EP1965039A2 - Montageträger für einen variablen Düsenmechanismus eines Abgasturboladers mit variabler Einschnürung - Google Patents

Montageträger für einen variablen Düsenmechanismus eines Abgasturboladers mit variabler Einschnürung Download PDF

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Publication number
EP1965039A2
EP1965039A2 EP07122041A EP07122041A EP1965039A2 EP 1965039 A2 EP1965039 A2 EP 1965039A2 EP 07122041 A EP07122041 A EP 07122041A EP 07122041 A EP07122041 A EP 07122041A EP 1965039 A2 EP1965039 A2 EP 1965039A2
Authority
EP
European Patent Office
Prior art keywords
nozzle
turbine casing
insert member
variable
scroll
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
EP07122041A
Other languages
English (en)
French (fr)
Inventor
Yasuaki Jinnai
Ryo Miyauchi
Yoichi Ueno
Noriyuki Hayashi
Takao Yokoyama
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries 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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP1965039A2 publication Critical patent/EP1965039A2/de
Withdrawn legal-status Critical Current

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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
    • F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • 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
    • F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
    • 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
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the present invention relates to a mounting structure for a variable nozzle mechanism which is used in a variable-throat exhaust turbocharger, and which introduces exhaust gas from an engine (internal combustion engine) to apply the exhaust gas onto a turbine rotor by way of a scroll and a plurality of nozzle vanes formed in a turbine casing, and which is configured so as to change the blade angles of the plurality of nozzle vanes.
  • a patent document 1 Japanese Patent Laid-Open No. 2001-207858 discloses an example of a relatively small-sized turbocharger which is used for a vehicle internal combustion engine or the like, and in which engine exhaust gas charged in a scroll within a turbine casing is fed through a plurality of nozzle vanes provided on the inner peripheral side of the scroll, and is then applied to a turbine rotor provided on the inner peripheral side of the nozzle vanes. Further, there have been developed a variable-throat radial flow exhaust turbocharger incorporating a variable nozzle mechanism which is capable of changing the blade angle of a plurality of nozzle vanes.
  • Japanese Patent document 2 Japanese Patent Laid-Open No. 2004-132367 discloses another example of the variable-throat radial flow exhaust turbocharger incorporating a variable nozzle mechanism.
  • FIG. 12 which shows a conventional example of the variable-throat radial flow exhaust turbocharger incorporating the above-mentioned variable nozzle mechanism, in a sectional view along the rotating axis thereof, there are shown a turbine casing 10, a scroll 11 formed in a spiral-like configuration on the outer peripheral side of the turbine casing 11, and a radial flow turbine rotor 12 arranged coaxially with a compressor 8.
  • the turbine rotor 12 has a turbine shaft 12a which is rotatably journalled to a bearing housing 13 through the intermediary of a bearing 16.
  • a compressor housing 7 accommodated therein with the compressor 8, an air inlet 9 of the compressor housing, spiral air passages 7a and the rotating axis 100a of the exhaust turbocharger.
  • nozzle vanes 2 which are arranged in the circumferential direction of the turbine on the inner peripheral side of the scroll 11 at equal intervals.
  • Each of the nozzle vanes 2 is coupled at its end part with a nozzle shaft 02 which is rotatably supported in a nozzle mount 4 secured to the turbine casing 10. Further, the blade angle of the nozzle vanes can be changed by a variable nozzle mechanism 100.
  • the nozzle vanes 2 are arranged between the nozzle mount 4 and an annular nozzle plate 6 which is coupled to the nozzle mount 4 through the intermediary of a plurality of nozzle supports. Further the nozzle plate 6 is fitted in an attaching part of the turbine casing 10.
  • a drive ring 3 which is formed in a disc-like shape and which is rotatably supported to the turbine casing 10.
  • the drive ring 3 is fixed thereto with drive pins 32 at circumferentially equal intervals.
  • lever plates 1 each having on the inlet side a groove which is engaged therein with the associated drive pin 32, and fixed on the outlet side to the associated nozzle shaft 02.
  • a link 15 coupled to a drive source (which is not shown) for the nozzle vanes 2, and a pin 14 which is coupled to the link 15.
  • the pin 14 is engaged with the drive ring 3 which is therefore rotated.
  • variable-throat exhaust turbocharger incorporating the variable nozzle mechanism having the above-mentioned configuration
  • exhaust gas from an engine (which is not shown) is led into the scroll 11 so as to be swirled along spiral passages in the scroll, and is then introduced through the nozzle vanes 2.
