CN105156361A - Compressor stator cascade with blade root provided with equal-width circular arc shaped channels - Google Patents
Compressor stator cascade with blade root provided with equal-width circular arc shaped channels Download PDFInfo
- Publication number
- CN105156361A CN105156361A CN201510583793.9A CN201510583793A CN105156361A CN 105156361 A CN105156361 A CN 105156361A CN 201510583793 A CN201510583793 A CN 201510583793A CN 105156361 A CN105156361 A CN 105156361A
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- Prior art keywords
- compressor stator
- cascade
- channels
- blade root
- suction surface
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Classifications
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- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
-
- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a compressor stator cascade with a blade root provided with equal-width circular arc shaped channels, relating to passive flow control technology in the technical field of turbo-machinery. The adverse pressure gradient resistance is stronger, Coanda effects are additionally brought and corner separation is better inhibited by forming the equal-width circular arc shaped channels in an end wall of the blade root of the compressor stator cascade from a pressure surface to a suction surface, forming high-speed jet by utilizing self-differential pressure of blades, increasing the kinetic energy of low energy fluid at a corner and blowing down airflows on boundary layers of the suction surface and the end wall. The compressor stator cascade is characterized in that the channels are formed in the end wall of the blade root of the compressor stator cascade; the spanwise height is a constant value; the number of the channels can be one or multiple; inlets of the channels are formed in the pressure surface of the stator cascade and outlets are formed in the suction surface of the cascade; center lines of the channels are shaped like circular arcs; the two sides of the channels are equally distant from the center lines; and the outlets in the side walls of the channels are tangent to the downstream wall of the suction surface of the cascade. The compressor stator cascade has the beneficial effects of effectively inhibiting corner separation, increasing the cascade flow capacity, reducing the total pressure loss and increasing the pressure diffusion capacity.
Description
Technical field
The present invention relates to Profile For Compressor Stator Cascade Flow to control, particularly relate to a kind of flowing control program suppressing the Profile For Compressor Stator leaf grating blade root of Profile For Compressor Stator corner separation to be slotted, belong to the passive flow control technique of impeller machinery technical field.
Background technique
In the internal flow of turbomachine, the flowing of the most complicated is angular region, there is end-wall boundary layer, blade boundary layer, various vortex structure and interaction thereof in the corner region flow between suction surface and end wall, is the principal element causing Profile For Compressor Stator penalty.The flow separation of angular region can cause channel blockage, blade loading and diffusion ability to decline, thus causes pitot loss and decrease in efficiency, can cause engine surge time serious.It is comparatively large that Profile For Compressor Stator corner region flow is lost in the proportion that accounts in the total losses of level, therefore, manages to suppress Profile For Compressor Stator corner separation to be the important channel reducing angular region loss and delay the engine performance deterioration problem caused due to corner separation.
At present, the flow control technique for Profile For Compressor Stator corner separation and stall mainly can be divided into ACTIVE CONTROL and the large class of Passive Control two.Active control technology mainly contains plasma excitation, boundary layer blow-suck technology, synthesizing jet-flow etc.; Passive Control technology mainly contains vortex generator, wing fence, end wall moulding etc.These controlling methods all pros and cons coexist, and angular region controlling method also needs further research.
Our seminar proposes technology (the gas turbine Testing and research that blade root fluting controls leaf grating corner separation early stage, 2007, Vol.20, No.3,28-33), slot Profile For Compressor Stator leaf grating blade root, the pressure reduction between blade pressure surface and suction surface is utilized to form jet, increase the low energy fluid kinetic energy of angular region, blow down the air-flow of blade suction surface and end-wall boundary layer, thus suppress corner separation.Specific implementation method is: on blade pressure surface and suction surface, diverse location gets some A, B and C, D first respectively, and recycling circular sliding slopes AC and BD forms conduit.At least there is following shortcoming in above-mentioned technology: for engineer applied, and fluting project plan comparison is partially idealized, connects circular arc relatively more random, bad processing; Especially the effluxvelocity direction formed is uncontrollable, may produce " step " comparatively greatly and flows thus produce negative effects, make control program be difficult to optimal design with main flow direction angle.
Summary of the invention
The object of the invention is to, propose a kind of being easy to and process, conveniently to the blade root fluting controlling method that the control Profile For Compressor Stator leaf grating corner separation of geometric Parameters Optimization Design flows.
Technological scheme of the present invention is as follows:
Conduit is offered at the blade root end wall place of axial-flow compressor stator leaf grating.
The exhibition of described conduit to being highly steady state value, and get leaf grating height 2% to 20% between value.
Described conduit can have one or more.
Described conduit import is positioned at Profile For Compressor Stator leaf grating pressure side.
Described channel outlet is positioned at Profile For Compressor Stator leaf grating suction surface.
The axial position at described conduit import place is positioned at the axial position upstream at channel outlet place.
Described conduit center line is circular arc, and conduit two side and center line equidistant.
Described channel sidewalls outlet is tangent with leaf grating suction surface downstream wall.
