CN107327318B - Turbocharger with tip clearance control using abradable coating - Google Patents
Turbocharger with tip clearance control using abradable coating Download PDFInfo
- Publication number
- CN107327318B CN107327318B CN201710609956.5A CN201710609956A CN107327318B CN 107327318 B CN107327318 B CN 107327318B CN 201710609956 A CN201710609956 A CN 201710609956A CN 107327318 B CN107327318 B CN 107327318B
- Authority
- CN
- China
- Prior art keywords
- abradable coating
- volute
- turbine
- impeller
- clearance
- 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.)
- Active
Links
- 238000000576 coating method Methods 0.000 title claims abstract description 45
- 239000011248 coating agent Substances 0.000 title claims abstract description 43
- 239000002184 metal Substances 0.000 claims description 12
- 230000007704 transition Effects 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 3
- CHJAYYWUZLWNSQ-UHFFFAOYSA-N 1-chloro-1,2,2-trifluoroethene;ethene Chemical group C=C.FC(F)=C(F)Cl CHJAYYWUZLWNSQ-UHFFFAOYSA-N 0.000 claims description 2
- 229920001780 ECTFE Polymers 0.000 claims description 2
- 239000012530 fluid Substances 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 239000000843 powder Substances 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Supercharger (AREA)
Abstract
The turbocharger adopting the abradable coating to control the blade tip clearance comprises an impeller, a turbine, a main shaft, a bearing body, a volute, a back disc and a pressing shell; an abradable coating A is arranged on the inner cavity wall of the volute, and the abradable coating A is arranged in a fit clearance area between the volute and the turbine; an abradable coating B is arranged on the inner cavity wall of the press shell, and the abradable coating B is arranged in the fit clearance area between the press shell and the impeller. According to the invention, abradable coatings with certain thickness are respectively sprayed in clearance areas of the turbine, the volute, the impeller and the pressure shell, a relatively ideal clearance value can be automatically formed by rotating the supercharger without manual control and adjustment, and the automatically formed clearance value is the minimum clearance value which can be controlled between the turbine, the volute, the impeller and the pressure shell on the premise of ensuring the reliability of the supercharger, so that the clearance seal of the blade top of the supercharger is realized, the leakage loss of fluid in the clearance area of the blade top is reduced, and the overall efficiency of the turbocharger is improved.
Description
Technical Field
The invention relates to the technical field of turbocharging, in particular to a turbocharger adopting an abradable coating to control a blade tip clearance.
Background
With the recent trend of upgrading emission standards, engine miniaturization has become a trend, and in order to increase the power up of an engine, the most effective method is to match an exhaust gas turbocharger. The overall performance of the engine is directly affected by the quality of the comprehensive performance of the exhaust gas turbocharger, and particularly, the vehicle engine is more focused on low-speed large torque and good fuel economy performance, so that more strict requirements are put forward for the performance improvement of the turbocharger.
At present, besides the hydrodynamic optimization design of the compressor and the turbine circulation element of the supercharger to improve the performance of the supercharger, the performance of the supercharger can be improved by adjusting the blade top clearance between the impeller and the pressure shell and the blade top clearance between the turbine and the volute, but because the supercharger belongs to a high-speed rotating part, when the supercharger is in a fast running state, the turbine rotating shaft of the supercharger can generate radial and axial runout, the runout amplitude is different from the supercharger, and a determined value is difficult to obtain, so that a design engineer can set clearance values with a certain amount of safety margin between the impeller and the pressure shell and between the turbine and the volute respectively when designing the supercharger clearance, so that the supercharger cannot scratch with the shell due to vibration in the rotation process, but the overall efficiency of the supercharger is reduced due to the clearance margin.
Disclosure of Invention
The invention aims to solve the problem that the reliability of the turbocharger cannot be considered when the overall performance of the turbocharger is improved by simply adopting a blade tip clearance (the blade tip clearance refers to the clearance between the outer edge of an impeller blade and the inner cavity wall of a pressure shell and the clearance between the outer edge of the turbine blade and the inner cavity wall of a volute) when the existing turbocharger is designed.
The technical scheme of the invention is as follows: the turbocharger adopting the abradable coating to control the blade tip clearance comprises an impeller, a turbine, a main shaft, a bearing body, a volute, a back disc and a pressing shell;
the impeller and the turbine are respectively arranged at two ends of the main shaft; the bearing body is arranged in the middle of the main shaft; the volute is arranged at one end of the bearing body, the turbine is accommodated in the inner cavity of the volute, and the back disc is arranged at the other end of the bearing body; the pressing shell is arranged on the back disc and accommodates the impeller in the inner cavity of the back disc;
an abradable coating A is arranged on the inner cavity wall of the volute, and the abradable coating A is arranged in a fit clearance area between the volute and the turbine; an abradable coating B is arranged on the inner cavity wall of the press shell, and the abradable coating B is arranged in the fit clearance area between the press shell and the impeller.