  • the exhaust gas flows through the gaps between the vanes and then flows onto the turbine rotor 12 from the outer periphery of the latter.
  • the exhaust gas flows radially toward the center of the turbine rotor 12 so as to carry out an expansive work to the turbine rotor 12.
  • the exhaust gas axially flows being led to a gas outlet 10b from which the exhaust gas is discharged, outside of the supercharger.
  • a blade angle of the nozzle vanes 2 is set in the actuator by a blade angle control means (which is not shown) in order to regulate the flow rate of exhaust gas passing through the nozzle vanes to a desired value.
  • the reciprocal displacement of the actuator in response to the thus set blade angle is transmitted by way of the link 15 and the pin 14 to the drive ring 3 which is therefore rotated.
  • the rotation of the above-mentioned drive ring 3 causes drive pins 32 which are secured to the drive ring 3 at equal intervals in the circumferential direction thereof to rotate the lever plates 1 around the nozzle shafts 02. Due to the rotation of the nozzle shafts 02, the nozzle vanes 2 are configured so as to be turned in order to change the blade angle thereof up to the value set to the actuator.
  • Patent Document 2 Japanese Patent Laid-Open No. 2004-132367 discloses another example of the variable-throat radial flow exhaust turbocharger, which incorporates the above-mentioned variable nozzle mechanism.
  • variable-throat radial flow exhaust turbocharger incorporating the above-mentioned variable nozzle mechanism, which is shown in Fig. 12 and which is disclosed in the Patent Document 1 (Japanese Patent Laid-Open No. 2001-207858 ), the Patent Document 2 (Japanese Laid-Open No. 2004-132367 ) or the like, has raised the following problems which should be solved:
  • variable-throat radial flow exhaust turbocharger incorporating the variable nozzle mechanism 100, as shown in Fig. 12 , a drive force is transmitted from an actuator having a diaphragm or a motor driven actuator to the drive ring 3 by way of the link 15 and the pin 14.
  • the drive ring 3 is rotated, and accordingly, the drive pins 32 rotate the lever plates 1 around the nozzle shafts 02 through the rotation of the drive ring 3.
  • the nozzle vanes 2 are turned so as to change the blade angle thereof to a value set by the actuator.
  • the above-mentioned nozzle plates 6 may serve as slide surfaces on which the above-mentioned nozzle vanes 2 slide, and accordingly, it is sufficient to allow the nozzle plates 6 alone to have an acid resistance and a strength which can prevent deformation. Thus, the durability of the variable nozzle mechanism can be prevented from being affected by a strength or the same of the turbine casing 10.
  • a nozzle assembly composed of the nozzle vanes 2, the nozzle plates 6, the nozzle supports 5, the nozzle mount 4 and the like is held by the nozzle mount 4 whose outer peripheral flange is supported by the inner diameter side flange of the turbine casing 10.
  • the nozzle mount 4 which is a main support member for the nozzle assembly is supported by the turbine casing 10.
  • the turbine casing 10 would possibly be largely deformed.
  • the nozzle assembly is excited by vibration from the engine, and accordingly, the nozzle assembly and the nozzle link mechanism coupled to the former are worn so as to lower the function of the variable nozzle mechanism 100.
  • the boost pressure (air supply pressure) to the engine is greatly lowered.
  • variable displacement type exhaust turbocharger inevitably has a cut part 11s which defines a scroll underline in the lower portion of the scroll 11 in the turbine casing 10. Accordingly, in order to increase the sectional area A of the scroll 11, it is required to enlarge the scroll in both radial and axial directions for increasing the sectional area A thereof. As a result, there would be caused such a problem that the turbine casing 10 becomes large-sized.
  • the distance R to the center of the sectional area can be decreased by flattening the scroll 11 in the radial direction of the turbine.
  • the scroll 11 itself becomes longer in the axial direction of the turbine.
  • the scroll 11 shown in Fig. 12 is formed therein with the undercut part 11s in order to cause the turbine outlet side to have a large bulge.
  • This undercut part 11a is advantageous in order to ensure a satisfactory aerodynamic performance.
  • the manufacture of a mold core for the scroll of the turbine casing 10 having the under cut part 11s causes a high degree of difficulty in working, resulting in a problem of low productivity.
  • the turbine casing is usually made of cast iron.
  • the above-mentioned structure inevitably requires split-type core, and accordingly, burring is possibly caused within the scroll 11.
