CN101846100B - Blade grid for improving pneumatic stability of gas compressor - Google Patents
Blade grid for improving pneumatic stability of gas compressor Download PDFInfo
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- CN101846100B CN101846100B CN200910021665XA CN200910021665A CN101846100B CN 101846100 B CN101846100 B CN 101846100B CN 200910021665X A CN200910021665X A CN 200910021665XA CN 200910021665 A CN200910021665 A CN 200910021665A CN 101846100 B CN101846100 B CN 101846100B
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- blade
- leaf grating
- blades
- leading edge
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Abstract
The invention relates to a pneumatic blade grid layout for improving the pneumatic stability of a gas compressor. Every three adjacent blades in the same blade row are a blade group, the axial position of the front edge of a first blade (1) is taken as a standard, and the front edge of a second blade (2), which is adjacent to the first blade (1), moves rearwards to 7 to 15 percent of the axial chord length L of the first blade (1) along the axial direction of a blade grid according to the positioned standard; the front edge of a third blade (3), which is adjacent to the second blade (2), and the front edge of the second blade (2) are positioned on the same position on the axis direction of the blade grid, and the third blade (3) and the second blade (2) adopt the same blades; and other blades on the same blade row are distributed according to the manner. In the invention, three different air channels are formed in the same blade row, and the air current flow has unique characteristics which are different from the prior art, therefore, the invention can improve the pneumatic stability of the gas compressor better and has the capacities of increasing the pneumatic load of the blades and reducing the flow loss.
Description
One, technical field
The present invention relates to the axial-flow blower mechanical field, is a kind of leaf grating that improves pneumatic stability of gas compressor.
Two, background technique
Modern high thrust weight ratio aero gas turbine engine requirement gas compressor progression is few, aerodynamic stability is high; Yet; Concerning the gas compressor pneumatic design of existing technology, reduce gas compressor progression, when improving pneumatic load of blades, usually cause that the aerodynamic stability of gas compressor reduces.For this reason, people have taked the whole bag of tricks to improve the aerodynamic stability of gas compressor on pneumatic design and structural design.Existing conventional axial flow compressor blade adopts design proposal axisymmetric fully, even layout; When the inlet air flow angle of attack is big; The friction layer on each blade blade back surface can separate simultaneously, causes rotating stall even surge when serious, and finally possibly cause structural failure.In the gas compressor design, should increase the stability margin of gas compressor as far as possible, be operated in this unsure state to avoid gas compressor.But to existing leaf grating symmetrically and evenly, the potentiality that can excavate are limited to very much.
A kind of aerodynamic arrangement's scheme of compressor blade row, notification number is disclosed in being the Chinese invention patent of CN1955492; Through two adjacent blades leading edges in the blade row compressorshaft to the position be staggered (displacement distance be sharf to chord length 5%～15%); When axial position when preceding blade (blade 1) is operated in big import positive incidence state; Because the leaf basin surface of blade 1 is to flowing into the restriction and the leading role of air-flow; The inlet air flow angle of attack of the blade (blade 2) that the leading edge axial position moves backward reduces, thereby the mobile of blade 2 improved, and improves the aerodynamic stability of gas compressor.Yet, because influencing each other of adjacent blade grid passage weakened the effect that this cascade structure increases aerodynamic stability.
Three, summary of the invention
For overcoming the defective of the increase leaf grating aerodynamic stability poor effect that exists in the existing technology, the present invention proposes a kind of leaf grating that improves pneumatic stability of gas compressor.
The technological scheme that the present invention taked is with along the leaf grating tangential, and promptly each blade inlet edge in the same blade row arranged of directions X press the axial of leaf grating, and promptly the front and back difference of Z direction position is arranged.When arranging; Every three adjacent blades are a vane group in the same blade row; Promptly; Leading edge axial position with first blade is axial locating basis, second the blade inlet edge position that is adjacent with respect to first blade along leaf grating axially after move, the distance that is moved is that first sharf is to 7%～15% of chord length L; The leading edge of three blade adjacent with second blade and the leading edge of second blade are in identical position in the cascade axis direction, and the 3rd blade adopts identical blade with second blade.Other vane group of same blade row is then arranged in this way.
