CN105864105A - Axial flow compressor stator with in-vitro small blades in hub corner area - Google Patents
Axial flow compressor stator with in-vitro small blades in hub corner area Download PDFInfo
- Publication number
- CN105864105A CN105864105A CN201610259830.5A CN201610259830A CN105864105A CN 105864105 A CN105864105 A CN 105864105A CN 201610259830 A CN201610259830 A CN 201610259830A CN 105864105 A CN105864105 A CN 105864105A
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- China
- Prior art keywords
- stator
- vitro
- blade
- vanelets
- blades
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- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
Abstract
The invention discloses an axial flow compressor stator with in-vitro small blades in a hub corner area. The axial flow compressor stator comprises a casing, stator blades and a hub, and is characterized by further comprising the in-vitro small blades, wherein the in-vitro small blades are double-circular arc blade-shaped straight blades, are positioned between the stator blades, and are not in contact with the stator blades; the blade roots of the in-vitro small blades are fixedly connected with the hub; and mounting angles of the blade roots of the in-vitro small blades are not larger than mounting angles of the blade roots of the stator blades. According to the axial flow compressor stator, the corner area separation in stator blade channels is inhibited, induction vortex structures generated at the front edges of the blade tops of the in-vitro small blades and separation fluids of the stator blades act on each other, the separation fluids are enabled to flow more close to the blade backs, and the further development of fluid separation is inhibited, so that the effective circulation area of a runner of the compressor is enlarged, and the flow margin of the compressor is improved; and compared with a stator tandem cascade technology, the axial flow compressor stator has the advantages that modification design is not required, the mounting is convenient, and the industrial manufacturing cost is reduced.
Description
Technical field
The present invention relates to the flowing control field of turbomachine, be specifically related to the axle of a kind of wheel hub angular region in vitro vanelets of band
Flow air compressor stator.
Background technology
For modern aeroengine, usually require that its fan and import level function of calming the anger is stable under various complex flowfields
Work.But when compressor is operated in severe off-design behaviour, under the effect of runner adverse pressure gradient, compressor stator blade
Wheel hub angular region is susceptible to corner separation phenomenon.Once flow separation expands, and separates fluid blockage compressor passage, makes compressor
Entering the unsteady-stage conditions such as rotating stall, surge, Capability of Compressor drastically deteriorates, and has a strong impact on the normal work of engine.Right
Big in high load capacity stator blade diffusion degree, flow segregative feature, document " Wei Wei, Liu Bo etc., high load capacity baby compressor
Big bent angle tandem stator characteristic [J]. aviation power journal .2013.28 (5): 1067-1073 " provide a kind of flow separation control
The technology of system, document has carried out tandem remodeling and has ground the big bent angle stator blade of axial flow part one of a small-sized turboshaft engine
Studying carefully, the air-flow using tandem stator effectively to reduce original stator separates, and improves pressure ratio and efficiency.In order to improve pressure in document
Mechanism of qi stator performance, need to redesign a set of tandem stator blade, replace original stator blade, and workload certainly will be caused big,
And increase industry manufacturing cost.
Summary of the invention
The technical issues that need to address of the present invention are: in order to avoid the weak point of existing tandem cascade technology, the present invention
Propose the axial flow compressor stator of a kind of wheel hub angular region in vitro vanelets of band, i.e. at the wheel hub angle of compressor stator blade leading edge
District, install an in vitro vanelets, in vitro vanelets near stator blade suction surface, overall dimensions 1-2 lower than stator blade number
Magnitude.Utilize in vitro vanelets that the separation fluid of stator passage carries out control of flowing.On the one hand, air-flow in vitro vanelets and
Accelerating in stator blade to flow through, blow down the separation fluid of stator blade trailing edge, on the other hand, the leaf top of in vitro vanelets induces
Helical flow, the motion of this whirlpool inhibits the development of corner separation in stator blade passage.Improve the steady operation model of compressor
Enclose.This technology is simple, only need to install an in vitro vanelets in original stator blade wheel hub angular region leading edge.Avoid as string
Row Cascade Flow controls technology needs to redesign the trouble of a set of blade profile.
The technical scheme is that the axial flow compressor stator of a kind of wheel hub angular region in vitro vanelets of band, including casing
4, stator blade 1, wheel hub 3, also includes in vitro vanelets 2, and described in vitro vanelets 2 is dual arc blade profile prismatic blade, is positioned at quiet
Between blades 1 and stator blade 1, and in vitro vanelets 2 does not contacts with stator blade 1；In vitro vanelets 2 blade root and wheel hub 3
Being connected, the established angle of in vitro vanelets blade root is not more than the established angle of stator blade blade root.