  • an object of the present invention is to provided a nozzle assembly including a nozzle mount and nozzle vanes, which has a firm support structure while avoiding receiving affection by a thermal deformation of a turbine casing or an external force applied to the turbine casing.
  • Another object of the present invention is to facilitate the formation of the nozzle assembly by simplifying a scroll portion so as to have a substantially opened configuration.
  • Another object of the present invention is to provide a variable-throat exhaust turbocharger with enhanced productivity of a turbine casing by decreasing the number of mold cores for the scroll, used during casting of the turbine casing.
  • variable-throat exhaust turbocharger incorporating a variable nozzle mechanism in which the plurality of nozzle vanes are rotatably supported on an annular nozzle mount so as to change the blade angle of the nozzle vanes in order to regulate the volume of the exhaust gas fed onto the turbine rotor.
  • the present invention specifically includes the following configurations:
  • variable-throat exhaust turbocharger incorporating a variable nozzle mechanism, characterized in that an opening which has no protrusion projected from the inner peripheral surface of the scroll in the turbine casing toward the outer peripheral side thereof, and which is axially linear is formed in the turbine casing.
  • the present invention is characterized in that an insert shroud having a protrusion projected toward the outer peripheral side and serving as a part of the inner surface of the scroll is attached to the opening, and the support part of an annular nozzle plate which is coupled to the nozzle mount through the intermediary of the nozzle supports is formed in the insert shroud.
  • variable-throat exhaust turbocharger incorporating the variable nozzle mechanism, characterized in that an insert member formed in an annular shape is removably attached to the outer periphery of the nozzle mount, and the outer periphery of the insert member is fitted in an attaching bore which is formed so as to be opened from the scroll of the turbine casing toward the bearing housing side in order to mount the insert member to the bearing housing.
  • the present invention is characterized in that an opening having no protrusion which is projected from the inner peripheral part of the scroll of the turbine casing toward the outer peripheral side thereof and which is axially linear is formed in the turbine casing, then an insert shroud having a protrusion projected toward the outer peripheral part of the scroll, and which serves as a part of the inner surface of the scroll is attached to the opening, and a support part of an annular nozzle plate which is coupled to the nozzle mount through the intermediary of the nozzle supports is formed in the insert shroud.
  • Fig. 1 is a longitudinal sectional view illustrating an essential part of a variable-throat exhaust turbocharger in a first embodiment of the present invention
  • Fig. 2 is an enlarged view illustrating a Z part in Fig. 1 , in the first embodiment.
  • a turbine casing 10 a scroll 11 formed in the outer peripheral part of the turbine casing, in a spiral shape, a radial flow turbine rotor 12 which is arranged coaxial with a compressor 13 (refer to Fig. 12 ), the turbine rotor 12 having a turbine shaft 12a rotatably journalled to a bearing housing 13 through the intermediary of bearings' 16, and a center axis 100a of the exhaust turbocharger.
  • a plurality of nozzle vanes 2 are provided so as to be arranged in the inner peripheral side of the scroll 11, at equal intervals in the circumferential direction of the turbine.
  • Each of the nozzle vanes 2 is coupled at its end part with a nozzle shaft 02 which is rotatably supported on a nozzle mount 4 secured to the turbine casing 10, and is configured so as to change its blade angle by means of a variable nozzle mechanism 100.
  • the nozzle vanes 2 are each arranged between the nozzle mount 4 and an annular nozzle plate 6 coupled to the nozzle mount 4 through the intermediary of a plurality of nozzle supports 5.
  • the nozzle plate 6 is fitted on an attaching part of the turbine casing 10.
  • a drive ring 3 formed in a disc-like shape, which is rotatably supported in the turbine casing 10 and which is fixed thereto with drive pins 32 at equal intervals in the circumferential direction, and lever plates 1 each having an input side groove which is engaged with the associated drive pin 32 and each having an output side which is secured to the associated nozzle shaft.
  • a link 15 coupled to an actuator (which is not shown) serving as a drive source for the nozzle vanes 2, and a pin 14 coupled to the link 15.
  • the pin 14 is engaged with the drive ring 3 so as to rotate the drive ring 3.
  • variable-throat exhaust turbo-charger incorporating the variable nozzle mechanism having the above-mentioned configuration
  • exhaust gas from an engine (which is not shown) is led into the scroll 11 so as to be swirled along spiral passages in the scroll 11, then flowing into the nozzle vanes 2.