In a vane group; Three blades are arranged in order according to two kinds of different axial positions; Three kinds of multi-form leaf grating air-flow paths have been constituted; Be that the blade back of first blade and the leaf basin of second blade constitute leaf grating air-flow path A, the leaf grating air-flow path B that the leaf basin of the blade back of second blade and the 3rd blade constitutes, the leaf grating air-flow path C that the leaf basin of first blade of the blade back of the 3rd blade and another adjacent group constitutes.
In general, constitute the blade and blade basin of same air-flow path and the difference of position to axial on two surfaces of blade back, different to the influence of flowing.Like the relative axial position on two surfaces when identical, be exactly blade conventional in the existing technology pairing air-flow path of leaf grating of arranging symmetrically.Compare leaf grating symmetrically, leaf basin surface to axial the position in front, the leaf basin surface that constitutes this passage to the position of air-flow generation effect in advance and effect strengthen, the flox condition in the passage will improve; On the contrary, the position is in the back to axial on leaf basin surface, and the leaf basin surface that constitutes this passage is stepped back and acted on the position of air-flow generation effect and weakens, and the flox condition in the passage will worsen.
The notable feature that compressor blade row of the present invention is different from existing technology is: leaf grating is made up of tactic vane group; Each vane group is made up of three blades; First blade in three blades, second blade and the 3rd blade are arranged in order along the tangential of leaf grating; The leading edge of second blade and the 3rd blade is with respect to the back vertically phase shift of first a blade inlet edge segment distance together; And second blade be identical blade with the 3rd blade, thereby formed the arrangement mode of blade in the distinctive leaf grating, and constituted three mutually different, as to have unique texture air-flow paths; The flow characteristic of air-flow in three different passages is different from existing technology, and aerodynamic stability is improved.
Compare with one group of staggered leaf grating of two blades (notification number is the Chinese invention patent of CN1955492); The air-flow path A of leaf grating of the present invention and channel C respectively with one group of leaf grating that is staggered of two blades in passage A and channel B similar, channel B of the present invention is then similar with the passage of leaf grating symmetrically.When leaf grating is operated in big inlet air flow angle of attack state, for one group of staggered leaf grating of two blades, flowing of passage A will worsen; Flowing of channel B then can improve; Utilize channel B to suppress among the passage A separation zone in the propagation of leaf grating tangential, this is its basic ideas that improve aerodynamic stability, but because passage A and channel B are adjacent one another are; Flowing among the passage A that worsens will inevitably have influence on flowing in the adjacent channel B, improves the effect of stability thereby weakened it.For leaf grating of the present invention, flowing of passage A will worsen, and the mobile meeting of channel C improves, and remain flowing in the channel C of utilizing after improving and stop the propagation of separation zone along the leaf grating tangential.Different with existing technology is; Also there is a channel B between the passage A of leaf grating of the present invention and the channel C; And flowing of channel B is similar with leaf grating symmetrically, and so, channel B has played a kind of effect of isolation; Make passage A can't directly influence flowing in the channel C, strengthened the effect of improving stability.
Leaf grating of the present invention and one group of leaf grating that is staggered of two blades (notification number is the Chinese invention patent of CN1955492) have been carried out the comparative study of Flow Field Calculation; The blade 1 of one group of leaf grating that is staggered of first blade and two blades is identical in the vane group wherein of the present invention; Second blade 2 with one group of leaf grating that is staggered of the 3rd blade and two blades is identical in the vane group of the present invention; Blade tangential spacing is identical, after to move the displacement distance of blade identical.Result calculated shows that all greater than the air-flow deflection angle of one group of leaf grating that is staggered of two blades, especially in the Low Angle Of Attack scope, leaf grating of the present invention not only air-flow deflection angle increases about 0.5 ° to the air-flow deflection angle of leaf grating of the present invention, and flow losses reduce.
