CN105240322A - Method for forming S-shaped channels on blade root to control corner separation of compressor stator - Google Patents
Method for forming S-shaped channels on blade root to control corner separation of compressor stator Download PDFInfo
- Publication number
- CN105240322A CN105240322A CN201510741822.XA CN201510741822A CN105240322A CN 105240322 A CN105240322 A CN 105240322A CN 201510741822 A CN201510741822 A CN 201510741822A CN 105240322 A CN105240322 A CN 105240322A
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- China
- Prior art keywords
- conduit
- compressor stator
- channels
- leaf grating
- blade root
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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
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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
Abstract
The invention relates to a method for forming S-shaped channels on a blade root to control the corner separation of a compressor stator, relates to a passive flow control technology in the technical field of turbomachinery, and achieves the purposes that equally wide S channels are formed from a pressure surface to a suction surface on the blade root of the compressor stator, jet flow is formed by self round pressure drop of a blade, the low energy fluid kinetic energy of corners is increased, and air flow on the suction surface and a boundary layer of an end wall is blown off, so that the adverse pressure gradient resistance is stronger; and a coanda effect is additionally brought, so as to inhibit the corner separation better. The channels are formed in the end wall of the blade root of a blade cascade of the compressor stator, the spanwise height is a constant value, and the number of the channels can be one or more; and the inlets of the channels are formed in the pressure surface of the blade cascade, the outlets of the channels are formed in the suction surface of the blade cascade, the center lines of the channel are S-shaped, the distances between the two side walls and the center line of each channel are the same, and the airflow direction of the outlets of the channels is basically identical to the ideal non-separation streamline direction. The method has the beneficial effects of effectively inhibiting the corner separation, increasing the blade cascade flow capacity, reducing the total pressure loss, and increasing the 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 cascade performance to worsen.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 the plasma excitation of end wall and suction surface, boundary layer blow-suck technology etc.; Passive Control technology mainly contains eddy generator, wing fence, end wall moulding etc.These controlling methods all also also exist some problems, fail to solve the problem of high load gas compressor corner separation of future generation in engineering, also need further further investigation.
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, a kind of Profile For Compressor Stator leaf grating blade root grooving method being easy to process, the convenient fluting shape flowed to the control Profile For Compressor Stator leaf grating corner separation of geometric Parameters Optimization Design is S shape is proposed, to reach the effect reducing the loss of Profile For Compressor Stator leaf grating corner separation.
Technological scheme of the present invention is as follows:
Conduit is offered at the blade root place of axial-flow compressor stator leaf grating.
Wherein, 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 S shape, and conduit two side and center line equidistant.
The outlet of described channel sidewalls is tangent with leaf grating suction surface downstream wall, channel sidewalls entrance and leaf grating pressure side upstream wall tangent.
Other channel sidewalls described and leaf grating joint all adopt round-corner transition.
Beneficial effect of the present invention is: by offering wide S shape conduit from pressure towards suction surface at Profile For Compressor Stator leaf grating blade root 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 the ability of its opposing adverse pressure gradient stronger, avoid flowing premature disengagement to form the performance caused angular region and decline fast; 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; S shape conduit inlet velocity and main flow carry out flow path direction when reaching unanimity, conduit effective stream amount can be increased under the condition waiting conduit area, through S shape runner smooth transition, regulate flow-deviation angle in conduit, making channel outlet air-flow consistent without being separated grain direction with desirable, additionally bringing Coanda effect, carry main flow and produce very strong jet attached flow, add " circular rector ", suppress corner separation better, strengthen flowing control effects.Thus increase the negotiability of blade grid passage, reduce pitot loss, increase diffusion ability.
Compared with the control technique proposed early stage with our seminar, wide S shape conduit center line of the present invention is S shape smoothed curve, and conduit perpendicular to the wall of end wall and center line equidistantly, is beneficial to processing; S shape smoothed curve structure makes conduit import and export position and conduit imports and exports angle all energy free adjusting, is easy to the optimization of fluting scheme; Smooth transition reduces loss coefficient in conduit; 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 a kind of Profile For Compressor Stator structural representation suppressing the blade root of corner separation to offer S shape conduit.
Fig. 2 is a kind of Profile For Compressor Stator conduit cross sectional representation suppressing the blade root of corner separation to offer S shape conduit.
Fig. 3 is that a kind of Profile For Compressor Stator suppressing the blade root of corner separation to offer S shape conduit is along leaf grating exhibition to schematic diagram.