  • the exhaust gas then passes through gaps between the nozzle vanes 2 and is led onto the turbine rotor 12 from the outer peripheral side of the latter. Thereafter, the exhaust gas radially flows toward the center axis of the turbine rotor so as to carry out expansive work for the turbine rotor 12, and then axially flows out, being led into a gas outlet 10b from which it is discharged out from the turbocharger.
  • the blade angle of the nozzle vanes 2 is set by a blade angle control means (which is not shown) so as to regulate the flow rate of the exhaust gas flowing through the nozzle vanes 2 to a predetermined value.
  • the reciprocal displacement of the actuator in response to the blade angle is transmitted to the drive ring 3 through the intermediary of the link 15 and the pin 14, and accordingly, the drive ring 3 is rotated.
  • the rotation of the drive ring 3 causes the drive pins 32 which are secured to the drive ring 3 at equal intervals in the circumferential direction thereof, to rotate the lever plates 1 around the nozzle shafts 02.
  • the rotation of the nozzle shafts 02 turn the nozzle vanes 2 in order to change the blade angle to a value set by the actuator.
  • the present invention concerns a mounting structure of the variable nozzle mechanism 100 in the variable-throat exhaust turbocharger having the above-mentioned configuration.
  • an insert member 20 which is annularly formed is removably attached to the side surface of the bearing housing 13 at the outer periphery of the nozzle mount 4 by means of a plurality of fixing screws (screw caps) 21 which are circumferentially positioned.
  • fixing screws 21 which are circumferentially positioned.
  • the turbine casing 10 is formed therein with an attaching bore 10a having a diameter substantially equal to the outer diameter of the scroll 11, being extended from the scroll 11 to the bearing housing 13.
  • the outer peripheral part of the insert member 20 is fitted in the attaching bore 10a at the inner periphery of the latter in a spigot configuration.
  • the insert member 20 is axially positioned by a stepped part 10c.
  • the inert member 20 is also fixed to the turbine casing 10, being clamped by the outer flange of the bearing housing 13 which is also fastened to the turbine casing 10 by bolt screws 25.
  • the inner peripheral surface of the insert member 20 is fitted on the outer peripheral surface of the nozzle mount 4 in a spigot configuration, and is axially positioned by a stepped part 4c.
  • Nail pins 22 serve as a detent for the nozzle mount 4. These nail pins 22 are press-fitted in the bearing housing 13 through cutouts which are formed in the lever plates 1 at a plurality of circumferential positions, from the fitted part of the nozzle mount 4 in order to serve as a detent for the nozzle mount 4.
  • the nozzle assembly composed of the nozzle vanes 2, the nozzle shafts 02, the nozzle plates 6, the nozzle supports 5, the nozzle mount 4 and the like is fastened to the bearing housing 13 through the intermediary of the insert member 20.
  • the nozzle assembly cannot be affected by a thermal deformation of the turbine casing, and an external force exerted to the turbine casing 10. Accordingly, the nozzle assembly can be prevented from being deformed by these factors. Thereby it is possible to prevent the nozzle assembly from being deformed.
  • nozzle assembly can be firmly fixed to the turbine casing 10 through the intermediary of the insert member 20 without decreasing the fastening force.
  • the nozzle assembly is excited by vibration from the engine side so as to cause the nozzle assembly and the nozzle link mechanism coupled to the former to be worn, resulting in lowering of the function of the variable nozzle mechanism 100, and as a result, the boost pressure (air supply pressure) fed into the engine is greatly decreased.
  • the necessity of a flange for stably fixing nozzle assembly is eliminated from the inner diameter side of the turbine casing 10, and accordingly, the insert member 20 can be fitted in the part where the above-mentioned flange has been provided.
  • the turbine casing itself may have such a configuration that the outer peripheral part of the scroll is opened to the bearing housing 13 in the axial direction, as the turbine casing is viewed as a single component.
  • the configuration of mold cores during casting of the turbine casing can be simplified, that is, the number of mold cores can be reduced, and thereby it is possible to simplify the manufacture of the turbine casing 10. Further, since the turbine casing 10 is usually composed of a casting, as stated above, the presence of burrs in the scroll 11 can be easily checked through the opened part as stated above.
  • the outer peripheral part of the scroll 11 can be opened in the axial direction due to the provision of the insert member 20.
  • the management of the mold core can be facilitated, and accordingly, the number of mold cores can be greatly reduced in comparison with the conventional one.
  • the scroll end (tongue-like part) is restrained by the turbine casing 10 therewithin, and accordingly, a thermal stress applied thereto becomes usually higher.
  • the scroll end is split by the provision of the insert member 20 so as to relief the restraint, and thereby it is possible to prevent the scroll end (tongue-like part) from clacking.
