CN102797703A - Impeller of compressor - Google Patents
Impeller of compressor Download PDFInfo
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- CN102797703A CN102797703A CN2012103318939A CN201210331893A CN102797703A CN 102797703 A CN102797703 A CN 102797703A CN 2012103318939 A CN2012103318939 A CN 2012103318939A CN 201210331893 A CN201210331893 A CN 201210331893A CN 102797703 A CN102797703 A CN 102797703A
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- impeller
- blade
- turntable
- radius
- rotating disk
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Abstract
The invention provides an impeller of a compressor. The impeller comprises a turntable and a plurality of blades arranged on the turntable, wherein the blades are separated from the centre of the turntable along the radial direction, and outwards extended along the surface of the turntable; a fillet-shaped structure is formed at the part at which the roots of the blades are connected with the turntable; fillet-shaped parts formed at the front edges of the blades and the turntable have radius Rh, the filled-shaped parts formed at the tail edges of the blade and the turntables have radius Rf, and the Rh is less than Rf based on the number. With adoption of the impeller of the compressor provided by the invention, the conflict in design of a pneumatic sensitive position and a stress concentration position can be effectively solved, and the pneumatic performance of the actual impeller appropriate ideal design value, and moreover, the stress concentration at the roots can be greatly reduced, the service life of the impeller is prolonged, and the requirements on the materials of the impeller are also relatively reduced, and as a result, the economy of the impeller is increased.
Description
Technical field
The present invention relates to the compressor apparatus technical field, relate in particular to the impeller that uses in a kind of turbocompressor.
Background technique
Generally, turbocompressor impeller blade root structure shape all is to wait the rounded shapes of radius, be accomplish the milling cutter of selecting certain radius after blade mills system for use along the root of blade system of milling form etc. the radius arc structure.In impeller design, blade inlet edge is the sensitive position that inlet gas flows, and this regional fillet radius should be as far as possible little; Simultaneously, blade trailing edge suction surface root is the sensitive position of structural stress, and this position needs bigger fillet radius to concentrate to reduce stress again.Generally speaking, in the impeller design process, aeroperformance and stress are considered in compromise usually, and the blade root fillet is chosen the radius that waits of compromise, and this structural design promptly can't reduce stress very fully to be concentrated, and has influenced the impeller aeroperformance again.
Summary of the invention
To the deficiency that exists in the existing technology, the present invention proposes a kind of compressor impeller of novel structure.Aeroperformance according to actual impeller; The compressor that proposes has solved the design contradiction of pneumatic sensitive position and stress concentrated position effectively, reduces the stress of root significantly and concentrates, and improves impeller life; Also correspondingly reduce simultaneously the impeller material requirement, improved the impeller Economy.
To achieve these goals; The present invention provides a kind of compressor impeller; Comprise rotating disk and be installed in a plurality of blades on the rotating disk, it is characterized in that said blade radially leaves center of turntable and protruding along disc surfaces; The root of said blade and rotating disk joint form the rounding shape and structure, and the radius that the front edge of said blade and rotating disk place form the rounding shape is R
h, the radius that the trailing edge of said blade and rotating disk place form the rounding shape is R
f, said R
hNumerical value less than R
fNumerical value.
In a preferred embodiment provided by the invention, the radius of wherein said root of blade rounded shapes increases along the root of blade direction gradually.
Compressor impeller provided by the invention has solved the design contradiction of pneumatic sensitive position and stress concentrated position effectively; The aeroperformance that makes actual impeller is near the ideal design value; Reducing the stress of root again significantly concentrates; Improve impeller life, also correspondingly reduced the impeller material requirement simultaneously, improve the impeller Economy.
Description of drawings
Fig. 1 is a compressor impeller schematic representation provided by the invention.
Fig. 2 is the enlarged view of compressor impeller upper blade of the present invention.
Fig. 3 is the root structure schematic representation of compressor impeller upper blade of the present invention.
Embodiment
The present invention provides a kind of compressor impeller, guarantees compressor impeller leaf aeroperformance, makes the impeller aeroperformance near the Design Theory value.Simultaneously, reduce impeller stress and concentrate, and then reduce material requirements, improve Economy.
Below through embodiment compressor impeller provided by the invention is done further explain so that better understand the content of the invention, but embodiment's content does not limit the protection domain of the invention.