Therefore; With notification number is that the Chinese invention patent of CN1955492 is compared; Adopt cascade layout pattern of the present invention, the effect of leaf grating aerodynamic stbilization property improvement is enhanced, but also obtained the additional effect that airload increase, flow losses reduce.
Four, description of drawings
Accompanying drawing 1 is a cascade layout scheme of the present invention.
In the accompanying drawing:
The 3rd blade of second blade 3-of first blade of 1-2-
The leaf grating air-flow path that the leaf basin of the blade back of first blade of A-and second blade constitutes
The leaf grating air-flow path that the leaf basin of the blade back of second blade of B-and the 3rd blade constitutes
The leaf grating air-flow path that the leaf basin of the blade back of the 3rd blade of C-and first blade of adjacent blades group constitutes
The axial chord length X-leaf grating tangential direction coordinate Z-leaf grating axial direction coordinate of first blade of L-
Five, embodiment
Embodiment one
Present embodiment will be along the leaf grating tangential, promptly the leading edge of same row's blade of directions X press cascade axis to, promptly the front and back difference of Z direction position is arranged.Wherein the leading edge of blade 2 is moved a segment distance with respect to the leading edge of blade 1 after the cascade axis direction, and mobile distance is 10% of blade 1 axial chord length L; Blade 3 adopts the blade profile identical with blade 2, and its leading edge moves distance with moving distance behind the blade 2 after the cascade axis direction, and promptly mobile distance is 10% of blade 1 axial chord length L.
Said each vane foil design bent angle is 41 °; The leaf grating of present embodiment and one group of staggered leaf grating of two blades all carry out flow field numerical optimization design according to same inlet/outlet condition; Cascade flow field numerical simulation result calculated shows; The flow losses of leaf grating of the present invention are lower than one group of staggered leaf grating of two blades, and the air-flow deflection angle increases about 0.5 ° than one group of staggered leaf grating of two blades.
Embodiment two
Present embodiment will be along the leaf grating tangential, promptly the leading edge of same row's blade of directions X press cascade axis to, promptly the front and back difference of Z direction position is arranged.Wherein the leading edge of blade 2 is moved a segment distance with respect to the leading edge of blade 1 after the cascade axis direction, and mobile distance is 7% of blade 1 axial chord length L; Blade 3 adopts the blade profile identical with blade 2, and its leading edge moves distance with moving distance behind the blade 2 after the cascade axis direction, and promptly mobile distance is 7% of blade 1 axial chord length L.
Embodiment three
Present embodiment will be along the leaf grating tangential, promptly the leading edge of same row's blade of directions X press cascade axis to, promptly the front and back difference of Z direction position is arranged.Wherein the leading edge of blade 2 is moved a segment distance with respect to the leading edge of blade 1 after the cascade axis direction, and mobile distance is 15% of blade 1 axial chord length L; Blade 3 adopts the blade profile identical with blade 2, and its leading edge moves distance with moving distance behind the blade 2 after the cascade axis direction, and promptly mobile distance is 15% of blade 1 axial chord length L.
Embodiment four
Present embodiment will be along the leaf grating tangential, promptly the leading edge of same row's blade of directions X press cascade axis to, promptly the front and back difference of Z direction position is arranged.Wherein the leading edge of blade 2 is moved a segment distance with respect to the leading edge of blade 1 after the cascade axis direction, and mobile distance is 12% of blade 1 axial chord length L; Blade 3 adopts the blade profile identical with blade 2, and its leading edge moves distance with moving distance behind the blade 2 after the cascade axis direction, and promptly mobile distance is 12% of blade 1 axial chord length L.