  • Fig. 3 is a longitudinal sectional view illustrating an essential part of an upper half of a second embodiment of the present invention on the turbine side.
  • an integrated nozzle mount type insert member 26 in which the nozzle mount 4 and the insert member 20 that have been explained in the first embodiment are integrally incorporated with each other.
  • the above-mentioned integrated nozzle mount type insert member 26 is fitted at its outer periphery in an attaching bore 10a which is formed in the turbine casing 10, being opened from the scroll 11 toward the bearing housing 13. Further, the integrated nozzle mount type insert member 26 is attached to the bearing housing 13 by means of a plurality of fixing screws (cap screws) 21, as explained in the first embodiment.
  • the above-mentioned integrated nozzle mount type insert member 26 is fixed to the turbine casing 10 being fastened together with the outer peripheral flange of the bearing housing by bolts 25 through the intermediary of a ring lock 27.
  • the configuration of the second embodiment is the same as that of the first embodiment explained with reference to Figs. 1 and 2 , and accordingly, same reference numerals are used to denote same parts to those explained in the first embodiment.
  • Fig. 4 is a view which shows a third embodiment of the present invention, corresponding to Fig. 2 .
  • the insert member 20 is formed in its outer peripheral part with a flange 20s which is clamped between the flanges which are formed at the outer peripheries of the turbine casing 10 and the bearing housing 13, and the thus clamped parts are joined at their outer peripheries together in a fluid tight manner by means of a coupling 28.
  • the configuration of the third embodiment is the same as that of the first embodiment, and accordingly, same reference numerals are use to denote same parts to those explained in the first embodiment.
  • the insert member 20 can be coupled by means of the single coupling 28 alone in a fluid tight manner, the number of component parts can be reduced. Further, in the third embodiment, three components, that is, the insert member 20, the turbine casing 10 and the bearing housing 13 are fastened at their outermost peripheral flanges by the coupling 28, and accordingly, the fastening can be made in a part which is held at a relatively lower temperature. Thus, even though the coupling 28 is made of a relatively inexpensive material, its fastening function can be satisfactory.
  • Fig. 5 is a view which illustrates a fourth embodiment of the present invention, corresponding to Fig. 2 .
  • a snap ring 29 is fitted in a ring groove 30 formed in the side end part of the turbine casing 10 on the bearing housing 13 side.
  • the outer peripheral parts of the bearing housing 13 and the insert member 20 are clamped on the inside of the snap ring 29, that is, the bearing housing 13 and the insert member 20 are pressed and secured against the turbine casing 10 by an inclined side surface 29a of the snap ring 29.
  • the snap ring 29 has the inclined side surface 29a, an axial force is generated by pushing the snap ring 29 into the ring groove 30. By this axial force, the outer peripheral part of the insert member 20 can be firmly held between the bearing housing 13 and the turbine casing 10.
  • the configuration of the fourth embodiment 1 is the same as that of the first embodiment shown in Fig. 1 , and accordingly, same reference numerals are used to denote same parts to those explained in the first embodiment.
  • the snap ring 29 is fitted in the inner diameter side of the attaching bore 10a, 10b in the turbine casing 10, and thereby it is possible to avoid increasing the outer diametrical size of the fastened part of the insert member 20.
  • Fig. 6 is a view illustrating a fifth embodiment of the present invention, corresponding to Fig. 2 .
  • a female thread is formed in the attaching bore 10b (refer to Fig. 1 ) in the turbine casing 10, and a male thread is formed at the outer peripheral part of the insert member 20.
  • the thread portion 30s in which the female thread is meshed with the male thread the outer peripheral part of the insert member is fixed between the turbine casing 10 and the bearing housing 13.
  • the configuration of the fifth embodiment is the same as that of the first embodiment.
  • same reference numerals are used to denote same part to those explained in the first embodiment.
  • the fastened parts of the insert member 20 and the turbine casing 10 can be broadened. Thus, it is possible to stably fasten the insert member 20.
  • the insert member 20 can be readily fastened to the turbine casing 10 by screwing the male thread of the former into the female thread of the latter, no particular attaching screw member is required, and thereby it is possible to miniaturize the insert member 20 itself.
  • Fig. 7 is a view for illustrating a sixth embodiment of the present invention, corresponding to Fig. 2 .
  • the outer peripheral part of the insert member 20 is fixed by welding to the outer peripheral parts of both bearing housing 13 and the turbine casing 10, that is, by a welded part 33.