Fig. 4 is that blade root does not offer the PVD prototype stator leaf grating surface of conduit and the streamline chart of end wall.
Fig. 5 be a kind of suppress the blade root of corner separation to offer S shape conduit Profile For Compressor Stator leaf grating surface and the streamline chart of end wall.
Fig. 6 be a kind of suppress the blade root of corner separation to offer S shape conduit Profile For Compressor Stator and blade root do not offer the PVD prototype stator cascade performance comparative bid parameter of conduit.
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described.
As shown in Figure 1, a kind of Profile For Compressor Stator suppressing the blade root of corner separation to offer S shape conduit, at leaf grating 1 root end wall 2 place, offers wide S shape 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 1.5% 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 5% to 15% leaf exhibition height.
In order to verify effect of the present invention, it is that the blade root fluting Profile For Compressor Stator leaf grating of S shape has carried out numerical simulation that the present inventor does not offer the PVD prototype leaf grating of conduit and fluting shape to blade root.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, fluting shape be blade root fluting Profile For Compressor Stator leaf grating and the blade root of S shape do not offer conduit PVD prototype leaf grating compared with, slot suction surface surface and the separated flow region that formed of end wall surface obviously reduce, therefore blade root is offered wide S shape 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, a kind of Profile For Compressor Stator suppressing the blade root of corner separation to offer S shape conduit is compared with prototype stator leaf grating, total pressure loss coefficient reduces 65.55%, deviation angle reduces 79.73%, and pressure ratio adds 0.039%.
Visible, the blade root of suppression corner separation of the present invention offers the design proposal of the Profile For Compressor Stator of S shape conduit, by improving leaf grating suction surface and end wall bounda layer flow condition from leaf grating pressure side to leaf grating suction surface fluting jet, 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 diffusion ability, 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 the blade root place of axial-flow compressor stator leaf grating (1).
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 S shape, and conduit (5) two side and center line are equidistantly,
Described conduit (5) sidewall exit and leaf grating (1) suction surface (4) downstream wall tangent, conduit (5) side wall entrance and leaf grating (1) pressure side (3) upstream wall tangent,
Described other conduits (5) sidewall and leaf grating (1) joint all adopt round-corner transition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510741822.XA CN105240322B (en) | 2015-11-04 | 2015-11-04 | A kind of axial-flow compressor stator leaf grating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510741822.XA CN105240322B (en) | 2015-11-04 | 2015-11-04 | A kind of axial-flow compressor stator leaf grating |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105240322A true CN105240322A (en) | 2016-01-13 |
| CN105240322B CN105240322B (en) | 2017-08-22 |
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| CN201510741822.XA Active CN105240322B (en) | 2015-11-04 | 2015-11-04 | A kind of axial-flow compressor stator leaf grating |
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| CN (1) | CN105240322B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107762973A (en) * | 2017-10-20 | 2018-03-06 | 哈尔滨工程大学 | Steady blade and its trailing edge groove forming method are expanded in a kind of compressor angular region |
| CN108661947A (en) * | 2017-03-28 | 2018-10-16 | 中国科学院工程热物理研究所 | Using the axial flow compressor blade of Condar jet and using its axial flow compressor |
| CN108730230A (en) * | 2018-04-04 | 2018-11-02 | 大连依勒斯涡轮增压技术有限公司 | A kind of turbocharger and its centrifugal compressor |
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2015
- 2015-11-04 CN CN201510741822.XA patent/CN105240322B/en active Active
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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 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108661947A (en) * | 2017-03-28 | 2018-10-16 | 中国科学院工程热物理研究所 | Using the axial flow compressor blade of Condar jet and using its axial flow compressor |
| CN108661947B (en) * | 2017-03-28 | 2020-05-19 | 中国科学院工程热物理研究所 | Axial flow compressor blade adopting coanda jet and axial flow compressor applying axial flow compressor blade |
| CN107762973A (en) * | 2017-10-20 | 2018-03-06 | 哈尔滨工程大学 | Steady blade and its trailing edge groove forming method are expanded in a kind of compressor angular region |
| CN107762973B (en) * | 2017-10-20 | 2020-06-16 | 哈尔滨工程大学 | Compressor corner region stability-expanding blade and trailing edge groove forming method thereof |
| CN108730230A (en) * | 2018-04-04 | 2018-11-02 | 大连依勒斯涡轮增压技术有限公司 | A kind of turbocharger and its centrifugal compressor |
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| Publication number | Publication date |
|---|---|
| CN105240322B (en) | 2017-08-22 |
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