As depicted in figs. 1 and 2, compressor impeller is made up of rotating disk and a plurality of blades 1 that are installed on the rotating disk.Blade 1 radially leaves center of turntable and protruding along disc surfaces, and the root of blade 1 and rotating disk joint form the rounding shape and structure.The front edge 11 of said blade is R with the radius that the rotating disk place forms the rounding shape
h, the trailing edge 14 of said blade is R with the radius that the rotating disk place forms the rounding shape
f, said R
hNumerical value less than R
fNumerical value.The rounding shape radius of whole blade and rotating disk intersection prolongs the linear increase of blade bearing of trend, and the radius unequal fillet smooth transition that progressively increases to the disk edge position from nearly center of turntable position forms fillet and removes face, to increase the intensity of blade.
Generally be provided with 12 ~ 20 blades on the rotating disk of compressor impeller, preferred rotating disk is provided with 16 blades.
The present invention proposes the shape that turbocompressor impeller blade root has radius variable rounding structure, at the blade inlet edge root, exhausts the little fillet radius R of possibility
hTo guarantee the impeller aeroperformance; At the blade trailing edge root, get suitably big fillet radius R
fConcentrate with effective reduction stress.Blade inlet edge root fillet radius R
hWith blade trailing edge root fillet radius R
fConcrete size combine Pneumatic Calculation with intensity calculating and confirm.This compressor impeller makes the aeroperformance of actual impeller near the ideal design value, reduces the stress of root again significantly and concentrates, and improves impeller life, has also correspondingly reduced the impeller material requirement simultaneously, improves the impeller Economy.
More than specific embodiment of the present invention is described in detail, but it is just as example, the present invention is not restricted to the specific embodiment of above description.To those skilled in the art, any equivalent modifications that the present invention is carried out with substitute also all among category of the present invention.Therefore, not breaking away from impartial conversion and the modification of being done under the spirit and scope of the present invention, all should contain within the scope of the invention.
Claims (2)
1. compressor impeller; Comprise rotating disk and be installed in a plurality of blades on the rotating disk; It is characterized in that; Said blade radially leaves center of turntable and protruding along disc surfaces, and the root of said blade and rotating disk joint form the rounding shape and structure, and the radius that the front edge of said blade and rotating disk place form the rounding shape is R
h, the radius that the trailing edge of said blade and rotating disk place form the rounding shape is R
f, said R
hNumerical value less than R
fNumerical value.
2. compressor impeller according to claim 1 is characterized in that the radius of wherein said root of blade rounded shapes increases along the root of blade direction gradually.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210331893.9A CN102797703B (en) | 2012-09-10 | 2012-09-10 | Impeller of compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210331893.9A CN102797703B (en) | 2012-09-10 | 2012-09-10 | Impeller of compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102797703A true CN102797703A (en) | 2012-11-28 |
| CN102797703B CN102797703B (en) | 2015-04-15 |
Family
ID=47196950
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210331893.9A Active CN102797703B (en) | 2012-09-10 | 2012-09-10 | Impeller of compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102797703B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103362867A (en) * | 2013-08-02 | 2013-10-23 | 无锡杰尔压缩机有限公司 | Variable chamfer structure of unshrouded impeller |