  • Fig. 8 is a view illustrating a seventh embodiment, corresponding to Fig. 2 .
  • a piston ring 34 for fluid-tight sealing is fitted in a groove formed in the outer peripheral part of the insert member 20, having an outer peripheral surface which is made into slidable contact with the inner peripheral surface of the attaching bore 10b in the turbine casing 10.
  • the piston ring 34 may be fitted in a groove formed in the inner peripheral surface of the attaching bore 10b in the turbine casing 10, having an inner peripheral surface which is made into slidable contact with the outer peripheral surface of the insert member 20.
  • the configuration of the seventh embodiment is the same as that of the first embodiment shown in Fig. 1 , and accordingly, same reference numerals are used to denote same parts to those explained first embodiment.
  • gas leakage through the fitting portion between the insert member 20 and the turbine casing 10 can be surely prevented by the piston ring 34 fitted in the fitting portion.
  • Fig. 9 is an eighth embodiment of the present invention, corresponding to Fig. 2 .
  • a piston ring 35 is fitted in the groove formed in the inner peripheral surface of the insert member 20, and has an inner peripheral surface which is made into slidable contact with the outer peripheral surface of the nozzle mount 4.
  • the piston ring 35 may be fitted in a groove formed in the outer peripheral surface of the nozzle mount 4, and has an outer peripheral surface which is made into slidable contact with the inner peripheral surface of the insert member 20.
  • the configuration of the eighth embodiment is the same as that of the first embodiment, and accordingly, same reference numerals are used to denote same parts to those explained in the first embodiment.
  • gas leakage through the fitting portion between the inner periphery of the insert member 20 and the outer periphery of the nozzle mount 4 can be surely prevented by the piston ring 35.
  • the piston ring 35 does not exert an appreciably large force to its associated component, and thereby it is possible to avoid causing a risk of deformation of the nozzle mount 4 due to the fitting of the piston ring 35, and so forth.
  • Fig. 10 is a longitudinal sectional view illustrating an essential part of a turbine casing in a ninth embodiment of the present invention.
  • the scroll 11 in the turbine casing 10 is formed therein with an opening which is axially straight forward so as to have no protrusion projected from the inner peripheral part to the outer peripheral part of the scroll 11. Further, the opening is attached thereto with an insert shroud 36 having a protrusion 36y projected toward the outer periphery of the scroll 11 and serving as a part of the inner peripheral surface of the scroll 11, and the insert shroud 36 is formed therein with an annular nozzle plate 36z adapted to be coupled to the nozzle mount 4 through the intermediary of the nozzle supports 5.
  • the insert shroud 36 is positioned in the turbine casing 10 at an inner spigot part 36a.
  • insert shroud 36 is located on the inside of the nozzle plates 6, and is fixed to the opening end surface of the turbine casing 10 by means of screw caps 27 provided along the inner periphery.
  • the scroll of the turbine casing 10 made by casting is formed only by casting, and accordingly, should an undercut 11s be formed in the scroll 11 as shown in Fig. 12 , a mold core for the scroll should have a split structure.
  • the scroll 11 is split in parts, and is formed therein with the opening which is axially straightforward, having no protrusion projected from the inner periphery toward the outer periphery of the scroll 11. Further, the opening is provided therein with an insert shroud 36 having the protrusion 36y projected toward the outer peripheral surface of the scroll and serving as a part of the inner surface of the scroll 11.
  • the scroll 11 is axially opened.
  • the undercut part 11s as in the prior art is formed by the insert shroud 36, and thereby it is possible to manufacture the turbine casing 10 from an inexpensive casting having such a configuration as to sustain satisfactory aerodynamic performance and to prevent the mold core for the scroll 11 from being formed in a split structure.
  • the insert shroud 36 is fastened to the turbine casing 10 by the plurality of screw caps 37, the drilling for the fastening is made in a direction the same as those of the other bolt holes and the like in the turbine casing 10. Thus, no planning for changing the direction of the drilling is required, and thereby it is possible to minimize an increase in the working man-hours for the drilling.
  • the fastened part of the insert shroud 36 is faced to the inside of the nozzle plate 6, and accordingly, the screw caps 37 are not exposed to the gas passage, and thereby it is possible to prevent the screw caps 37 from being directly made into contact with the exhaust gas.
  • the screw caps 37 themselves can be made of inexpensive materials. Further, even though the screw caps are loosened, their fastened condition can be maintained since the screw caps 37 are retained by the nozzle plate 6 which is arranged adjacent thereto.
