CN107327318A - The turbocharger of blade tip clearance control is carried out using abradable coating - Google Patents
The turbocharger of blade tip clearance control is carried out using abradable coating Download PDFInfo
- Publication number
- CN107327318A CN107327318A CN201710609956.5A CN201710609956A CN107327318A CN 107327318 A CN107327318 A CN 107327318A CN 201710609956 A CN201710609956 A CN 201710609956A CN 107327318 A CN107327318 A CN 107327318A
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- CN
- China
- Prior art keywords
- abradable coating
- volute
- turbine
- impeller
- pressure shell
- 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.)
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Classifications
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- 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
Abstract
The turbocharger of blade tip clearance control, including impeller, turbine, main shaft, bearing body, volute, back of the body disk and pressure shell are carried out using abradable coating；Volute internal chamber wall is provided with abradable coating A, and abradable coating A is located in the fit clearance region of volute and turbine；Pressure shell internal chamber wall is provided with abradable coating B, and abradable coating B is located in the fit clearance region of pressure shell and impeller.The present invention sprays certain thickness abradability coating respectively in turbine and volute, impeller and pressure shell gap area, booster rotation can automatically form a more satisfactory gap width, without being manually controlled regulation, the gap width automatically formed is ensures the minimum clearance value that can be controlled between turbine and volute, impeller and pressure shell under the premise of booster reliability, so as to realize that booster blade tip clearance is sealed, the leakage loss of fluid in blade tip clearance region is reduced, turbocharger whole efficiency is improved.
Description
Technical field
The present invention relates to turbocharging technology field, particularly a kind of use abradable coating carries out blade tip clearance control
Turbocharger.
Background technology
It is Engine Downsizing to turn into a kind of development trend recently as discharge standard upgrading, in order to improve engine
Power per liter, maximally efficient method be matching exhaust-driven turbo-charger exhaust-gas turbo charger.The quality of exhaust-driven turbo-charger exhaust-gas turbo charger combination property is directly
It has impact on the overall performance of engine, especially vehicular engine and more focus on low-speed big and good fuel economy
Can, this proposes more strict demand to booster performance.
At present, increasing is lifted except carrying out hydrodynamics optimization design to supercharger air compressor and turbine flow-through element
Outside depressor performance, can also by adjust the blade tip clearance between the blade tip clearance between impeller and pressure shell, turbine and volute come
Booster performance is lifted, but is due to that booster belongs to high speed revolving part, when booster is in fast turn-around state, booster
Turbine shaft can produce radial and axial bounce, and the amplitude of the bounce is different because of booster, it is difficult to obtain the value of determination, therefore
Design engineer can set a certain amount of between impeller and pressure shell, between turbine and volute respectively when designing booster gap
The gap width of margin of safety, to ensure that booster with housing will not occur to scrape so as to occurring in rotary course because of vibration
Reliability failure, but due to the presence of gap nargin, reduce the whole efficiency of booster.
The content of the invention
The purpose of the present invention is that when overcoming existing turbocharger design, simple use reduces blade tip clearance (between leaf top
Between gap is referred between the gap between impeller blade outer rim and pressure shell internal chamber wall, and turbo blade outer rim and volute internal chamber wall
Gap) lifting booster overall performance when the problem of can not take into account booster reliability.
The technical scheme is that：The turbocharger of blade tip clearance control, including leaf are carried out using abradable coating
Wheel, turbine, main shaft, bearing body, volute, back of the body disk and pressure shell；
Impeller and turbine are separately mounted to the two ends of main shaft；Bearing body is arranged in the middle part of main shaft；Volute is arranged on the one of bearing body
Hold and turbine is accommodated within chamber, back of the body disk is arranged on the other end of bearing body；Pressure shell is arranged on back of the body disk and holds impeller
It is contained in its inner chamber；
Volute internal chamber wall is provided with abradable coating A, and abradable coating A is located in the fit clearance region of volute and turbine；Pressure
Shell internal chamber wall is provided with abradable coating B, and abradable coating B is located in the fit clearance region of pressure shell and impeller.
Further technical scheme is the present invention：Connected between abradable coating A and volute internal chamber wall by intermediate metal A
Connect；Abradable coating B is directly connected with pressure shell internal chamber wall.
Further technical scheme is the present invention：Intermediate metal A and abradable coating A thickness ratio is 1：2-4；
Further technical scheme of the invention is：Abradable coating A and intermediate metal A fills matching somebody with somebody for volute and turbine jointly
Gap area is closed, total filling thickness is 60% ~ 90% with fit clearance ratio；Abradable coating B is filled between the cooperation of pressure shell and impeller
Gap region, filling thickness is 60% ~ 90% with fit clearance ratio.
The present invention has the following advantages that compared with prior art：
Spray certain thickness abradability coating, booster rotation respectively in turbine and volute, impeller and pressure shell gap area
The change of team automatically forms a more satisfactory gap width, without being manually controlled regulation, the gap width automatically formed
To ensure the minimum clearance value that can be controlled between turbine and volute, impeller and pressure shell under the premise of booster reliability, so that real
The leakage loss of fluid, improves turbocharger whole efficiency in existing booster blade tip clearance sealing, reduction blade tip clearance region.