The further technical scheme of the present invention is: along wheel hub 3 axis direction, before described in vitro vanelets 2 and stator blade 1
The distance of edge is the axial chord length of blade root of 5%-15%；Along wheel hub 3 circumferential direction, in vitro vanelets 2 and stator blade 1 suction surface
The axial chord length of the blade root that distance is 5%-10%.
The further technical scheme of the present invention is: the blade profile bent angle of described in vitro vanelets 2 is 30 °-60 °
The further technical scheme of the present invention is: the 40%-that leaf a height of stator blade leaf of described in vitro vanelets is high
60%.In vitro vanelets blade root chord length is the 5%-10% of stator blade blade root chord length.
Invention effect
The method have technical effect that: relative to design conditions, under low flow rate condition, stator wheel hub angular region is taken turns
Hub corner separation phenomenon, the in vitro vanelets being installed on stator blade wheel hub angular region leading edge guides air-flow to deflect, and accelerates
Flowing, it is suppressed that the corner separation in stator blade passage, and the induction vortex structure that produces of in vitro vanelets leaf top leading edge with
The separation fluid interaction of stator blade, makes separation fluid more press close to blade back flowing, it is suppressed that flow separation further
Development.Therefore expand the valid circulation area of compressor passage, improve the flow nargin of compressor.Compared with stator tandem cascade
Technology, it is not necessary to Transform Type design, the present invention is easy for installation, saves industry manufacturing cost.Subsonic axial compressor level is carried out
The research that in vitro vanelets suppression compressor stator blade wheel hub corner region flow separates.Result of study shows, does not installs in vitro
The single-stage compressor flow nargin of vanelets is 12.26%, and the flow nargin arranging the acquisition of in vitro vanelets at stator blade is
15.49%, flow nargin improvement is 3.23%.The in vitro vanelets flow control technique of invention increases the steady of compressor stage
Determine working range.
Accompanying drawing explanation
Fig. 1 is that the in vitro vanelets flow control technique of the present invention applies the single channel at compressor stator blade to illustrate
Figure；
Fig. 2 is the in vitro vanelets in stator blade blade root cross section and stator blade contour structure schematic diagram；
Fig. 3 be atmospheric pressure be in vitro vanelets antero posterior axis flow air compressor stator 10% leaf height to be installed under 105500Pa back pressure cut
Face air-flow streamline distribution contrast；
Description of reference numerals: 1 stator blade；2 in vitro vanelets；3 wheel hubs；4 casings；Before 5 stator blades
Edge；6 stator blade trailing edges；7 suction surfaces；8 pressure faces.
Detailed description of the invention
Below in conjunction with being embodied as example, technical solution of the present invention is further illustrated.
1, Fig. 1-Fig. 3 is seen, including axial flow compressor stator blade, axial flow compressor wheel hub, casing and in vitro vanelets,
It is characterized between each two stator blade that in vitro vanelets is installed in stator passage.Along hub axis direction, the least
Blade and the axial chord length of the blade root that distance is 5%-15% of stator blade leading edge, axial chord length is that blade chord length is in rotary shaft
The projection in direction.The blade root axle that distance is 5%-10% along wheel hub circumferential direction, in vitro vanelets and stator blade suction surface
To chord length, in vitro vanelets blade root is connected with stator wheel hub.
In vitro vanelets is the prismatic blade of a dual arc blade profile, the 40%-60% that leaf a height of stator blade leaf is high.The least
The 5%-10% of chord of blade a length of stator blade blade root chord length, established angle is not more than the established angle of stator blade blade root.
1) compressor casing 4 radius of research object of the present invention is 0.1466m, wheel hub 3 radius 0.091m, stator blade number
Mesh is 44.
2) installing in vitro vanelets 2 on wheel hub 3, the blade root of in vitro vanelets 2 is connected with wheel hub 3.In vitro vanelets) 2
For prismatic blade, accounting for the 40% of stator blade 1 radical length, i.e. blade height to leaf top radial span from blade root is stator blade 1
The 40% of height.Blade root chord length is stator blade 1 blade root chord length the 5% of in vitro vanelets 2.
3) blade profile that in vitro vanelets 2 uses is dual arc blade profile, and the maximum relative thickness of blade profile is 0.17mm.Blade profile is curved
Angle is 50 °.
4) axial location in vitro vanelets 2 blade root is installed in the wheel hub 3 of stator blade 1 blade root leading edge 10% shaft orientation string strong point
On, blade profile established angle is 26 °, and the circumferential position in vitro vanelets 2 blade root leading edge distance away from stator blade suction surface 7 is 7.4%
The axial chord length of stator blade root.It should be noted that the established angle of blade profile is the string of a musical instrument and axial angle, the compressor of blade profile
The direction that middle acquiescence leaf is high is radially, and direction of rotation is circumference, and rotary shaft is axial.