| CN104373377A (en) * | 2014-10-30 | 2015-02-25 | 中国北车集团大连机车研究所有限公司 | High-pressure-ratio gas compressor impeller of supercharger for internal combustion engine |
| CN106715920A (en) * | 2014-09-22 | 2017-05-24 | 西门子公司 | Radial compressor impeller and associated radial compressor |
| CN107304774A (en) * | 2016-04-19 | 2017-10-31 | 本田技研工业株式会社 | Compressor |
| CN110770449A (en) * | 2017-11-15 | 2020-02-07 | 三菱重工发动机和增压器株式会社 | Compressor impeller, compressor, and turbocharger |
| CN111069670A (en) * | 2019-12-31 | 2020-04-28 | 苏州千机智能技术有限公司 | Blisk variable-radius transition fillet machining method and system |
| CN112049818A (en) * | 2019-06-06 | 2020-12-08 | 中国航发商用航空发动机有限责任公司 | Compressor and compressor blade |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004052754A (en) * | 2002-05-10 | 2004-02-19 | Borgwarner Inc | Hybrid method for manufacturing titanium compressor impeller |
| CN2736567Y (en) * | 2004-10-20 | 2005-10-26 | 徐光伦 | Axial flow fan impeller with low noise and large wind rate |
| EP1750014A2 (en) * | 2005-08-03 | 2007-02-07 | Mitsubishi Heavy Industries, Ltd. | Axial fan for heat exchanger of in-vehicle air conditioner |
| CN101893003A (en) * | 2010-05-31 | 2010-11-24 | 宋波 | 3-D impeller of high-load centrifugal compressor |
-
2012
- 2012-09-10 CN CN201210331893.9A patent/CN102797703B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004052754A (en) * | 2002-05-10 | 2004-02-19 | Borgwarner Inc | Hybrid method for manufacturing titanium compressor impeller |
| CN2736567Y (en) * | 2004-10-20 | 2005-10-26 | 徐光伦 | Axial flow fan impeller with low noise and large wind rate |
| EP1750014A2 (en) * | 2005-08-03 | 2007-02-07 | Mitsubishi Heavy Industries, Ltd. | Axial fan for heat exchanger of in-vehicle air conditioner |
| CN101893003A (en) * | 2010-05-31 | 2010-11-24 | 宋波 | 3-D impeller of high-load centrifugal compressor |
Non-Patent Citations (1)
| Title |
|---|
| 刘军: "大流量离心压缩机首级叶轮强度分析及结构改进设计研究", 《中国优秀硕士学位论文全文数据库》, 11 August 2009 (2009-08-11) * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103362867A (en) * | 2013-08-02 | 2013-10-23 | 无锡杰尔压缩机有限公司 | Variable chamfer structure of unshrouded impeller |
| CN106715920A (en) * | 2014-09-22 | 2017-05-24 | 西门子公司 | Radial compressor impeller and associated radial compressor |
| CN104373377A (en) * | 2014-10-30 | 2015-02-25 | 中国北车集团大连机车研究所有限公司 | High-pressure-ratio gas compressor impeller of supercharger for internal combustion engine |
| CN107304774A (en) * | 2016-04-19 | 2017-10-31 | 本田技研工业株式会社 | Compressor |
| CN107304774B (en) * | 2016-04-19 | 2019-03-15 | 本田技研工业株式会社 | Compressor |
| CN110770449A (en) * | 2017-11-15 | 2020-02-07 | 三菱重工发动机和增压器株式会社 | Compressor impeller, compressor, and turbocharger |
| CN112049818A (en) * | 2019-06-06 | 2020-12-08 | 中国航发商用航空发动机有限责任公司 | Compressor and compressor blade |
| CN112049818B (en) * | 2019-06-06 | 2022-04-26 | 中国航发商用航空发动机有限责任公司 | Compressor and compressor blade |
| CN111069670A (en) * | 2019-12-31 | 2020-04-28 | 苏州千机智能技术有限公司 | Blisk variable-radius transition fillet machining method and system |
| CN111069670B (en) * | 2019-12-31 | 2021-08-20 | 苏州千机智能技术有限公司 | Blisk variable-radius transition fillet machining method and system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102797703B (en) | 2015-04-15 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| C56 | Change in the name or address of the patentee | ||
| CP03 | Change of name, title or address |
Address after: 201400 Fengxian District Bay Town, Shanghai, No. 54 Road, building 751, building 3 Patentee after: SANY ENVIRONMENTAL PROTECTION TECHNOLOGY Co.,Ltd. Address before: 201422 Fengxian District Bay Town, Shanghai, No. 54 Road, building 751, building 3 Patentee before: SANY ENERGY HEAVY INDUSTRY Co.,Ltd. |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20170303 Address after: Cheng Hu road Kunshan Development Zone in Suzhou City, Jiangsu province 215300 No. 9999 room 6 Patentee after: KUNSHAN SANYI ENVIRONMENTAL PROTECTION TECHNOLOGY Co.,Ltd. Address before: 201400 Fengxian District Bay Town, Shanghai, No. 54 Road, building 751, building 3 Patentee before: SANY ENVIRONMENTAL PROTECTION TECHNOLOGY Co.,Ltd. |