Below in conjunction with figure, the invention will be further described with embodiment.
Brief description of the drawings
Fig. 1 is structural representation of the invention；
Fig. 2 is Fig. 1 A portions enlarged drawing；
Fig. 3 is Fig. 1 B portions enlarged drawing.
Embodiment
Embodiment 1：
As Figure 1-3, the turbocharger of blade tip clearance control, including impeller 1, turbine 2, master are carried out using abradable coating
Axle 3, bearing body 4, volute 5, back of the body disk 6, pressure shell 7.
Impeller 1 and turbine 2 are separately mounted to the two ends of main shaft 3.Bearing body 4 is arranged on the middle part of main shaft 3.Volute 5 is arranged on
Turbine 2 is simultaneously accommodated within chamber by one end of bearing body 4, and back of the body disk 6 is arranged on the other end of bearing body 4.Pressure shell 7 is arranged on the back of the body
It is accommodated within disk 6 and by impeller 1 in chamber.The internal chamber wall of volute 5 is provided with abradable coating A51, and abradable coating A51 is located at
In the fit clearance region of volute 5 and turbine 2.The internal chamber wall of pressure shell 7 is provided with abradable coating B71, and abradable coating B71 is located at
In the fit clearance region of pressure shell 7 and impeller 1.
It is preferred that, connected between abradable coating A51 and the internal chamber wall of volute 5 by intermediate metal A52；Intermediate metal A
Setting can lift abradable coating A bonding firmness.
It is preferred that, intermediate metal A52 and abradable coating A51 thickness ratio is 1：2-4；
It is preferred that, abradable coating A51 and abradable coating B71 material is ethene chlorotrifluoroethylene, and both is hard
Degree is respectively lower than the hardness of turbine 5 and impeller 1.Intermediate metal A52 materials are NiCrAlYSi/h-BN powder.
It is preferred that, abradable coating A51 and intermediate metal A52 fills the fit clearance region of volute 5 and turbine 2 jointly,
Total filling thickness (total filling thickness refers to abradable coating A51 and intermediate metal A52 thickness sum) and fit clearance
Than for 60% ~ 90%；Abradable coating B71 fills the fit clearance region of pressure shell 7 and impeller 1, filling thickness and fit clearance ratio
For 60% ~ 90%.
Claims (4)
1. using abradable coating carry out blade tip clearance control turbocharger, including impeller (1), turbine (2), main shaft (3),
Bearing body (4), volute (5), back of the body disk (6), pressure shell (7)；
Impeller (1) and turbine (2) are separately mounted to the two ends of main shaft (3)；Bearing body (4) is arranged in the middle part of main shaft (3)；Volute
(5) it is arranged on one end of bearing body (4) and turbine (2) is accommodated within chamber, back of the body disk (6) is arranged on the another of bearing body (4)
One end；Pressure shell (7) is arranged on back of the body disk (6) and impeller (1) is accommodated within chamber；
It is characterized in that：Volute (5) internal chamber wall be provided with abradable coating A (51), abradable coating A (51) be located at volute (5) with
In the fit clearance region of turbine (2)；Pressure shell (7) internal chamber wall is provided with abradable coating B (71), and abradable coating B (71) is set
In the fit clearance region of pressure shell (7) and impeller (1).
2. the turbocharger of blade tip clearance control is carried out using abradable coating as claimed in claim 1, it is characterized in that：Can
It is connected between abrasion coating A (51) and volute (5) internal chamber wall by intermediate metal A (52)；Abradable coating B (71) directly with
Pressure shell (7) internal chamber wall is connected.
3. the turbocharger of blade tip clearance control is carried out using abradable coating as claimed in claim 2, it is characterized in that：Gold
The thickness ratio for belonging to transition zone A (52) and abradable coating A (51) is 1：2-4.
4. the turbocharger of blade tip clearance control is carried out using abradable coating as claimed in claim 3, it is characterized in that：Can
Abrasion coating A (51) and intermediate metal A (52) fills the fit clearance region of volute (5) and turbine (2) jointly, and total filling is thick
Degree is 60% ~ 90% with fit clearance ratio；The fit clearance region of abradable coating B (71) filling pressure shells (7) and impeller (1), is filled out
It is 60% ~ 90% to fill thickness with fit clearance ratio.
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 true CN107327318A (en) | 2017-11-07 |
| CN107327318B CN107327318B (en) | 2023-09-22 |
Family
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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) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108661949A (en) * | 2018-08-16 | 2018-10-16 | 湖南天雁机械有限责任公司 | A kind of turbocharger with abradable coating |
Citations (5)
| 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 |
| US20180051707A1 (en) * | 2015-02-27 | 2018-02-22 | Mitsubishi Heavy Industries, Ltd. | Method of manufacturing supercharger |
-
2017
- 2017-07-25 CN CN201710609956.5A patent/CN107327318B/en active Active
Patent Citations (5)
| 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 |
| US20180051707A1 (en) * | 2015-02-27 | 2018-02-22 | Mitsubishi Heavy Industries, Ltd. | Method of manufacturing supercharger |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108661949A (en) * | 2018-08-16 | 2018-10-16 | 湖南天雁机械有限责任公司 | A kind of turbocharger with abradable coating |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107327318B (en) | 2023-09-22 |
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