Beneficial effect of the present invention is: by offering wide circular arc conduit from pressure towards suction surface at Profile For Compressor Stator leaf grating blade root end wall place, the pressure reduction between blade pressure itself face and suction surface is utilized to form high-speed jet, increase the kinetic energy of angular region low energy fluid, make its opposing negative sequence harmonic ability stronger, avoiding flowing forms corner separation too early; High-velocity fluid has blown down suction surface boundary layer and end-wall boundary layer air-flow, and make the thinning acceleration of air stream on accompany surface, boundary layer velocity profile is fuller, and opposing negative sequence harmonic ability is stronger, suppresses the flow separation of suction surface and end wall; Channel sidewalls outlet is tangent with leaf grating suction surface downstream wall, make high-speed jet velocity attitude also basic and suction surface downstream wall is tangent, thus also additionally bring Coanda effect, produce very strong jet attached flow, add " circular rector ", also can suppress corner separation better.Thus increase leaf grating negotiability, reduce pitot loss, increase diffusion ability.
Compared with the control technique proposed early stage with our seminar, wide circular arc conduit center line of the present invention is circular arc, conduit perpendicular to end wall wall and with center line equidistantly, channel outlet and leaf grating suction surface downstream tangent, conduit smooth transition, is beneficial to processing; And high-speed jet velocity attitude is controlled, be easy to the optimal design of fluting scheme, and bring extra Coanda effect, have better corner separation inhibition.
Accompanying drawing explanation
Fig. 1 is that blade root offers wide arc groove Profile For Compressor Stator cascade structure schematic diagram.
Fig. 2 is that blade root offers wide arc groove Profile For Compressor Stator leaf grating conduit cross sectional representation.
Fig. 3 is that blade root offers wide circular arc conduit Profile For Compressor Stator leaf grating along leaf grating exhibition to schematic diagram.
Fig. 4 is that blade root does not offer the prototype leaf grating leaf grating surface of wide arc groove and the streamline chart of end wall.
Fig. 5 is that blade root offers the Profile For Compressor Stator leaf grating leaf grating surface of wide arc groove and the streamline chart of end wall.
Fig. 6 is the prototype cascade performance comparative bid parameter that blade root offers that the owner pressure difference jet Profile For Compressor Stator leaf grating of wide arc groove and blade root do not offer conduit.
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described.
As shown in Figure 1, blade root offers wide arc groove Profile For Compressor Stator leaf grating, at leaf grating 1 root end wall 2 place, offers wide circular arc conduit 5 from leaf grating 1 pressure side 3 to suction surface 4.
As shown in Figure 2, according to PVD prototype stator cascade flow field situation, conduit 5 is before the position of suction surface 4 upper outlet is chosen at separation point; Along cascade axis to, conduit 5 is positioned at upstream, suction surface 4 exit position in the position of pressure side 3 upper inlet; According to PVD prototype stator leaf grating surface pressure distribution, conduit 5 is selected in pressure side 3 upper surface static pressure larger part in the position of pressure side 3 upper inlet; Conduit 5 two side is 3.6% axial chord length apart from the distance of center line, and according to actual conditions, this value can adjust between 0.5% to 6%.
As shown in Figure 3, conduit 5 to contour, is 10% leaf exhibition height in exhibition, can adjust according to this value of actual conditions between 2% to 20% leaf exhibition height.
In order to verify effect of the present invention, the present inventor does not offer to blade root the Profile For Compressor Stator leaf grating that the PVD prototype leaf grating of conduit and blade root offer wide arc groove and has carried out numerical simulation.Physical simulation parameter and result as follows:
PVD Cascade Blade Profile parameter for simulating is as shown in the table:
As shown in Figure 4, Figure 5, can be found by the streamline chart of suction surface 4 and end wall 2 before and after contrast fluting, compared with the PVD prototype leaf grating that the blade root Profile For Compressor Stator leaf grating of offering wide arc groove and blade root do not offer conduit, the separated flow region that fluting rear end wall is formed obviously reduces, therefore blade root is offered wide arc groove and can delay and the generation of control separation.
As shown in Figure 6, by the result of the total pressure loss coefficient of numerical simulation, deviation angle and pressure ratio, can find out, fluting shape is that the blade root fluting Profile For Compressor Stator leaf grating of wide circular arc is compared with prototype leaf grating, total pressure loss coefficient reduces 56.52%, pressure ratio adds 0.039%, and deviation angle reduces 78.91%.
Visible, blade root of the present invention offers the design proposal of the Profile For Compressor Stator leaf grating of wide arc groove, by improving end wall bounda layer flow condition from leaf grating pressure side to leaf grating suction surface fluting jet, reducing end wall separated region area, achieving the object suppressing corner separation.And then reduce the loss that corner separation causes, reduce pitot loss, increase pressure ratio, reduce deviation angle, be conducive to improving Capability of Compressor and stability thereof.