5) radical length of in vitro vanelets 2 is much larger than blade chord length much larger than tangential length, i.e. blade height, but is not
Stressed member.The passage that fluid is formed from suction surface 7 and the pressure face 8 of stator blade 1 flows through, near stator blade leading edge 5
Being divided into two parts by vitro vanelets 2, sub-fraction fluid is from leading between in vitro vanelets 2 and the suction surface 7 of stator blade 1
Road flows through, and air-flow, through accelerating, suppresses the wheel hub angular region stall occurred near stator blade trailing edge 6, thus alleviates low energy stream
Body is piled up, and effectively expands the circulation area of stator blade 1 wheel hub angular region.
Single-stage axial compressor is carried out the CFD Study on Numerical Simulation that the flowing of stator in vitro vanelets controls, has obtained
Data before and after single-stage axial compressor performance changes after in vitro vanelets suppression flow separation.
The single-stage compressor performance comparison before and after in vitro vanelets installed by table 1
Result of study shows that arranging in vitro vanelets at axial flow compressor stator blade can suppress flow separation effectively, expands
The big stable operation range of compressor, can be clear that by Fig. 3, and original stator blade inner fluid passage there occurs point
From, and after installing in vitro vanelets, air-flow isolated suppresses.Can find out intuitively with reference to table 1.Spinodal decomposition point flow from
2.826Kg/s be reduced to 2.722Kg/s.The flow nargin of the compressor stage not installing in vitro vanelets is 12.26%, arrange from
The flow nargin obtained after body vanelets is 15.49%, and flow nargin improvement is 3.23%.Further, the pressure ratio of compressor stage
It is not decreased obviously.The in vitro vanelets of invention expands steady technology makes compressor steady operation ability be enhanced.
Claims (4)
1. an axial flow compressor stator for the in vitro vanelets of wheel hub angular region band, including casing (4), stator blade (1), wheel hub
(3), it is characterised in that also including in vitro vanelets (2), described in vitro vanelets (2) is dual arc blade profile prismatic blade, is positioned at quiet
Between blades (1) and stator blade (1), and in vitro vanelets (2) does not contacts with stator blade (1)；In vitro vanelets (2) leaf
Root is connected with wheel hub (3), and the established angle of in vitro vanelets blade root is not more than the established angle of stator blade blade root.
The axial flow compressor stator of a kind of wheel hub angular region the most as claimed in claim 1 in vitro vanelets of band, it is characterised in that edge
Wheel hub (3) axis direction, described in vitro vanelets (2) is axial with the blade root that distance is 5%-15% of stator blade (1) leading edge
Chord length；The blade root that distance is 5%-10% along wheel hub (3) circumferential direction, in vitro vanelets (2) and stator blade (1) suction surface
Axially chord length.
The axial flow compressor stator of a kind of wheel hub angular region the most as claimed in claim 1 in vitro vanelets of band, it is characterised in that institute
The blade profile bent angle stating in vitro vanelets (2) is 30 °-60 °.
4. the axial flow compressor stator of a kind of wheel hub angular region in vitro vanelets of band as described in claim 1 or 3, its feature exists
In the 40%-60% that leaf a height of stator blade leaf of, described in vitro vanelets is high.In vitro vanelets blade root chord length is stator blade
The 5%-10% of blade root chord length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610259830.5A CN105864105A (en) | 2016-04-25 | 2016-04-25 | Axial flow compressor stator with in-vitro small blades in hub corner area |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610259830.5A CN105864105A (en) | 2016-04-25 | 2016-04-25 | Axial flow compressor stator with in-vitro small blades in hub corner area |
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|---|---|
| CN105864105A true CN105864105A (en) | 2016-08-17 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610259830.5A Pending CN105864105A (en) | 2016-04-25 | 2016-04-25 | Axial flow compressor stator with in-vitro small blades in hub corner area |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106481369A (en) * | 2016-11-01 | 2017-03-08 | 南京航空航天大学 | A kind of shunting leaflet structure controlling stators flow separation |
