CN105156356A - Compressor stator cascade with blade root provided with equal-width broken line shaped channels - Google Patents
Compressor stator cascade with blade root provided with equal-width broken line shaped channels Download PDFInfo
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- CN105156356A CN105156356A CN201510583791.XA CN201510583791A CN105156356A CN 105156356 A CN105156356 A CN 105156356A CN 201510583791 A CN201510583791 A CN 201510583791A CN 105156356 A CN105156356 A CN 105156356A
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- Prior art keywords
- compressor stator
- channels
- cascade
- blade root
- conduit
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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
- F04D29/684—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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- 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
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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 broken line 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 broken line 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 cascade and outlets are formed in the suction surface of the cascade; center lines of the channels are multiple broken lines; the two sides of the channels are equally distant from the center lines; and the directions of airflows at the outlets of the channels are basically consistent with the directions of ideal non-separation flow lines. 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 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 multistage fold-line-shaped, and conduit two side and center line equidistant.
Described conduit and blade connection all round-corner transitions.
Beneficial effect of the present invention is: by offering wide fold-line-shaped 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; Conduit inducer and upstream come flow path direction basically identical time, conduit effective stream amount can be increased under the condition waiting conduit area.Channel outlet airflow direction with desirable without be separated grain direction basically identical time, additionally can bring Coanda effect, produce very strong jet attached flow, add " circular rector ", also can suppress corner separation better, strengthen the effect of flowing control.Thus increase leaf grating negotiability, reduce pitot loss, increase diffusion ability.
Compared with the control technique proposed early stage with our seminar, wide fold-line-shaped conduit center line of the present invention is multistage broken line, and conduit perpendicular to the wall of end wall and center line equidistantly, is beneficial to processing; Multistage meander line structure makes conduit import and export position and conduit imports and exports angle all energy free adjusting, is easy to the optimal design of fluting scheme; Channel outlet is basically identical without being separated grain direction with desirable, brings extra Coanda effect, has better corner separation inhibition.
Accompanying drawing explanation
Fig. 1 is the Profile For Compressor Stator cascade structure schematic diagram that blade root offers wide fold-line-shaped conduit.
Fig. 2 is the Profile For Compressor Stator leaf grating conduit cross sectional representation that blade root offers wide fold-line-shaped conduit.
Fig. 3 is that blade root offers the Profile For Compressor Stator leaf grating of wide fold-line-shaped conduit along leaf grating exhibition to schematic diagram.
Fig. 4 is that blade root does not offer the PVD prototype leaf grating leaf grating surface of wide fold-line-shaped conduit and the streamline chart of end wall.
Fig. 5 is that blade root offers the owner pressure difference jet Profile For Compressor Stator leaf grating leaf grating surface of wide fold-line-shaped conduit and the streamline chart of end wall.
Fig. 6 is the PVD prototype cascade performance comparative bid parameter that blade root offers that the Profile For Compressor Stator leaf grating of wide fold-line-shaped conduit 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 the Profile For Compressor Stator leaf grating of wide broken line groove, at leaf grating 1 root end wall 2 place, offers wide fold-line-shaped 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 4% 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 owner pressure difference jet Profile For Compressor Stator leaf grating that the PVD prototype leaf grating of conduit and blade root offer wide fold-line-shaped conduit 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 fold-line-shaped groove and blade root do not offer conduit, fluting rear end wall and the separated flow region that formed, leaf grating suction surface surface obviously reduce, therefore blade root is offered wide fold-line-shaped conduit 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 fold-line-shaped is compared with prototype leaf grating, total pressure loss coefficient reduces 55.95%, deviation angle reduces 81.57%, and pressure ratio adds 0.0382%.
Visible, blade root of the present invention offers the design proposal of the Profile For Compressor Stator leaf grating of wide fold-line-shaped conduit, by improving the flow condition of leaf grating suction surface and end wall bounda layer to leaf grating suction surface fluting jet from leaf grating pressure side, reduce leaf grating suction surface and end wall separated region area, achieve the object suppressing corner separation.And then reduce the loss that corner separation causes, reduce pitot loss and deviation angle, increase pressure ratio, 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),
The exhibition of described conduit 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) and Profile For Compressor Stator leaf grating (1) connection all round-corner transitions,
Described conduit (5) center line is multistage broken line, and conduit (5) two side and center line equidistant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510583791.XA CN105156356B (en) | 2015-09-14 | 2015-09-14 | Blade root opens up the Profile For Compressor Stator leaf grating of wide broken line groove |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510583791.XA CN105156356B (en) | 2015-09-14 | 2015-09-14 | Blade root opens up the Profile For Compressor Stator leaf grating of wide broken line groove |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105156356A true CN105156356A (en) | 2015-12-16 |
| CN105156356B CN105156356B (en) | 2017-12-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510583791.XA Active CN105156356B (en) | 2015-09-14 | 2015-09-14 | Blade root opens up the Profile For Compressor Stator leaf grating of wide broken line groove |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106996312A (en) * | 2016-01-26 | 2017-08-01 | 李仕清 | A kind of power blade |
| CN112955661A (en) * | 2019-07-22 | 2021-06-11 | 开利公司 | Centrifugal or mixed flow compressor comprising a suction diffuser |
| CN114087027A (en) * | 2021-11-23 | 2022-02-25 | 浙江燃创透平机械股份有限公司 | Gas turbine stationary blade with flow guide pipe |
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| JP2006144784A (en) * | 2004-11-16 | 2006-06-08 | General Electric Co <Ge> | Manufacturing method of repaired turbine engine stationary blade assembly, and repaired assembly |
| 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 |
| CN202266500U (en) * | 2011-09-01 | 2012-06-06 | 西北工业大学 | Gas compressor stator blade with pressure surface suction |
| CN202468447U (en) * | 2011-11-25 | 2012-10-03 | 中国航空工业集团公司沈阳发动机设计研究所 | Adsorption type hollow stator blade adopting T-shaped groove structure |
| 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 |
-
2015
- 2015-09-14 CN CN201510583791.XA patent/CN105156356B/en active Active
Patent Citations (6)
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| JP2006144784A (en) * | 2004-11-16 | 2006-06-08 | General Electric Co <Ge> | Manufacturing method of repaired turbine engine stationary blade assembly, and repaired assembly |
| 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 |
| CN202266500U (en) * | 2011-09-01 | 2012-06-06 | 西北工业大学 | Gas compressor stator blade with pressure surface suction |
| CN202468447U (en) * | 2011-11-25 | 2012-10-03 | 中国航空工业集团公司沈阳发动机设计研究所 | Adsorption type hollow stator blade adopting T-shaped groove structure |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106996312A (en) * | 2016-01-26 | 2017-08-01 | 李仕清 | A kind of power blade |
| CN112955661A (en) * | 2019-07-22 | 2021-06-11 | 开利公司 | Centrifugal or mixed flow compressor comprising a suction diffuser |
| CN114087027A (en) * | 2021-11-23 | 2022-02-25 | 浙江燃创透平机械股份有限公司 | Gas turbine stationary blade with flow guide pipe |
| CN114087027B (en) * | 2021-11-23 | 2024-02-27 | 浙江燃创透平机械有限公司 | Gas turbine stationary blade with honeycomb duct |
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| Publication number | Publication date |
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| CN105156356B (en) | 2017-12-22 |
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Inventor after: Lu Lipeng Inventor after: Tang Yumeng Inventor after: Liu Yangwei Inventor after: Sun Jinjing Inventor before: Liu Yangwei Inventor before: Tang Yumeng Inventor before: Lu Lipeng Inventor before: Sun Jinjing |
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