CN109098780B - Gas exhaust casing of turbocharger - Google Patents
Gas exhaust casing of turbocharger Download PDFInfo
- Publication number
- CN109098780B CN109098780B CN201810510660.2A CN201810510660A CN109098780B CN 109098780 B CN109098780 B CN 109098780B CN 201810510660 A CN201810510660 A CN 201810510660A CN 109098780 B CN109098780 B CN 109098780B
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- China
- Prior art keywords
- air inlet
- exhaust
- shell
- cover
- outer cover
- Prior art date
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- 239000007789 gas Substances 0.000 claims abstract description 44
- 238000007789 sealing Methods 0.000 claims abstract description 12
- 239000002912 waste gas Substances 0.000 claims abstract description 3
- 238000005266 casting Methods 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 2
- 230000008646 thermal stress Effects 0.000 abstract description 10
- 239000002737 fuel gas Substances 0.000 abstract description 5
- 230000035882 stress Effects 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 230000001788 irregular Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Classifications
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a turbocharger fuel gas waste gas intake and exhaust shell, which comprises an intake air guide inner cover, a nozzle ring, an exhaust outer meridian cover, an exhaust inner meridian cover, an intake outer shell, an exhaust shell and an intake air guide outer cover, wherein the intake air guide outer cover is arranged in the intake air outer shell, the exhaust end of the intake air guide outer cover is fixed on the exhaust outer meridian cover, the exhaust shell and the exhaust outer meridian cover are fixed in a sealing way, the intake outer shell is fixed on the exhaust shell in a sealing way, and the intake air guide inner cover and the nozzle ring are mutually fixed. When the air inlet outer shell is deformed and stressed, the invention can release thermal deformation and thermal stress generated by the connection of the turbine air inlet outer shell and the engine gas exhaust pipeline under the high-temperature working condition, and solves the problems of the joint grinding of the turbine blade and the exhaust outer meridian shell, the loosening or fracture of the connecting bolt of the air inlet shell and the exhaust shell, the crack of the exhaust shell or the air inlet shell, the deformation of the shell flange and the like under the working condition of the turbine inlet high-temperature gas exhaust.
Description
Technical Field
The invention relates to the technical field of turbochargers, in particular to a gas exhaust inlet and outlet shell of a turbocharger.
Background
Turbochargers are machines that convert engine gas exhaust heat energy into mechanical energy to increase engine intake pressure and density and thereby increase engine power. The gas exhaust inlet and outlet shell of the turbocharger is connected with a gas exhaust pipeline of the engine, and bears the vibration load and the thermal stress load of the engine in operation. Particularly, due to the limitation of engine space arrangement, the turbocharger turbine air inlet shell and an engine gas exhaust pipeline are spatially staggered, and when the pipeline connection with a bent shape is needed, the turbine air inlet shell bears complex and changeable sizes and directions of vibration and thermal stress loads, so that the problems of shell deformation, cracks, looseness of connecting bolts or breakage and the like occur after the turbocharger gas exhaust air inlet and outlet shell works for a certain time, and the safe service life of the supercharger is reduced. In recent years, as the emission index of the engine and the strengthening level of the diesel engine are increased, the temperature of the exhaust gas at the inlet of the turbine is also increased, and the thermal stress load of the gas inlet and outlet shells of the supercharger gas exhaust is also increased.
As shown in fig. 1 (in the drawing, 1 is an exhaust inner meridian housing, 2 is an exhaust outer meridian housing, 3 is a second connecting bolt, 4 is an exhaust housing, 5 is a turbine disc, 6 is a first connecting bolt, 7 is a nozzle ring, 8 is an air inlet outer housing, and 9 is a pin structure), in the prior art, the turbine air inlet inner meridian housing and the air inlet outer housing 8 are connected into an integral structure by ribs, the nozzle ring 7 is positioned in an axial space formed by the air inlet outer housing 8 and the exhaust outer meridian housing 2, a certain gap exists between the exhaust inner meridian housing 1 and the nozzle ring 7 in a cold state, the nozzle ring 7 is in an axial compression state due to expansion in a hot state, and the pin structure 9 exists between the nozzle ring 7 and the air inlet housing. The casing of the turbine disc 5 in the radial direction is formed of the exhaust outer meridian casing 2 and the turbine casing into a two-wall one-chamber structure, which has a containment safety function of preventing broken fragments (blocks) from breaking through the casing and encasing the fragments (blocks) in the casing when the turbine disc 5 is accidentally damaged. When the existing structure is used for designing the turbine air inlet shell into a space bending shape or using the space bending shape pipeline to be in transitional connection when the space dislocation exists between the turbine air inlet shell and the engine gas exhaust pipeline of the supercharger, the faults such as loosening or fracture of the air inlet shell and the first connecting bolt 6 of the exhaust shell, crack of the exhaust shell 4 or the air inlet shell, deformation of the air outlet shell or the flange of the air inlet shell, partial reduction of the clearance between the top of the turbine disc 5 and the inner wall of the exhaust outer meridian shell 2 caused by uneven circumferential deformation of the exhaust outer meridian shell 2 or partial connection and grinding of the supercharger can occur under the working condition of high-temperature gas exhaust at the inlet of the turbine.
Disclosure of Invention
The invention aims at the proposal of the problems, and researches and designs a turbocharger gas exhaust gas inlet and outlet shell. The invention adopts the following technical means:
The utility model provides a turbocharger gas waste gas advances exhaust casing, includes air intake kuppe, nozzle ring, exhaust outer meridian housing, exhaust inner meridian housing, air intake shell body and exhaust casing, still includes air intake water conservancy diversion dustcoat, the air intake water conservancy diversion dustcoat sets up in the air intake shell body, and the exhaust end of air intake water conservancy diversion dustcoat is fixed on the exhaust outer meridian housing, seal fixation between exhaust casing and the exhaust outer meridian housing, the air intake shell body seal is fixed on the exhaust casing, air intake water conservancy diversion inner cover and nozzle ring are fixed each other.
Further, the air inlet guide inner cover is connected with the air inlet guide outer cover through ribs.
Further, a flange is arranged on the outer portion of the air inlet outer shell, and the flange is fixed on the air outlet shell through a pressing piece and a bolt.
Further, a high-temperature elastic sealing gasket is arranged between the exhaust shell and the exhaust outer meridian housing, and a high-temperature elastic sealing gasket is arranged between the flange and the exhaust shell.
Further, the air inlet guide outer cover is provided with a groove for accommodating the outer edge of the nozzle ring, and the outer edge of the nozzle ring is matched with the groove in size and has a gap, so that the nozzle ring is in a free state in a certain range in the axial direction and the radial direction.
Further, the air inlet outer shell is of a casting structure, and the wall thickness of the air inlet outer shell is 7-14 mm.
Further, a first gap is formed between the air inlet outer shell and the air outlet shell, and the width of the first gap is more than 1 mm.
Further, the air inlet outer shell is of a structure which is non-rotationally symmetrical relative to the central axis of the nozzle ring, and the air inlet guide inner cover and the air inlet guide outer cover are also of corresponding non-rotationally symmetrical structures. That is, the air inlet outer shell, the air inlet guide inner cover and the air inlet guide outer cover cannot coincide with the initial positions when rotating for 0-360 degrees around the central axis of the nozzle ring.
Further, a positioning pin is arranged between the air inlet outer shell and the air outlet shell, a positioning pin is arranged between the air inlet guide inner shell and the nozzle ring, and a positioning pin is also arranged between the air inlet guide outer shell and the air outlet outer meridian shell. The non-rotationally symmetrical shape of the air inlet outer shell, the air inlet guide inner cover and the air inlet guide outer cover are ensured to be installed correctly in the circumferential direction.
Further, an inner concave surface corresponding to the air inlet guide outer cover is arranged on the inner wall of the air inlet outer shell, the air inlet guide outer cover is arranged at the inner concave surface, so that an air inlet guide surface is formed by the inner wall of the air inlet guide outer cover and the inner wall of the air inlet outer shell, a cavity is formed between the air inlet outer shell and the air inlet guide outer cover, a second gap is arranged between the edge of the air inlet end of the air inlet guide outer cover and the edge of the inner concave surface, and the width of the second gap is 1-4 mm.
Compared with the prior art, the turbocharger gas exhaust gas inlet and outlet shell has the following advantages:
1. The deformation and stress of the air inlet outer shell are not influenced or transferred to the air inlet guide outer shell and the air outlet outer meridian shell, so that the thermal deformation and thermal stress generated by the connection of the turbine air inlet outer shell and an engine gas exhaust pipeline in a high-temperature working state can be released, the engine vibration load transferred to a supercharger is reduced, and the problems of loosening or fracture of a connecting bolt of the air inlet shell and the air outlet shell, cracking of the air outlet shell or the air inlet shell, deformation of a flange of the air outlet shell or the air inlet shell and the like under the working condition of the turbine inlet high-temperature gas exhaust are solved;
2. The radial and axial directions of the nozzle ring have a certain degree of freedom, a certain expansion space is provided during thermal expansion, thermal stress is reduced, and the problems that under the high-temperature working condition that the space dislocation exists between the turbine air inlet shell of the supercharger and the gas exhaust pipeline of the engine and the connection of a pipeline with a bent shape is needed, the gaps between the top of a turbine disc and the inner wall of the exhaust outer meridian shell are locally reduced or the supercharger is damaged due to local grinding due to uneven circumferential deformation of the exhaust outer meridian shell when the left-right or up-down asymmetric thermal stress load exists are solved;
3. The free end of the air inlet outer shell extends into a cavity formed by the air outlet shell and the air outlet outer meridian housing, and a layer of containing explosion-proof buffer shell structure is added to enhance the explosion-proof impact resistance of the shell;
4. the invention is especially suitable for the design of the turbine air inlet shell of the axial-flow turbocharger with space dislocation and space distortion, and the air inlet shell structure of the design is suitable for the free expansion of the air inlet shell with space distortion in all directions, reduces the thermal stress, is more beneficial to the operation of the turbine shell which is subjected to high temperature and low temperature for multiple times, and achieves the purposes of simple and applicable structure and long service life.
Drawings
Fig. 1 is a schematic diagram of a prior art turbocharger gas exhaust inlet and outlet housing.
Fig. 2 is a schematic structural view of an embodiment of the present invention.
Detailed Description
As shown in fig. 2, the gas exhaust casing of the turbocharger comprises an air inlet guide inner casing 1, a nozzle ring 3, an exhaust outer meridian casing 5, an exhaust inner meridian casing 6, an air inlet outer casing 17 and an exhaust casing 8, and further comprises an air inlet guide outer casing 15, wherein the air inlet guide outer casing 15 is arranged in the air inlet outer casing 17, the exhaust end of the air inlet guide outer casing 15 is fixed on the exhaust outer meridian casing 5 through a fixing bolt 13, the air outlet casing 8 and the exhaust outer meridian casing 5 are fixed in a sealing manner, the air inlet outer casing 17 is fixed on the air outlet casing 8 in a sealing manner, the air inlet guide inner casing 1 and the nozzle ring 3 are fixed with each other, and in the embodiment, the nozzle ring 3 is fixed at the joint of the air inlet guide outer casing 15 and the exhaust meridian casing 5. The air inlet guide inner cover 1 is connected with the air inlet guide outer cover 15 through ribs 14. And no direct connection structure is arranged between the air inlet shell 17 and the air inlet guide shell 15, and the two parts are completely separated. When there is a spatial misalignment between the turbocharger turbine intake housing 17 and the engine gas exhaust line, the turbine intake housing needs to be designed in a spatial curved shape or in transitional connection with the spatial curved shape line, and when the intake housing 17 is connected with the engine gas exhaust line or in transitional connection with the spatial curved shape line, the intake housing assumes spatial irregular deformation or stress. Deformation and stress of the air inlet shell 17 cannot be transmitted to the air inlet guide sleeve 15. Therefore, the air inlet diversion outer cover 15 and the exhaust outer meridian cover 5 are not subjected to irregular deformation and stress in space during operation, and the gap between the top of the turbine disc 4 and the inner wall of the exhaust outer meridian cover 5 can be controlled in a reasonable range, so that the supercharger can safely operate.
The outside of the intake housing 17 is provided with a flange which is fastened to the exhaust housing 8 by means of the hold-down 9 and the bolts 10. A first high-temperature elastic sealing gasket 7 is arranged between the exhaust shell 8 and the exhaust outer meridian housing 5, and a second high-temperature elastic sealing gasket 12 is arranged between the flange and the exhaust shell 8.
The air inlet guide outer cover 15 is provided with a groove for accommodating the outer edge of the nozzle ring 3, and the size of the outer diameter edge of the nozzle ring 3 is matched with the groove and has a gap, so that the nozzle ring 3 is in a free state in a certain range in the axial direction and the radial direction, and fatigue damage such as cracks and the like caused by thermal stress concentration generated by expansion resistance is prevented.
The air inlet outer shell 17 is of a casting structure, the wall thickness of the air inlet outer shell 17 is 7-14 mm, and certain rigidity is ensured so as to ensure the shape of a runner.
A first gap 3c is provided between the intake housing 17 and the exhaust housing 8, and the width of the first gap 3c is 1mm or more.
The spigot of the exhaust outer meridian housing 5 is positioned on the exhaust shell 8; the integral combined spigot of the air inlet guide outer cover 15, the air inlet guide inner cover 1 and the nozzle ring 3 is positioned on the exhaust outer meridian cover 5 so as to ensure the radial dimension of the air flow passage.
This embodiment is particularly suitable for the case of irregular air inlets, the air inlet outer shell 17 is of a non-rotationally symmetrical structure relative to the central axis of the nozzle ring 3, and the air inlet guide inner cover 1 and the air inlet guide outer cover 15 are also of corresponding non-rotationally symmetrical structures. That is, the air inlet outer casing 17, the air inlet guide inner casing 1 and the air inlet guide outer casing 15 cannot coincide with the respective initial positions when rotating about the central axis of the nozzle ring 3 by 0 to 360 degrees, and in practice, it is a common case that the air inlet of the air inlet outer casing 17 is of a bent pipe structure. Of course, this embodiment is also applicable to the case of circumferential symmetry of a conventional air intake outer casing, and the air intake casing of this embodiment can freely expand no matter the air intake outer casing is circumferentially symmetric or asymmetric, and has the effect of reducing thermal stress, and is not limited by the symmetry of the casing.
A first positioning pin 11 is arranged between the air inlet outer shell 17 and the air outlet shell 8, a second positioning pin 2 is arranged between the air inlet guide inner shell 1 and the nozzle ring 3, and a third positioning pin (not shown in the figure) is arranged between the air inlet guide outer shell 15 and the air outlet outer meridian shell 5. The non-rotationally symmetrical shape of the air inlet outer shell 17, the air inlet guide inner cover 1 and the air inlet guide outer cover 15 are ensured to be installed correctly in the circumferential direction.
The inner wall of the air inlet shell 17 is provided with an inner concave surface 1c corresponding to the air inlet guide shell, the air inlet guide shell 15 is arranged at the inner concave surface 1c, so that the inner wall of the air inlet guide shell 15 and the inner wall of the part of the air inlet shell 17 without the inner concave surface jointly form an air inlet guide surface, a cavity 2c is formed between the outer wall of the air inlet guide shell 15 and the inner concave surface 1c of the air inlet shell 17, a second gap 16 is arranged between the edge of the air inlet end of the air inlet guide shell 15 and the edge of the inner concave surface 1c, and the width d of the second gap 16 is 1 mm-4 mm. In operation, part of the fuel gas flows into the cavity 2c from the second gap 16, and after the cavity 2c is filled with the fuel gas, no more redundant fuel gas flows into the cavity 2c, and meanwhile, the fuel gas in the cavity 2c does not leak, so that the gas flow is not influenced. The concave surface 1c is formed according to the outer profile offset of the intake air guide cover 15 or other methods, and its shape is not particularly limited.
The molded lines 1a, 2a, 1b, 2b are aerodynamically optimized molded lines. The specific values of the molded lines 1a, 2a, 1b, 2b are different according to the space size.
The above examples are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art to the technical solution of the present invention should fall within the scope of protection defined by the claims of the present invention without departing from the spirit of the design of the present invention.
Claims (9)
1. The utility model provides a turbocharger gas waste gas advances exhaust casing, includes air inlet kuppe, nozzle collar, exhaust outer meridian housing, exhaust inner meridian housing, air inlet outer casing and exhaust casing, its characterized in that: the air inlet guide outer cover is arranged in the air inlet outer cover, the exhaust end of the air inlet guide outer cover is fixed on the exhaust outer meridian cover, the exhaust shell and the exhaust outer meridian cover are fixed in a sealing mode, the air inlet outer cover is fixed on the exhaust shell in a sealing mode, the air inlet guide inner cover and the nozzle ring are fixed with each other, a flange is arranged outside the air inlet outer cover and fixed on the air outlet shell through a pressing piece and a bolt, a first gap exists between the air inlet outer cover and the air outlet shell, an inner concave face corresponding to the air inlet guide outer cover is arranged on the inner wall of the air inlet outer cover, the air inlet guide outer cover is arranged at the inner concave face, the air inlet guide surface is formed between the inner wall of the air inlet guide outer cover and the inner wall of the air inlet outer cover, a cavity is formed between the air inlet outer cover and the air inlet guide outer cover, and a second gap is formed between the edge of the air inlet end of the air inlet guide outer cover and the edge of the inner concave face.
2. The turbocharger gas exhaust gas intake and exhaust housing of claim 1, wherein: the air inlet guide inner cover is connected with the air inlet guide outer cover through ribs.
3. The turbocharger gas exhaust gas intake and exhaust housing of claim 2, wherein: the high-temperature elastic sealing gasket is arranged between the exhaust shell and the exhaust outer meridian housing, and the high-temperature elastic sealing gasket is arranged between the flange and the exhaust shell.
4. The turbocharger gas exhaust gas intake and exhaust housing of claim 1, wherein: the air inlet guide outer cover is provided with a groove for accommodating the outer edge of the nozzle ring, and the outer edge of the nozzle ring is matched with the groove in size and has a gap, so that the nozzle ring is in a free state in a certain range in the axial direction and the radial direction.
5. The turbocharger gas exhaust gas intake and exhaust housing of claim 1, wherein: the air inlet outer shell is of a casting structure, and the wall thickness of the air inlet outer shell is 7-14 mm.
6. The turbocharger gas exhaust gas intake and exhaust housing of claim 1, wherein: the width of the first gap is more than 1 mm.
7. The turbocharger gas exhaust gas intake and exhaust housing of claim 1, wherein: the air inlet shell body is of a structure which is non-rotationally symmetrical relative to the central axis of the nozzle ring, and the air inlet guide inner cover and the air inlet guide outer cover are also of corresponding non-rotationally symmetrical structures.
8. The turbocharger gas exhaust gas inlet and outlet housing of claim 7, wherein: the air inlet outer shell and the exhaust shell are provided with positioning pins, the air inlet guide inner cover and the nozzle ring are provided with positioning pins, and the air inlet guide outer cover and the exhaust outer meridian cover are also provided with positioning pins.
9. The turbocharger gas exhaust gas intake and exhaust housing according to any one of claims 1 to 8, wherein: the width of the second gap is 1 mm-4 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810510660.2A CN109098780B (en) | 2018-05-24 | 2018-05-24 | Gas exhaust casing of turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810510660.2A CN109098780B (en) | 2018-05-24 | 2018-05-24 | Gas exhaust casing of turbocharger |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109098780A CN109098780A (en) | 2018-12-28 |
| CN109098780B true CN109098780B (en) | 2024-05-14 |
Family
ID=64796505
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810510660.2A Active CN109098780B (en) | 2018-05-24 | 2018-05-24 | Gas exhaust casing of turbocharger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109098780B (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1172893A (en) * | 1996-05-08 | 1998-02-11 | 亚瑞亚·勃朗勃威力有限公司 | Exhaust turbine of exhaust turbine supercharger |
| US6354815B1 (en) * | 2000-05-10 | 2002-03-12 | General Motors Corporation | Turbocharger thermal isolation connection |
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| DE29624508U1 (en) * | 1996-05-08 | 2004-12-16 | Abb Turbo Systems Ag | Axial turbine of exhaust turbo-supercharger - has burst prevention ring as integral radially extending part of wall on gas intake side of gas exit casing |
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| CN103850732A (en) * | 2009-02-18 | 2014-06-11 | 三菱重工业株式会社 | Axial-flow turbine and operation method thereof |
| EP2781695A1 (en) * | 2013-03-22 | 2014-09-24 | ABB Turbo Systems AG | Nozzle for an exhaust gas turbine |
| CN105980685A (en) * | 2014-06-25 | 2016-09-28 | 三菱重工业株式会社 | Labyrinth seal device for axial-flow turbine and exhaust gas turbocharger equipped with same |
| CN208380635U (en) * | 2018-05-24 | 2019-01-15 | 中车大连机车研究所有限公司 | A kind of turbocharger combustion gas exhaust gas intake and exhaust shell |
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| DE10016082A1 (en) * | 2000-03-31 | 2001-10-04 | Alstom Power Nv | Turbine housing for an axially flow-through gas turbine |
| US7229247B2 (en) * | 2004-08-27 | 2007-06-12 | Pratt & Whitney Canada Corp. | Duct with integrated baffle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1172893A (en) * | 1996-05-08 | 1998-02-11 | 亚瑞亚·勃朗勃威力有限公司 | Exhaust turbine of exhaust turbine supercharger |
| DE29624508U1 (en) * | 1996-05-08 | 2004-12-16 | Abb Turbo Systems Ag | Axial turbine of exhaust turbo-supercharger - has burst prevention ring as integral radially extending part of wall on gas intake side of gas exit casing |
| US6354815B1 (en) * | 2000-05-10 | 2002-03-12 | General Motors Corporation | Turbocharger thermal isolation connection |
| CN1454285A (en) * | 2000-11-30 | 2003-11-05 | 霍尼韦尔加勒特股份有限公司 | Variable geometry turbocharger with sliding piston |
| WO2006005199A1 (en) * | 2004-07-15 | 2006-01-19 | Abb Turbo Systems Ag | Exhaust-gas turbine for a turbocharger comprising an air-cooled turbine disc |
| CN101506476A (en) * | 2006-08-24 | 2009-08-12 | Abb涡轮系统有限公司 | Turbine housing |
| CN103850732A (en) * | 2009-02-18 | 2014-06-11 | 三菱重工业株式会社 | Axial-flow turbine and operation method thereof |
| CN102639838A (en) * | 2009-12-17 | 2012-08-15 | 株式会社Ihi | Turbocharger |
| CN103189614A (en) * | 2011-11-02 | 2013-07-03 | 丰田自动车株式会社 | Turbine housing and exhaust turbine supercharger |
| EP2781695A1 (en) * | 2013-03-22 | 2014-09-24 | ABB Turbo Systems AG | Nozzle for an exhaust gas turbine |
| CN105980685A (en) * | 2014-06-25 | 2016-09-28 | 三菱重工业株式会社 | Labyrinth seal device for axial-flow turbine and exhaust gas turbocharger equipped with same |
| CN208380635U (en) * | 2018-05-24 | 2019-01-15 | 中车大连机车研究所有限公司 | A kind of turbocharger combustion gas exhaust gas intake and exhaust shell |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109098780A (en) | 2018-12-28 |
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