  • insert shroud 36 may be fixed to the turbine casing 10, direct thereto by shrinkage fitting with no use of the plurality of cap screws 37.
  • the spigot parts in both insert shroud 36 and the turbine casing 10 may be made to be longer, and thereby it is possible to ensure stable fastening.
  • Fig. 11 is a view illustrating a tenth embodiment of the present invention, corresponding to Fig. 1 .
  • the tenth embodiment is has a configuration which is in combination of those of the first embodiment shown in Figs. 1 and 2 , and the ninth embodiment shown in Fig. 10 . That is, the above-mentioned insert member 20 which is annularly formed is removably attached to the outer periphery of the nozzle mount 4 by means of a plurality of fixing screws 21. Further, in the tenth embodiment, the insert member 20 is fitted at its outer periphery in the attaching bore 10a which is formed in the turbine casing 10, being opened from the scroll 11 toward the bearing housing 13.
  • the configuration of the first embodiment in which the insert member 20 is attached to the bearing housing 13, is combined with the configuration of the ninth embodiment in which the axially linear opening having no protrusion that is projected from the inner peripheral surface toward the outer peripheral surface of the scroll 11 is formed, and in which the insert shroud 36 having the protrusion 36y projected toward the outer periphery and serving as a part of the inner surface of the scroll 11 is attached to the opening while a support part 36z for the annular nozzle plate 6 that is coupled to the nozzle mount 4 through the intermediary of the nozzle supports 4 is formed in the insert shroud 36.
  • a nozzle assembly including a nozzle mount and nozzle vanes, which has a firm support structure without being affected by a thermal deformation of the turbine casing and an external force exerted to the turbine casing.
  • the configuration of the scroll is simplified so as to be substantially opened, and accordingly, the nozzle assembly can be simply formed.
  • a variable-throat exhaust turbocharger which is manufactured with a reduced number of mold cores for the scroll, that are used during casting of the turbine casing, and thereby it is possible to enhance the productivity of the turbine casing.
  • the annularly formed insert member is removably attached to the outer periphery of the nozzle mount. Further, according to the present invention, the insert member is fitted at its outer periphery in the attaching bore formed in the turbine casing and opened from the scroll toward the bearing housing so as to attach the insert member to the bearing housing, and thereby it is possible to obtain the following technical effects and advantages:
  • the nozzle mount and the insert member are integrally incorporated with each other so as to constitute the integrated nozzle mount type insert member.
  • the integrated nozzle mount type insert member is fitted at its outer periphery in the attaching bore which is formed in the turbine casing, being opened from the scroll toward the bearing housing.
  • the integrated nozzle mount type insert member is attached to the bearing housing by fastening means including attaching screws. With this configuration, the integrated nozzle mount type insert member can be more surely fastened to the bearing housing. Further, the number of component parts can be reduced.
  • the flange part is formed in the outer peripheral part of the insert member. This flange part is clamped between the flange parts formed in the turbine casing and the bearing housing. Further, the thus obtained clamped parts are joined by the coupling in the fluid tight manner. With this configuration, the insert member is coupled in a fluid tight manner with the use of only a single coupling, and thereby it is possible to reduce the number of component parts.
  • the above-mentioned three components that is, the insert member, the turbine casing and the bearing housing, are fastened at their outer peripheral flange parts by the coupling, and accordingly, they can be fastened in a part where the temperature is held at a relatively low value.
  • the coupling which is even made of relatively inexpensive materials can satisfy its fastening function.
  • the snap ring is fitted in the ring groove formed in the bearing side end part of the turbine casing.
  • the outer peripheral parts of the bearing housing and the insert member are clamped on the inside of the snap ring, and accordingly, the bearing housing and the insert member are fixed against the turbine casing by a side surface of the snap ring.
  • the fastening member can be constituted only by the single snap ring itself, and accordingly, the number of component parts can be reduced. Further, since the snap ring is fitted in the inner diameter side of the turbine casing, it is possible to avoid increasing the outer diameter size of the fastened parts.
  • the female thread is formed in the attaching bore in the turbine casing
  • the male thread is formed at the outer periphery of the insert member.
  • the outer peripheral part of the insert member is fixed to the bearing housing and the turbine casing by welding.
  • no particular attaching screw for fastening the insert member to the bearing housing or the turbine casing is required. Thereby it is possible to reduce the number of component parts.
  • the fastening is made by welding, the part around the seal surface can be welded, and thereby it is possible to minimize gas leakage.