| CN106762825A (en) * | 2016-12-07 | 2017-05-31 | 浙江理工大学 | Axial flow blower 3 d impeller with leaf vein texture and circular arc post splitterr vanes |
| CN110159358A (en) * | 2018-02-14 | 2019-08-23 | 中国航发商用航空发动机有限责任公司 | Casing between grade |
| CN110701111A (en) * | 2019-10-25 | 2020-01-17 | 江汉大学 | Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane |
| CN111156201A (en) * | 2019-12-30 | 2020-05-15 | 江汉大学 | Axial flow fan and guide vane thereof |
| CN112228403A (en) * | 2020-10-12 | 2021-01-15 | 中国民航大学 | Compressor stator blade cascade with equal-depth grooves formed in end wall |
| CN114109918A (en) * | 2021-11-26 | 2022-03-01 | 中国民航大学 | Compressor stator blade cascade with small oblique ribs on suction surface |
| CN114718907A (en) * | 2022-04-21 | 2022-07-08 | 珠海格力电器股份有限公司 | Two-stage axial diffuser, pneumatic component, dust collector and compressor |
| CN115186401A (en) * | 2022-06-15 | 2022-10-14 | 中国船舶重工集团公司第七0三研究所 | Method for determining subsonic cascade modeling key angle parameters of axial flow compressor |
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| CN1249408A (en) * | 1998-09-30 | 2000-04-05 | 东芝开利株式会社 | Axial blower |
| CN101173672A (en) * | 2007-11-29 | 2008-05-07 | 北京航空航天大学 | Big and small impeller vane impeller with non-full height small blade and compressor machine |
| EP2096320A1 (en) * | 2006-12-18 | 2009-09-02 | IHI Corporation | Cascade of axial compressor |
| CN102022378A (en) * | 2010-12-23 | 2011-04-20 | 北京航空航天大学 | Small or small vane impeller with blunt trailing edge structure used in vane compressor |
| US20140328675A1 (en) * | 2013-05-03 | 2014-11-06 | Techspace Aero S.A. | Axial Turbomachine Stator with Ailerons at the Blade Roots |
| CN105422186A (en) * | 2015-12-18 | 2016-03-23 | 清华大学 | Axial flow type turbine with small blade structure |
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2016
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1249408A (en) * | 1998-09-30 | 2000-04-05 | 东芝开利株式会社 | Axial blower |
| EP2096320A1 (en) * | 2006-12-18 | 2009-09-02 | IHI Corporation | Cascade of axial compressor |
| CN101173672A (en) * | 2007-11-29 | 2008-05-07 | 北京航空航天大学 | Big and small impeller vane impeller with non-full height small blade and compressor machine |
| CN102022378A (en) * | 2010-12-23 | 2011-04-20 | 北京航空航天大学 | Small or small vane impeller with blunt trailing edge structure used in vane compressor |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106481369B (en) * | 2016-11-01 | 2018-07-17 | 南京航空航天大学 | A kind of shunting leaflet structure of control aero-turbine stator blade flow separation |
| CN106481369A (en) * | 2016-11-01 | 2017-03-08 | 南京航空航天大学 | A kind of shunting leaflet structure controlling stators flow separation |
| CN106762825B (en) * | 2016-12-07 | 2023-05-09 | 浙江理工大学 | Axial flow fan ternary impeller with vein structure and circular arc column splitter blade |
| CN106762825A (en) * | 2016-12-07 | 2017-05-31 | 浙江理工大学 | Axial flow blower 3 d impeller with leaf vein texture and circular arc post splitterr vanes |
| CN110159358A (en) * | 2018-02-14 | 2019-08-23 | 中国航发商用航空发动机有限责任公司 | Casing between grade |
| CN110701111A (en) * | 2019-10-25 | 2020-01-17 | 江汉大学 | Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane |
| CN110701111B (en) * | 2019-10-25 | 2021-02-09 | 江汉大学 | Method for reducing total pressure loss of guide vane of axial flow fan by using splitter vane |
| CN111156201A (en) * | 2019-12-30 | 2020-05-15 | 江汉大学 | Axial flow fan and guide vane thereof |
| CN112228403A (en) * | 2020-10-12 | 2021-01-15 | 中国民航大学 | Compressor stator blade cascade with equal-depth grooves formed in end wall |
| CN114109918A (en) * | 2021-11-26 | 2022-03-01 | 中国民航大学 | Compressor stator blade cascade with small oblique ribs on suction surface |
| CN114109918B (en) * | 2021-11-26 | 2024-01-23 | 中国民航大学 | Compressor stator blade grid with small inclined ribs on suction surface |
| CN114718907A (en) * | 2022-04-21 | 2022-07-08 | 珠海格力电器股份有限公司 | Two-stage axial diffuser, pneumatic component, dust collector and compressor |
| CN115186401A (en) * | 2022-06-15 | 2022-10-14 | 中国船舶重工集团公司第七0三研究所 | Method for determining subsonic cascade modeling key angle parameters of axial flow compressor |
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Application publication date: 20160817 |