Claims (1)
1. an axial-flow compressor stator leaf grating, is characterized in that:
Conduit (5) is offered at blade root end wall (2) place of axial-flow compressor stator leaf grating (1),
Wherein, described conduit (5) exhibition to being highly steady state value, and get leaf grating height 2% to 20% between value,
Described conduit (5) can have one or more,
Described conduit (5) import is positioned at Profile For Compressor Stator leaf grating (1) pressure side (3),
Described conduit (5) outlet is positioned at Profile For Compressor Stator leaf grating (1) suction surface (4),
Described conduit (5) import place axial position is positioned at conduit (5) outlet axial position upstream, place,
Described conduit (5) center line is circular arc, and conduit (5) two side and center line are equidistantly,
Described channel sidewalls outlet is tangent with leaf grating suction surface downstream.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510583793.9A CN105156361B (en) | 2015-09-14 | 2015-09-14 | Blade root opens up the Profile For Compressor Stator leaf grating of wide arc groove |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510583793.9A CN105156361B (en) | 2015-09-14 | 2015-09-14 | Blade root opens up the Profile For Compressor Stator leaf grating of wide arc groove |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105156361A true CN105156361A (en) | 2015-12-16 |
| CN105156361B CN105156361B (en) | 2017-05-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510583793.9A Active CN105156361B (en) | 2015-09-14 | 2015-09-14 | Blade root opens up the Profile For Compressor Stator leaf grating of wide arc groove |
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| CN (1) | CN105156361B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105756719A (en) * | 2016-01-08 | 2016-07-13 | 北京航空航天大学 | Gas compressor stator blade root slotting method based on optimization algorithm |
| CN112228401A (en) * | 2020-09-30 | 2021-01-15 | 大连海事大学 | Slotted vane diffuser |
| CN112610283A (en) * | 2020-12-17 | 2021-04-06 | 哈尔滨工业大学 | Turbine blade cascade designed by adopting end wall partition modeling |
| CN113418716A (en) * | 2021-06-05 | 2021-09-21 | 西北工业大学 | Blade cascade experimental device with adjustable blade top clearance |
Citations (6)
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| CN101092978A (en) * | 2007-07-30 | 2007-12-26 | 北京航空航天大学 | Synergic action device of preventing breath heavily and expanding stability of airbleed inside stator of multistage axial flow air compresdsor |
| CN101871466A (en) * | 2010-05-13 | 2010-10-27 | 北京航空航天大学 | Multi-blade row circular blown-suck air flowing control method for compression system of aviation turbofan engine |
| CN202266500U (en) * | 2011-09-01 | 2012-06-06 | 西北工业大学 | Gas compressor stator blade with pressure surface suction |
| CN103321960A (en) * | 2013-07-12 | 2013-09-25 | 西北工业大学 | Compressor stator blade with suction surface provided with suction grooves |
| CN103410779A (en) * | 2013-08-30 | 2013-11-27 | 哈尔滨工业大学 | Flow separation method for stationary cascade of high-load axial flow air compressor |
| JP2014020293A (en) * | 2012-07-19 | 2014-02-03 | Panasonic Corp | Compressor |
-
2015
- 2015-09-14 CN CN201510583793.9A patent/CN105156361B/en active Active
Patent Citations (6)
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| CN101092978A (en) * | 2007-07-30 | 2007-12-26 | 北京航空航天大学 | Synergic action device of preventing breath heavily and expanding stability of airbleed inside stator of multistage axial flow air compresdsor |
| CN101871466A (en) * | 2010-05-13 | 2010-10-27 | 北京航空航天大学 | Multi-blade row circular blown-suck air flowing control method for compression system of aviation turbofan engine |
| CN202266500U (en) * | 2011-09-01 | 2012-06-06 | 西北工业大学 | Gas compressor stator blade with pressure surface suction |
| JP2014020293A (en) * | 2012-07-19 | 2014-02-03 | Panasonic Corp | Compressor |
| CN103321960A (en) * | 2013-07-12 | 2013-09-25 | 西北工业大学 | Compressor stator blade with suction surface provided with suction grooves |
| CN103410779A (en) * | 2013-08-30 | 2013-11-27 | 哈尔滨工业大学 | Flow separation method for stationary cascade of high-load axial flow air compressor |
Non-Patent Citations (1)
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| 周敏,王如根,白云,曾令君: "《静子叶片开槽处理对单级压气机特性影响的数值研究》", 《空气动力学学报》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105756719A (en) * | 2016-01-08 | 2016-07-13 | 北京航空航天大学 | Gas compressor stator blade root slotting method based on optimization algorithm |
| CN112228401A (en) * | 2020-09-30 | 2021-01-15 | 大连海事大学 | Slotted vane diffuser |
| CN112610283A (en) * | 2020-12-17 | 2021-04-06 | 哈尔滨工业大学 | Turbine blade cascade designed by adopting end wall partition modeling |
| CN112610283B (en) * | 2020-12-17 | 2023-01-06 | 哈尔滨工业大学 | Turbine blade cascade designed by adopting end wall partition modeling |
| CN113418716A (en) * | 2021-06-05 | 2021-09-21 | 西北工业大学 | Blade cascade experimental device with adjustable blade top clearance |
| CN113418716B (en) * | 2021-06-05 | 2024-05-31 | 西北工业大学 | Blade cascade experimental device with adjustable blade top gap |
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| Publication number | Publication date |
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| CN105156361B (en) | 2017-05-31 |
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