact. By contrast, without the dividing wall the primary conduit and the secondary conduit would each require respective outer walls. This would increase the overall size of the adapter, and make the adapter more difficult and costly to manufacture.
  • the adapter may be formed as a single integral body.
  • single integral body it is meant that the adapter is manufactured as a single piece.
  • the adapter may be manufactured, for example, by casting and/or machining. When the adapter is made from a single body, the adapter is cheaper and easier to manufacture and will have increased mechanical strength to resist vibrations.
  • the primary conduit may define a primary inlet and the secondary conduit defines a secondary inlet, the primary inlet and the secondary inlet being positioned at a first end of the adapter. Because the primary and secondary inlets are both positioned at the first end of the adapter, adapter is more compact and is easy to manufacture. Furthermore, such an adapter will be suitable for use with turbines in which the wastegate is positioned adjacent to the outlet of the turbine wheel, which is beneficial for turbochargers for internal combustion engines.
  • the adapter may comprise a flange configured to seal the adapter against a housing of the turbine at the outlet of the turbine. When the adapter is sealed against the turbine housing this ensures that all of the turbine flow is directed into the primary conduit and all of the bypass flow is directed into the secondary conduit without leakage. Where the adapter is used in conjunction with an internal combustion engine, if any leakage were to occur, this could result in exhaust gases escaping to atmosphere without passing through the exhaust gas aftertreatment system, which would be damaging to the environment and potentially cause the adapter to fail regulatory tests.
  • the primary conduit may define an outlet, and wherein the outlet is positioned at a second end of the adapter opposite to the first end.
  • opposite it is meant that the outlet is positioned at a terminal end of the adapter which is a different end of the adapter to the first end of the adapter.
  • the term“opposite” is not intended to imply that there is a symmetrical relationship between the first end and the second end of the adapter.
  • the primary conduit may define a generally linear flow axis.
  • the flow axis may be the primary flow axis.
  • generally linear it is meant that the primary conduit extends in a substantially straight line, along a single axis.
  • the primary conduit does not comprise any bends which would change the overall direction of the bulk flow through the primary conduit.
  • the primary conduit is therefore generally straight. Because the primary conduit is straight, the primary conduit does not comprise any bends which would change the overall flow direction of the turbine flow. As such, frictional losses associated with bent pipe sections are minimised.
  • the primary conduit may define a bent flow axis.
  • the flow axis may be the primary flow axis.
  • bent flow axis it is meant an axis that deviates from a straight line.
  • a bent flow axis therefore comprises one or more changes in direction.
  • the primary conduit defines comprises a bent flow axis, the primary conduit is able to direct the turbine flow around complex geometries. This is particularly advantageous when the adapter is for use in applications where space is tight, such as for example within a vehicle engine housing.
  • the bent flow axis may comprise a right angled bend.
  • the secondary conduit may define a first bend parallel to the bent flow axis of the primary conduit, and a second bend inclined towards the primary conduit. In such arrangements, the secondary conduit will follow the path of the primary conduit before merging the bypass flow with the turbine flow. Because the secondary conduit follows the path of the primary conduit, the adapter can be made more compact.
  • Figure 1 is a cross-section of a turbocharger according to the prior art
  • Figure 2 is a cross-sectional view of a portion of a further known turbocharger comprising a wastegate;
  • Figure 3 is a cross-sectional view of an adapter according to a first embodiment of the present invention, configured for use with the turbocharger of Figure 2;
  • Figure 4 is an external side view of the adapter of Figure 3;
  • Figure 5 is a plan view of a first end of the adapter of Figure 3;
  • Figure 6 is an external side view of an adapter according to a second embodiment of the present invention, configured for use with the turbocharger of Figure 2;
  • Figure 7 is a plan view of a first end of the adapter of Figure 6.
  • FIG. 1 shows a cross-section of a known turbocharger 2.
  • the turbocharger 2 comprises a compressor 4, a turbine 6 and a bearing housing 7.
  • the compressor 4 comprises a compressor inlet 8, a compressor wheel 10, a compressor housing 12, and a compressor outlet 14.
  • the turbine 6 comprises a turbine inlet 16, a turbine wheel 18, a turbine housing 20 and a turbine outlet 22.
  • the bearing housing 7 comprises bearings 26 which support a shaft 24 for rotation.
  • the compressor wheel 10 and the turbine wheel 18 are fixedly mounted to the shaft 24 such that that compressor wheel 10 and the turbine wheel 18 rotate in unison.
  • the compressor wheel 10 During use, rotation of the compressor wheel 10 causes air to enter the compressor inlet 8.
  • the air passes through the compressor wheel 10 and into a compressor volute 28 defined by the compressor housing 12. Due to the kinetic energy imparted on the incoming air by the compressor wheel 10, the air in the compressor volute 28 is at a higher pressure than the air entering the compressor inlet 8.
  • the compressed air exits the compressor 4 via the compressor outlet 14 where it is delivered to an internal combustion engine (not shown).
  • the air passes through a heat exchanger to cool the air before it arrives at the internal combustion engine. Fuel is mixed with the air and the fuel-air mixture is combusted within the internal combustion engine.
  • the turbine 6 further comprises a diffuser 34 which is defined by a tapered wall 36 of the turbine housing 20 at the turbine outlet 22.
  • the cross-sectional area of the diffuser 34 in a plane normal to the turbocharger axis 32 increases in a direction axially away from the turbine wheel 18. This causes the velocity of the exhaust gases exiting the turbine 6 to reduce and the pressure of the exhaust gases to increase (in accordance with the Bernoulli Effect).
  • the outlet of the diffuser 34 is connected to an exhaust gas aftertreatment system (not shown) which will determine the pressure of the exhaust gases at the outlet of the diffuser 34.
  • the presence of the diffuser 34 therefore has the effect of reducing the pressure of the exhaust gases at the exit of the turbine wheel 18. This increases the pressure difference between the turbine inlet 16 and the turbine outlet 22, thus increasing the amount of energy extracted from the exhaust gases and improving the efficiency of the turbine 6.
  • FIG. 2 shows a further known turbocharger 2.
  • the turbine 6 of the turbocharger 2 comprises a wastegate 38 including a wastegate valve 40 and a valve shaft 42.
  • the turbine housing 20 comprises a divider 33 which separates the turbine outlet 22 into a turbine wheel portion 22a and a wastegate portion 22b.
  • the turbine housing 20 further defines a bypass passage 46 which passes from the turbine volute 30 to the wastegate portion 22b of the turbine outlet 22.
  • the turbine housing 20 comprises an end face 50 which is configured for mating against a diffuser (not shown).
  • the end face 50 comprises a number of mounting holes 52 which are configured to receive bolts so as to hold the diffuser against the turbine housing 20.
  • the wastegate valve 40 defines a closed position in which the wastegate valve 40 bears against the turbine housing 20 to cover the bypass passage 46 and an open position in which the wastegate valve 40 does not contact the turbine housing 20.
  • an actuating member (not shown) exerts a rotational force upon the valve shaft 42 to move the wastegate valve 40 between the open and closed positions.
  • exhaust gases are prevented from passing through the bypass passage 46. As such, all exhaust gases are made to flow through the turbine wheel 18.
  • the wastegate valve 40 is in the open position, some of the exhaust gas can flow from the turbine volute 30 directly to the turbine outlet 22 via the bypass passage 46 without passing through the turbine wheel 18.
  • FIG 3 shows a cross-sectional view of a first embodiment of an adapter 54 according to the present invention
  • Figure 4 shows an exterior view of the adapter 54 of Figure 3.
  • the adapter 54 comprises an outer wall 56 defining a generally hollow interior.
  • the adapter 54 further comprises a dividing wall 58 which separates the interior into a primary conduit 60 and a secondary conduit 62.
  • the primary conduit 60 is configured to receive exhaust gases from the turbine wheel 18 and the secondary conduit 62 is configured to receive exhaust gases from the wastegate 38.
  • the primary conduit 60 defines a primary inlet 64 and the secondary conduit 62 defines a secondary inlet 66.
  • the exhaust gases entering the primary conduit 60 via the primary inlet 64 have passed through the turbine wheel 18 and are therefore referred to as the“turbine flow”.
  • the exhaust gases entering the secondary conduit 62 via the secondary inlet 66 have bypassed the turbine wheel 18 through the wastegate 38, and are therefore referred to as the“bypass flow”.
  • the bypass flow occurs only when the wastegate valve 40 is opened. When the wastegate valve 40 is closed, only the turbine flow will pass through the adapter 54.
  • the primary inlet 64 and the secondary inlet 66 are positioned at a first end 68 of the adapter 54.
  • the first end 68 comprises a mounting flange 69 configured to abut the end face 50 of the turbine housing 20.
  • the mounting flange 69 defines a plurality of through holes 71 (see Figure 5) which are aligned with the mounting holes 52 of the turbine housing 20.
  • adapter 54 is mounted against the turbine housing 20 so that the primary inlet 64 is aligned with the turbine wheel portion 22a of the turbine outlet 22 and the secondary inlet 66 is aligned with the wastegate portion 22b of the turbine outlet 22.
  • the dividing wall 58 of the adapter 54 is further aligned with the divider 33 of the turbine housing 20 so as to separate the bypass flow from the turbine flow.
  • bolts (not shown) are passed through the through holes 71 of the adapter 54 and are received by the mounting holes 52.
  • a gasket (not shown) may further be provided to prevent leakage of exhaust gases at the interface between the adapter 54 and the turbine housing 20. The gasket is positioned between the mounting flange 69 of the adapter 54 and end face 50 the turbine housing 20, the gasket being compressed between the mounting flange 69 and the end face 50 under the action of the bolts so as to form a fluid-tight seal.
  • the primary conduit 60 further comprises an outlet 70 positioned at a second end 72 of the adapter 54, opposite the first end 68.
  • the outlet 70 is typically connected to a downstream component such as an exhaust throttle valve or an exhaust gas aftertreatment system (not shown).
  • the outer wall 56 and the dividing wall 58 define a port 74 therebetween which provides fluid flow communication between the primary conduit 60 and the secondary conduit 62.
  • the port 74 acts as an outlet to the secondary conduit 62 to deliver exhaust gases from the secondary conduit 62 to the primary conduit 60.
  • exhaust gases are received at the first end 68 of the adapter 54 by the primary inlet 64 and the secondary inlet 66, and are discharged at the second end 72 by the outlet 70.
  • the shape of the port 74 is determined by the geometry of the primary conduit 60 and the secondary conduit 62 at the point where the primary conduit 60 and secondary conduit 62 meet.
  • the port 74 is typically a projection of the cross-section of the secondary conduit 62 onto the primary conduit 60.
  • the port 74 may define substantially any suitable geometry for permitting fluid flow communication from the secondary conduit 62 to the primary conduit 60. Because of the port 74, the secondary conduit 62 connects to the primary conduit 60 only on one side of the primary conduit 60. As such, the port 74 merges the bypass flow and the turbine flow at a single concentrated location.
  • the geometry of the adapter 54 is therefore relatively compact, thus making the adapter 54 easier to accommodate for applications with tight spatial constraints, such as within vehicle engines.
  • the dividing wall 58 extends at least partially across the interior of the adapter 54 to separate the primary conduit 60 from the secondary conduit 62 upstream of the port 74.
  • the dividing wall 58 therefore allows the adapter 54 to be more compact.
  • the adapter 54 may be manufactured as a single integral body. Because the adapter 54 is a single body, the adapter 54 is easier and more economical to manufacture.
  • the adapter 54 could be composed of a plurality of mechanically separate components.
  • the primary conduit 60 and the secondary conduit 62 may be manufactured as separate pieces of piping that are joined at the port 74.
  • the adapter 54 described above is preferably composed of ductile cast iron.
  • the adapter 54 may be composed of substantially any material suitable for the environment within which the adapter 54 is to be used.
  • the adapter 54 is for use within a turbocharger 2. Therefore, the material of the adapter 54 must be able to withstand high temperature exhaust gases and mechanical vibrations generated by the internal combustion engine.
  • suitable materials include, for example high temperature capable alloys of iron or steel, including Inconel.
  • the adapter 54 may be manufactured using any suitable method, such as for example by casting and/or machining.
  • the primary conduit 60 is generally tubular and comprises a diffuser 76 and a pipe section 78 which are defined by the outer wall 56 and dividing wall 58.
  • the diffuser 76 extends from the primary inlet 64 and connects to the pipe section 78.
  • the diffuser 76 has a cross-sectional area which increases in the direction of travel of the exhaust gases along the primary conduit 60 (i.e. from the first end 68 to the second end 72 of the adapter 54).
  • the diffuser 76 is generally frusto-conical in shape, such that the diffuser 76 has a narrower diameter at the primary inlet 60 than the pipe section 78.
  • the portions of the outer wall 56 and dividing wall 58 which define the diffuser 76 are tapered relative to a longitudinal centreline of the diffuser 76 at an angle within the range of about 5 ° to about 10 °, and preferably about 7 °. Larger taper angles result in lower resistance to flow due to fluid friction, but are more likely to cause flow separation (especially at high flow rates). Smaller taper angles reduce the likelihood of flow separation but increase fluid friction. Furthermore, smaller taper angles result in a less compact adapter 54 because the length of the diffuser 76 must be increased. It has been found that taper angles within the range above provide sufficient increase in pressure of the turbine flow whilst ensuring the adapter 54 remains compact, with a taper angle of 7 ° being the most optimised taper angle. However, it will be appreciated that in alternative embodiments substantially any suitable taper angle can be used.
  • the cross-section of the primary conduit 60 is generally circular so that the primary inlet 64 matches the shape of the turbine wheel portion 22a of the turbine outlet 22.
  • the primary inlet 64 defines a diameter of approximately 45 mm, however the diameter of the primary inlet 64 may be varied to match the size of the turbine wheel 18.
  • the cross-section of the primary conduit 60 may be substantially any suitable shape.
  • the cross-section of the primary conduit 60 may be quadrilateral.
  • the cross-section of the primary conduit 60 may change shape between the primary inlet 64 and the outlet 70.
  • the primary inlet 64 may be generally circular and the outlet 70 may be quadrilateral.
  • the diffuser 76 does not need to be precisely frusto-conical and, in practice, may include one or more distortions which depart from the frusto- conical shape.
  • the outer wall 56 may comprise one or more depressions 77 which are provided to permit a bolt to be passed into an adjacent through-hole 71.
  • the cross-sectional area of the diffuser 76 increases from the primary inlet 64 to the point at which the diffuser 76 joins the pipe section 78.
  • the change in cross-sectional area should be smooth so as to avoid the turbulence generated by the presence of sharp edges.
  • the pipe section 78 of the adapter 54 defines a constant cross-sectional area in the direction of travel of the exhaust gases along the primary conduit 60.
  • the diameter of the pipe section 78 is approximately 58 mm.
  • the diameter of the pipe section 78 may be varied in dependence upon the desired taper angle of the diffuser 76.
  • the diameter of the pipe section 78 may be sized to match that of any downstream components (e.g. exhaust throttle valves, aftertreatment piping etc.), and therefore the taper angle may be varied in dependence upon the size of the downstream components.
  • the port 74 connects the secondary conduit 62 to the pipe section 78 of the primary conduit 60.
  • the port 74 is positioned downstream of the diffuser 76, such that merging of the turbine and bypass flows occurs downstream of the diffuser 76.
  • the secondary conduit 62 provides a relatively large plenum for the containment of stagnant exhaust gases.
  • the additional fluid capacity provided by the secondary conduit 62 absorbs fluctuations in pressure in the region immediately downstream of the wastegate valve 40 and helps to reduce the likelihood of wastegate “flutter” (a condition in which the pressure downstream of a wastegate valve causes the valve to rattle, which may occur during opening or closing of the valve).
  • the turbine flow will be disturbed by the capacity provided by the secondary conduit 62.
  • the diffuser 76 is able to fully decelerate the turbine flow before the turbine flow is disturbed by the presence of the secondary conduit 62. That is to say, by displacing the point of confluence between turbine flow in the primary conduit 60 and bypass flow in the secondary conduit 62 downstream of the diffuser 76, the turbine flow can obtain the full benefit of the diffuser 76 before it is disturbed by stagnant exhaust gases, bypass flow from the secondary conduit 62, or the geometry of the port 74 itself (for example, by the edge of the dividing wall 58).
  • the primary conduit 60 defines a primary flow axis 80.
  • the primary flow axis 80 is the centreline of the primary conduit 60 between the primary inlet 64 and the outlet 70.
  • the secondary conduit 62 defines a secondary flow axis 82 which is the centreline of the secondary conduit 62 between the secondary inlet 66 and the port 74.
  • the primary conduit 60 extends generally axially, such that the primary flow axis 80 is generally linear.
  • the secondary conduit 62 comprises a bend 84 which causes the secondary conduit 62 to merge with the primary conduit 60 at the port 74.
  • the secondary flow axis 82 initially extends linearly from the secondary inlet 66 and then bends inwardly towards the primary flow axis 80.
  • the primary flow axis 80 and the secondary flow axis 82 define a confluence angle Q therebetween.
  • the confluence angle Q is the relative angle between the primary flow axis 80 and the secondary flow axis 82 at the port 74 (where the primary conduit 60 joins the secondary conduit 62).
  • the confluence angle Q is an acute angle, and is preferably within the range of about 35 ° to about 55 °, more preferably is within the range of about 40 ° to about 50 °, and most preferably is within the range of about 40 ° to about 45 °. In the embodiment shown in Figure 3, the confluence angle Q is 45 °.
  • Increasing the confluence angle Q improves flow through the primary conduit 60 when the wastegate valve 40 is closed, whilst decreasing the confluence angle Q improves the joining of the turbine and bypass flows when the wastegate valve 40 is open. It has been found that a confluence angle within the range of about 35 ° to 55 ° provides a good balance between these two factors. In particular, it has been found that by controlling the confluence angle Q the amount of turbulence produced by merging of the turbine flow and the bypass flow can be adjusted; in most cases the preferred result being a reduction in turbulence by optimisation of the confluence angle Q.
  • the size of the port 74 will increase due to the geometrical intersection between the primary conduit 60 and the secondary conduit 62.
  • the size of the port 74 will be limited by the axial extent of the pipe section 78, which in turn will be determined by the overall spatial requirements of the turbine adapter 54 for its application (for example, the available space within an engine compartment of a vehicle).
  • the size of the port 74 is increased, when the wastegate valve 40 is closed the port 74 will create a greater disturbance on the turbine flow as it passes the port 74, increasing pressure losses and decreasing the efficiency of the turbine 6. As such, it is generally not possible to reduce the confluence angle below around 35 ° or else the adapter 54 would become too large.
  • Figure 5 shows a plan view of the first end 68 of the adapter 54.
  • the primary conduit 60 defines a generally circular cross section at the primary inlet 64.
  • the diameter of the primary inlet 64 is sized to match the diameter of the turbine housing 20 at the outlet of the turbine wheel 18.
  • the secondary conduit 62 defines a generally triangular cross-section at the secondary inlet 66.
  • the secondary inlet 66 is shaped so that it is large enough to accommodate the wastegate 38 which sits within the outlet of the turbine housing 20. Referring back to Figure 3, as the bypass flow moves away from the secondary inlet 66 along the secondary conduit 62 and towards the port 74, the secondary conduit 62 converges to define a throat 79.
  • the throat 79 is the part of the secondary conduit 62 which defines the minimum cross-sectional area Athroat in relation to the direction of the bypass flow.
  • the cross-sectional area A thr oat of the throat 79 is chosen so that it is about at least three times greater than the cross- sectional area of the bypass passage 46 so as to ensure that the throat 79 does not create any restriction to flow through the secondary conduit 62. Furthermore, it has been found that when the cross-sectional area A thr oat of the throat 79 is about at least three times larger than the cross-sectional area of the bypass passage 46, if the wastegate valve 40 fails (i.e.
  • the wastegate valve 40 if it becomes separated from the valve shaft 42) the wastegate valve 40 is able to pass through the throat 79 and out of the outlet 70 of the adapter 54. This prevents the wastegate valve 40 from blocking the secondary conduit 62, which would prevent exhaust gases from bypassing the turbine wheel 18. As such, sizing the throat 79 so that it is sufficiently large enough to allow the wastegate valve 40 to pass through it in the event of failure reduces the risk of the turbine wheel 18 over-speeding.
  • the outlet 70 of the adapter 54 defines a cross-sectional area A ou t relative to the primary flow axis 80.
  • the primary inlet 64 defines a cross-sectional area A turbine relative to the primary flow axis 80.
  • the cross-sectional areas of the outlet 70 is chosen so that it is greater than or equal to the sum of the cross-sectional area A thr oat of the throat 79 of the secondary conduit 62 and the cross-sectional area A turbine of the primary inlet 64.
  • the cross-sectional area A ou t of the outlet 70 will be equal to the cross- sectional area of the downstream end of the diffuser 76.
  • the cross-sectional area A th roat of the throat 79 is therefore equal to the increase in cross- sectional area of the diffuser 76 between the primary inlet 64 and the pipe section 78.
  • the outlet 70 is therefore large enough to accommodate flow through both the primary conduit 60 and the secondary conduit 62, without causing a restriction when the wastegate valve 40 is open.
  • the primary conduit 60 of the adapter 54 changes in cross-sectional area due to the diffuser 76, it will be appreciated that the direction of the turbine flow through the primary conduit 60 occurs in a linear direction (i.e. along a generally straight line).
  • the primary conduit 60 is generally axially extending. That is to say, the primary conduit 60 does not bend or change direction.
  • the secondary conduit 62 extends generally parallel to the primary conduit 60 until it reaches the bend 84, at which point the secondary conduit changes direction to force the bypass flow to merge with the turbine flow. Most of the flow along the adapter 54 therefore occurs in the same direction as the primary conduit 54, which is to say in a straight line.
  • This configuration of the adapter 54 may therefore be referred to as a “straight” configuration.
  • the adapter 54 has a straight configuration, changes in flow direction from the primary inlet 64 and the secondary inlet 66 to the outlet 70 are minimised. This means that frictional pressure losses associated with more complex pipe geometries are reduced.
  • the precise spatial configuration of the adapter 54 will depend upon the spatial constraints for the application in which the adapter 54 is to be used. For example, where the adapter 54 is used within a vehicle engine, there may not be sufficient space for the adapter to have a straight configuration.
  • the primary conduit 60 and the secondary conduit 62 may comprise bends or turns in one or more directions so as to connect the inlets 64, 66 to the outlet 70.
  • the spatial constrains may require that the primary inlet 64 and/or the secondary inlet 66 and/or the outlet 70 are oriented in different planes relative to one another.
  • Figure 6 shows an exterior side view of a second embodiment of an adapter 54’ according to the present invention
  • Figure 7 shows an exterior top view of the adapter 54’ of Figure 6.
  • the second embodiment of the adapter 54’ differs from the first embodiment in that the first end 68 and the second end 72 of the adapter 54’ are oriented at right angles to one another. That is to say, the plane defined by the primary inlet 64 and the secondary inlet 66 is perpendicular to the plane defined by the outlet 70.
  • the primary conduit 60 and the secondary conduit 62 comprise a right angle turn 86, shown most clearly in Figure 6.
  • the right angle turn 86 occurs in a plane which is mutually orthogonal to the plane defined by primary and secondary inlets 64, 66 and the plane defined by the outlet 70. That is to say, the right angle turn occurs within the plane of Figure 6.
  • the right angle turn 86 differs from the bend 84 of the secondary conduit 62 in that the right angle turn 86 changes the direction of both the primary conduit 60 and the secondary conduit 62 by the same amount.
  • both the primary and secondary flow axes 80, 82 (now shown) are bent.
  • the secondary flow axis 82 comprises a bend and the primary flow axis 80 is straight.
  • the primary conduit 60 and secondary conduit 62 extend generally parallel to one another throughout the right angle turn 86.
  • the bend 84 of the secondary conduit 62 directs the bypass flow towards the turbine flow and the two flows subsequently merge.
  • the secondary conduit 62 therefore defines a first bend in which the secondary flow axis 82 is generally parallel to the primary flow axis 80, and a second bend in which the secondary flow axis 82 is inclined towards the primary flow axis 80.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

L'invention concerne un adaptateur pour une sortie d'une turbine munie d'une soupape de décharge. L'adaptateur comprend : un conduit principal conçu pour recevoir un fluide qui est passé par une roue de la turbine ; et un conduit secondaire conçu pour recevoir un fluide qui est passé par la soupape de décharge. Le conduit principal comprend en outre un diffuseur conçu pour ralentir le fluide à mesure qu'il s'éloigne de la roue de turbine, et un orifice conçu pour acheminer un fluide du conduit secondaire au conduit principal; et l'orifice étant positionné en aval du diffuseur.
PCT/GB2019/052379 2018-08-24 2019-08-23 Adaptateur WO2020039210A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201980069505.4A CN112888842B (zh) 2018-08-24 2019-08-23 适配器

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1813870.1A GB2576714B (en) 2018-08-24 2018-08-24 Adapter
GB1813870.1 2018-08-24

Publications (1)

Publication Number Publication Date
WO2020039210A1 true WO2020039210A1 (fr) 2020-02-27

Family

ID=63715308

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2019/052379 WO2020039210A1 (fr) 2018-08-24 2019-08-23 Adaptateur

Country Status (3)

Country Link
CN (1) CN112888842B (fr)
GB (1) GB2576714B (fr)
WO (1) WO2020039210A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2461810A1 (fr) * 1979-07-14 1981-02-06 Ishikawajima Harima Heavy Ind Turbogenerateur
EP1612385A1 (fr) * 2004-06-29 2006-01-04 Ford Global Technologies, LLC Conception compacte d'une turbine et d'une soupape de décharge
DE102013219329A1 (de) * 2013-09-25 2015-03-26 Volkswagen Aktiengesellschaft Turbinenanordnung für eine Brennkraftmaschine und aufladbare Brennkraftmaschine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2000199427A (ja) * 1998-12-28 2000-07-18 Hitachi Metals Ltd タ―ボチャ―ジャ用タ―ビンハウジングを鋳造一体化した排気マニホ―ルド
CN1213237C (zh) * 2002-05-31 2005-08-03 乐金电子(天津)电器有限公司 涡轮压缩机的扩散器结构
US8438855B2 (en) * 2008-07-24 2013-05-14 General Electric Company Slotted compressor diffuser and related method
US9759228B2 (en) * 2009-10-16 2017-09-12 GM Global Technology Operations LLC Turbocharger and air induction system incorporating the same and method of using the same
DE102015201805B4 (de) * 2015-02-03 2024-05-29 Borgwarner Inc. Abgasturbolader
US10731546B2 (en) * 2017-02-06 2020-08-04 Borgwarner Inc. Diffuser in wastegate turbine housings

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2461810A1 (fr) * 1979-07-14 1981-02-06 Ishikawajima Harima Heavy Ind Turbogenerateur
EP1612385A1 (fr) * 2004-06-29 2006-01-04 Ford Global Technologies, LLC Conception compacte d'une turbine et d'une soupape de décharge
DE102013219329A1 (de) * 2013-09-25 2015-03-26 Volkswagen Aktiengesellschaft Turbinenanordnung für eine Brennkraftmaschine und aufladbare Brennkraftmaschine

Also Published As

Publication number Publication date
CN112888842A (zh) 2021-06-01
GB2576714B (en) 2022-10-12
GB201813870D0 (en) 2018-10-10
CN112888842B (zh) 2022-12-27
GB2576714A (en) 2020-03-04

Similar Documents

Publication Publication Date Title
US8281588B2 (en) Turbomachine system and turbine therefor
US9157396B2 (en) Nozzled turbine
JPH0519013B2 (fr)
JP5711321B2 (ja) 四方排気ガス弁
US10087824B2 (en) Wastegate with injected flow
GB2320294A (en) Exhaust-gas turbocharger turbine for an internal combustion engine
US20100251709A1 (en) Flow-optimized bypass for turbo engines
EP3061921A1 (fr) Diffuseur de turbocompresseur avec corps central
JP2005521827A (ja) 可変ターボ過給機
CN103850727A (zh) 涡轮增压器的抽吸密封
CN112888842B (zh) 适配器
JP2012211572A (ja) ターボチャージャ
US20040062638A1 (en) Turbine for an exhaust gas turbocharger
JP6834862B2 (ja) ターボチャージャ
JP2022076179A (ja) 遠心圧縮機、ターボチャージャ及びエンジンシステム
US20220003151A1 (en) Turbine and turbocharger
US11280259B2 (en) Turbine
Tamaki et al. Enhancement of centrifugal compressor operating range by control of inlet recirculation with inlet fins
JP7084543B2 (ja) タービンハウジングおよびターボチャージャ
JP7232352B2 (ja) コンプレッサおよび該コンプレッサを備えるターボチャージャ
WO2024009407A1 (fr) Carter de compresseur centrifuge, compresseur centrifuge et turbocompresseur
JP7300908B2 (ja) タービンハウジングおよびターボチャージャ
JP7278903B2 (ja) タービン排気室
JP2023000817A (ja) ターボチャージャ
US20240125250A1 (en) Heat shield for a supercharging device

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 19759717

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 19759717

Country of ref document: EP

Kind code of ref document: A1