The invention further adopts the technical scheme that: the abradable coating A is connected with the inner cavity wall of the volute through a metal transition layer A; the abradable coating B is directly connected to the inner cavity wall of the press shell.
The invention further adopts the technical scheme that: the thickness ratio of the metal transition layer a to the abradable coating a is 1:2-4;
the invention further adopts the technical scheme that: the abradable coating A and the metal transition layer A jointly fill a fit clearance area of the scroll and the turbine, and the total filling thickness and the fit clearance ratio are 60% -90%; the abradable coating B fills the fit clearance area between the press shell and the impeller, and the filling thickness and the fit clearance ratio are 60% -90%.
Compared with the prior art, the invention has the following advantages:
abradable coatings with certain thickness are respectively sprayed in clearance areas of the turbine, the volute, the impeller and the pressure shell, a relatively ideal clearance value can be automatically formed by rotation of the supercharger without manual control and adjustment, and the automatically formed clearance value is the minimum clearance value which can be controlled between the turbine, the volute, the impeller and the pressure shell on the premise of ensuring the reliability of the supercharger, so that the clearance seal of the blade top of the supercharger is realized, the leakage loss of fluid in the clearance area of the blade top is reduced, and the overall efficiency of the turbocharger is improved.
The invention is further described below with reference to the drawings and examples.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
fig. 2 is an enlarged view of a portion a of fig. 1;
fig. 3 is an enlarged view of a portion B of fig. 1.
Detailed Description
Example 1:
as shown in fig. 1-3, the turbocharger adopting the abradable coating for blade tip clearance control comprises an impeller 1, a turbine 2, a main shaft 3, a bearing body 4, a volute 5, a back plate 6 and a press shell 7.
The impeller 1 and the turbine 2 are respectively installed at both ends of the main shaft 3. The bearing body 4 is installed in the middle of the main shaft 3. A scroll 5 is mounted at one end of the bearing body 4 and accommodates the turbine 2 in its inner cavity, and a back plate 6 is mounted at the other end of the bearing body 4. The press housing 7 is mounted on the back plate 6 and accommodates the impeller 1 in its inner cavity. The inner cavity wall of the volute 5 is provided with an abradable coating A51, and the abradable coating A51 is arranged in the fit clearance area between the volute 5 and the turbine 2. The inner cavity wall of the press shell 7 is provided with an abradable coating B71, and the abradable coating B71 is arranged in the fit clearance area between the press shell 7 and the impeller 1.
Preferably, the abradable coating A51 is connected with the inner cavity wall of the volute 5 through a metal transition layer A52; the arrangement of the metal transition layer A can improve the bonding firmness of the abradable coating A.
Preferably, the thickness ratio of the metal transition layer a52 to the abradable coating a51 is 1:2-4;
preferably, the abradable coating a51 and the abradable coating B71 are both ethylene chlorotrifluoroethylene copolymer, and the hardness of both is lower than that of the turbine 5 and the impeller 1, respectively. The material of the metal transition layer A52 is NiCrAlYSi/h-BN powder.
Preferably, the abradable coating A51 and the metal transition layer A52 jointly fill the fit-gap region of the scroll 5 and the turbine 2, and the total fill thickness (total fill thickness refers to the sum of the thicknesses of the abradable coating A51 and the metal transition layer A52) to fit-gap ratio is 60% -90%; the abradable coating B71 fills the fit clearance area between the press shell 7 and the impeller 1, and the ratio of the filling thickness to the fit clearance is 60% -90%.
Claims (1)
1. The turbocharger adopting the abradable coating to control the blade tip clearance comprises an impeller (1), a turbine (2), a main shaft (3), a bearing body (4), a volute (5), a back disc (6) and a press shell (7);
the impeller (1) and the turbine (2) are respectively arranged at two ends of the main shaft (3); the bearing body (4) is arranged in the middle of the main shaft (3); the volute (5) is arranged at one end of the bearing body (4) and is used for accommodating the turbine (2) in the inner cavity of the bearing body, and the back disc (6) is arranged at the other end of the bearing body (4); the pressing shell (7) is arranged on the back plate (6) and accommodates the impeller (1) in the inner cavity of the back plate;
the method is characterized in that: an abradable coating A (51) is arranged on the inner cavity wall of the volute (5), and the abradable coating A (51) is arranged in a fit clearance area between the volute (5) and the turbine (2); an abradable coating B (71) is arranged on the inner cavity wall of the press shell (7), and the abradable coating B (71) is arranged in the fit clearance area between the press shell (7) and the impeller (1); the abradable coating A (51) and the abradable coating B (71) are made of ethylene chlorotrifluoroethylene copolymer;