Claims (1)
1. leaf grating that improves pneumatic stability of gas compressor; Comprise the blade row of forming by blade; And each blade inlet edge in the same blade row press leaf grating axially, promptly the front and back difference of Z direction position is arranged, and constitutes the leaf grating air-flow path by the leaf basin and the blade back of adjacent blades; It is characterized in that every three adjacent blades are a vane group in the same blade row; In vane group; Leading edge axial position with first blade (1) is axial locating basis; Second blade (2) leading edge locus that is adjacent is with respect to the axially backward mobile segment distance of locating basis along leaf grating, and the distance that is moved is 7%～15% of the axial chord length L of first blade (1); The leading edge of three blade (3) adjacent with second blade (2) and the leading edge of second blade (2) are in identical position in the cascade axis direction, and the 3rd blade (3) adopts identical blade with second blade (2); Other vane group of same blade row is then arranged in this way.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910021665XA CN101846100B (en) | 2009-03-24 | 2009-03-24 | Blade grid for improving pneumatic stability of gas compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910021665XA CN101846100B (en) | 2009-03-24 | 2009-03-24 | Blade grid for improving pneumatic stability of gas compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101846100A CN101846100A (en) | 2010-09-29 |
| CN101846100B true CN101846100B (en) | 2012-05-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910021665XA Expired - Fee Related CN101846100B (en) | 2009-03-24 | 2009-03-24 | Blade grid for improving pneumatic stability of gas compressor |
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| Country | Link |
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| CN (1) | CN101846100B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105298912B (en) * | 2015-11-10 | 2017-12-05 | 南京航空航天大学 | Bulge leading edge inlet guiding blade |
| CN113217226B (en) * | 2021-06-02 | 2022-08-02 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
| CN113864243A (en) * | 2021-09-10 | 2021-12-31 | 中国民航大学 | Axial flow compressor for improving full-circumferential flow field |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3442441A (en) * | 1966-07-21 | 1969-05-06 | Wilhelm Dettmering | Supersonic cascades |
| RU2213272C1 (en) * | 2002-04-02 | 2003-09-27 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Rotor rim of axial-flow compressor (fan) of turbojet engine |
| CN1955492A (en) * | 2005-10-25 | 2007-05-02 | 西北工业大学 | Louver distribution of raising pneumatic stability |
| CN101158362A (en) * | 2007-11-29 | 2008-04-09 | 北京航空航天大学 | Big and small blade tandem blade cascade impeller and compressor |
| CN101169138A (en) * | 2006-10-27 | 2008-04-30 | 西北工业大学 | Axial flow compressor stator blade arrangement style |
| EP1956247A1 (en) * | 2005-11-29 | 2008-08-13 | IHI Corporation | Cascade of stator vane of turbo fluid machine |
-
2009
- 2009-03-24 CN CN200910021665XA patent/CN101846100B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3442441A (en) * | 1966-07-21 | 1969-05-06 | Wilhelm Dettmering | Supersonic cascades |
| RU2213272C1 (en) * | 2002-04-02 | 2003-09-27 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Rotor rim of axial-flow compressor (fan) of turbojet engine |
| CN1955492A (en) * | 2005-10-25 | 2007-05-02 | 西北工业大学 | Louver distribution of raising pneumatic stability |
| EP1956247A1 (en) * | 2005-11-29 | 2008-08-13 | IHI Corporation | Cascade of stator vane of turbo fluid machine |
| CN101169138A (en) * | 2006-10-27 | 2008-04-30 | 西北工业大学 | Axial flow compressor stator blade arrangement style |
| CN101158362A (en) * | 2007-11-29 | 2008-04-09 | 北京航空航天大学 | Big and small blade tandem blade cascade impeller and compressor |
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| Publication number | Publication date |
|---|---|
| CN101846100A (en) | 2010-09-29 |
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Granted publication date: 20120530 Termination date: 20170324 |