  • the piston ring for fluid-tight sealing is fitted between the outer periphery of the insert member and the inner periphery of the attaching bore in the turbine casing.
  • the outer peripheral surface of the piston ring is made into slidable contact with the inner peripheral surface of the attaching bore in the turbine casing.
  • the piston ring for fluid tight sealing is fitted between the inner peripheral surface of the insert member and the outer peripheral surface of the nozzle mount faced to the former. With this configuration, gas leakage from the fitted part between the insert member and the turbine casing can be prevented by the piston ring. Further, since the piston ring does not exert a force which is relatively large, to its associated part, it is not required to take care of a risk of deformation of the nozzle mount due to the fitting of the piston ring.
  • the scroll of the turbine casing formed by casting has been formed of a casting alone.
  • a mold core for the scroll should have a split structure.
  • the opening which has no protrusion projected from the inner periphery toward the outer periphery of the scroll and which is axially linear is formed in the turbine casing.
  • the insert shroud having a protrusion projected toward the outer periphery of the scroll and serving as a part of the inner surface of the scroll is attached to the opening, and the support part of the annular nozzle plate which is coupled to the nozzle mount through the intermediary of the nozzle supports is formed in the insert shroud.
  • the scroll has a partially split structure, and the opening having no protrusion projected from the inner peripheral part toward the outer peripheral part of the scroll and which is axially linear is formed in the scroll.
  • the insert shroud having the protrusion projected toward the outer periphery and serving as a part of the inner surface of the scroll is attached to the opening, and accordingly, the scroll can be axially opened.
  • the undercut part as in the prior art is formed by the insert shroud, and thereby it is possible to manufacture the turbine casing in an inexpensive casting configuration without using a split type mold core for the scroll while a satisfactory aerodynamic performance can be maintained.
  • the insert shroud is fastened to the turbine casing with the use of a plurality of screw members (cap screws or the like), and drilling for the fastening is in a direction which is the same as that of other bolts holes or the like in the turbine casing, and thereby it is possible to eliminate the necessity of such a planning that the direction of the drilling is changed. Thus, it is possible to minimize an increase in the man hours for the drilling.
  • the screw members themselves can be made of inexpensive materials. Further, even though the screw members are loosened, the screw members can be retained by the nozzle plate which is arranged adjacent thereto, and the fastening thereof can be maintained.
  • the insert shroud may be directly fixed to the turbine casing by means of shrinkage fitting or the like without using a plurality of screw members (cap screws) as stated above.
  • the spigot parts of both insert shroud and the turbine casing are made to be longer, and thereby it is possible to obtain stable fastening.
  • the present invention can include a configuration in combination of claim 1 and claim 10. With this configuration, synergetic technical effects and advantages can be obtained from the configuration stated in claim 1 and that stated in claim 10, and thereby it is possible to obtain an attaching structure of the variable nozzle mechanism which is practically excellent, in a variable-throat exhaust turbocharger.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
EP07122041A 2007-02-28 2007-11-30 Montageträger für einen variablen Düsenmechanismus eines Abgasturboladers mit variabler Einschnürung Withdrawn EP1965039A2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2007049700A JP2008215083A (ja) 2007-02-28 2007-02-28 可変容量型排気ターボ過給機における可変ノズル機構部取付構造

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EP1965039A2 true EP1965039A2 (de) 2008-09-03

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EP07122041A Withdrawn EP1965039A2 (de) 2007-02-28 2007-11-30 Montageträger für einen variablen Düsenmechanismus eines Abgasturboladers mit variabler Einschnürung

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US (1) US20080223956A1 (de)
EP (1) EP1965039A2 (de)
JP (1) JP2008215083A (de)
KR (1) KR20080079983A (de)
CN (1) CN101255814A (de)
BR (1) BRPI0704517A (de)

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EP2402579A1 (de) * 2009-02-26 2012-01-04 Mitsubishi Heavy Industries, Ltd. Abgasturbolader mit veränderlicher kapazität
EP2402579A4 (de) * 2009-02-26 2012-08-15 Mitsubishi Heavy Ind Ltd Abgasturbolader mit veränderlicher kapazität
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EP3128152A1 (de) * 2015-08-06 2017-02-08 Honeywell International Inc. Turboladeranordnung
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Also Published As

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CN101255814A (zh) 2008-09-03
KR20080079983A (ko) 2008-09-02
BRPI0704517A (pt) 2008-10-14
JP2008215083A (ja) 2008-09-18
US20080223956A1 (en) 2008-09-18

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