the abradable coating A (51) is connected with the inner cavity wall of the volute (5) through a metal transition layer A (52); the abradable coating B (71) is directly connected with the inner cavity wall of the pressing shell (7);
the thickness ratio of the metal transition layer a (52) to the abradable coating a (51) is 1:2-4;
the abradable coating A (51) and the metal transition layer A (52) jointly fill a fit clearance area of the volute (5) and the turbine (2), and the total filling thickness and the fit clearance ratio are 60% -90%; the abradable coating B (71) fills the fit clearance area between the press shell (7) and the impeller (1), and the filling thickness and the fit clearance ratio are 60% -90%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710609956.5A CN107327318B (en) | 2017-07-25 | 2017-07-25 | Turbocharger with tip clearance control using abradable coating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710609956.5A CN107327318B (en) | 2017-07-25 | 2017-07-25 | Turbocharger with tip clearance control using abradable coating |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107327318A CN107327318A (en) | 2017-11-07 |
| CN107327318B true CN107327318B (en) | 2023-09-22 |
Family
ID=60200745
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710609956.5A Active CN107327318B (en) | 2017-07-25 | 2017-07-25 | Turbocharger with tip clearance control using abradable coating |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107327318B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108661949B (en) * | 2018-08-16 | 2025-01-17 | 湖南天雁机械有限责任公司 | Abradable coated turbocharger |
| CN114992163A (en) * | 2022-06-09 | 2022-09-02 | 一汽解放汽车有限公司 | Gas compressor and turbocharger |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102135020A (en) * | 2010-01-25 | 2011-07-27 | 株式会社日立制作所 | Gas turbine shroud with ceramic abradable coatings |
| CN102207008A (en) * | 2010-03-31 | 2011-10-05 | 芜湖杰锋汽车动力系统有限公司 | Turbocharger and method for improving boost efficiency thereof |
| WO2012104132A1 (en) * | 2011-02-01 | 2012-08-09 | Continental Automotive Gmbh | Turbine of an exhaust-gas turbocharger, and exhaust-gas turbocharger having a turbine of this type for a motor vehicle |
| CN104220723A (en) * | 2012-04-29 | 2014-12-17 | 博格华纳公司 | VTG turbocharger vane pack assembly with abradable coating |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107250552B (en) * | 2015-02-27 | 2020-02-14 | 三菱重工发动机和增压器株式会社 | Method for manufacturing supercharger |
-
2017
- 2017-07-25 CN CN201710609956.5A patent/CN107327318B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102135020A (en) * | 2010-01-25 | 2011-07-27 | 株式会社日立制作所 | Gas turbine shroud with ceramic abradable coatings |
| CN102207008A (en) * | 2010-03-31 | 2011-10-05 | 芜湖杰锋汽车动力系统有限公司 | Turbocharger and method for improving boost efficiency thereof |
| WO2012104132A1 (en) * | 2011-02-01 | 2012-08-09 | Continental Automotive Gmbh | Turbine of an exhaust-gas turbocharger, and exhaust-gas turbocharger having a turbine of this type for a motor vehicle |
| CN104220723A (en) * | 2012-04-29 | 2014-12-17 | 博格华纳公司 | VTG turbocharger vane pack assembly with abradable coating |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107327318A (en) | 2017-11-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107327318B (en) | Turbocharger with tip clearance control using abradable coating | |
| CN100559019C (en) | A core rotor device of an exhaust gas turbocharger | |
| CN209212316U (en) | Flap component, turbine and exhaust-driven turbo-charger exhaust-gas turbo charger for turbine | |
| CN110821712A (en) | A connection structure of high temperature gas outlet end of low temperature turbo pump | |
| CN204371494U (en) | Micro Turbine Jet Engine axial flow turbine dish axle | |
| CN108661949B (en) | Abradable coated turbocharger | |
| CN104747240A (en) | Rotor system of small turbocharger | |
| CN110410154A (en) | Thrust structure of turbocharger and turbocharger thereof | |
| CN110247503B (en) | Sealing structure for electronic actuator | |
| CN203756315U (en) | Small-sized gasoline engine turbine booster | |
| CN207245765U (en) | The turbocharger of blade tip clearance control is carried out using abradable coating | |
| CN103953431A (en) | Small gasoline engine turbosuperchager | |
| CN208578590U (en) | The packing of steam turbine combines | |
| CN201944011U (en) | Water pump assembly | |
| CN205445687U (en) | Turbine structure of turbine disc rigidity self enhancement | |
| CN202047870U (en) | Improved rotor sealing structure of improved 300 MW steam turbine | |
| CN219733476U (en) | Nozzle ring assembly with improved mounting structure | |
| CN219733709U (en) | Shaft seal structure for turbocharger | |
| CN206668622U (en) | Has the water pump structure of Unitary Impeller pump shaft | |
| CN201908692U (en) | Novel turbine for pressurizer of diesel engine | |
| CN217652785U (en) | Efficient stainless steel turbine assembly | |
| CN216157761U (en) | Integrated air release valve | |
| CN211449168U (en) | Whole ring type metal inlaid floating ring seal with whole wave spring | |
| CN216406964U (en) | Air bleed valve component for turbocharger | |
| CN216895014U (en) | Shaft assembly for use in a turbocharger |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |