CN105179322A - Gas compressor stationary blade cascade with equal-width linear groove formed in blade root - Google Patents
Gas compressor stationary blade cascade with equal-width linear groove formed in blade root Download PDFInfo
- Publication number
- CN105179322A CN105179322A CN201510583792.4A CN201510583792A CN105179322A CN 105179322 A CN105179322 A CN 105179322A CN 201510583792 A CN201510583792 A CN 201510583792A CN 105179322 A CN105179322 A CN 105179322A
- Authority
- CN
- China
- Prior art keywords
- leaf grating
- gas compressor
- groove
- blade cascade
- cascade
- Prior art date
- 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.)
- Granted
Links
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
- F04D29/66—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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a gas compressor stationary blade cascade with an equal-width linear groove formed in a blade root and relates to the passive flow control technology in the technical field of turbomachinery. By means of the gas compressor stationary blade cascade, the equal-width linear groove is formed in the blade root end wall of the gas compressor stationary blade cascade from the pressure face to suction face, and jet flow is formed through detour flow pressure differentials of a blade, so that flow separation is restrained and delayed. The groove is located in the blade root end wall of the gas compressor stationary blade cascade. The spanwise height is a constant value. The inlet of the groove is located in the pressure face of the stationary blade cascade. The outlet of the groove is located in the suction face of the blade cascade. The center line of the groove is a straight line and equidistant from the two side walls of the groove. The gas compressor stationary blade cascade has the beneficial effects that corner separation is restrained; the flow capacity of the blade cascade is increased; the total pressure loss is reduced; the diffusion capacity is improved.
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 it is relatively more random that fluting scheme connects circular arc, bad processing; Controling parameters is too many, and lacks design criterion, and control program is also difficult to optimal design.
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;
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 and blade connection all round-corner transitions;
Described conduit center line is straight line, and conduit two side and center line equidistant.
It should be noted that, open wide straight-line groove in this paper, according to the analysis controlling front cascade flow field, provide better control program fast.The specific design criterion corresponding with this controlling method is as follows: according to the flow field analysis of original leaf grating result of calculation, first determine effluxvelocity V and jet flow m, based on effluxvelocity V, pressure differential deltap p=P1-P2 (the low speed leaf grating of pressure side needed for inverse and suction surface, general Mach number is less than 0.3) or pressure ratio Pt=P1/P2 (high speed leaf grating, general Mach number is less than 0.3), thus determine pressure side slotting position (corresponding pressure P1) and suction surface slotting position (corresponding pressure P2), then obtain groove width according to flow m and effluxvelocity V.So, preliminary control program can be obtained very fast, easily carry out fluting optimal design on this basis.
Beneficial effect of the present invention is: by offering wide straight-line groove from pressure towards suction surface at Profile For Compressor Stator leaf grating blade root end wall place, utilizes the pressure reduction between blade pressure itself face and suction surface to form high-speed jet.High-speed jet adds the kinetic energy of angular region low energy fluid, and 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.Suppress corner separation, thus increase leaf grating negotiability, reduce pitot loss, increase diffusion ability.
Compared with the control technique proposed early stage with our seminar, wide straight-line groove has the advantage being easy to process; And give corresponding design criterion, control program proposal plan can be carried out fast, easily be optimized design, there is good future in engineering applications.
Accompanying drawing explanation
Fig. 1 is the Profile For Compressor Stator cascade structure schematic diagram that blade root offers wide straight-line groove.
Fig. 2 is the Profile For Compressor Stator leaf grating conduit cross sectional representation that blade root offers wide straight-line groove.
Fig. 3 is that blade root offers the Profile For Compressor Stator leaf grating of wide straight-line groove along leaf grating exhibition to schematic diagram.
Fig. 4 is that blade root does not offer the prototype leaf grating leaf grating surface of conduit 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 straight-line groove and the streamline chart of end wall.
Fig. 6 is the prototype cascade performance comparative bid parameter that blade root offers that the Profile For Compressor Stator leaf grating of wide straight-line 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 the Profile For Compressor Stator leaf grating of wide straight-line groove, at leaf grating 1 root end wall 2 place, offers wide straight-line groove 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 Profile For Compressor Stator leaf grating that the PVD prototype leaf grating of straight-line groove and blade root offer wide straight-line 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 straight-line groove and blade root do not offer conduit, the separated flow region that slot suction surface and end wall surface are formed obviously reduces, therefore blade root is offered wide straight-line 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 wide rectilinear blade root fluting Profile For Compressor Stator leaf grating is compared with prototype leaf grating, total pressure loss coefficient reduces 18.07%, deviation angle reduces 38.74%, and pressure ratio adds 0.033%.
Visible, blade root of the present invention offers the design proposal of the owner pressure difference jet Profile For Compressor Stator leaf grating of wide straight-line groove, improved the flow condition of leaf grating suction surface and end wall bounda layer by fluting jet, reduce 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),
Wherein, 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 straight line, and conduit (5) two side and center line equidistant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510583792.4A CN105179322B (en) | 2015-09-14 | 2015-09-14 | Blade root opens up the Profile For Compressor Stator leaf grating of wide straight-line groove |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510583792.4A CN105179322B (en) | 2015-09-14 | 2015-09-14 | Blade root opens up the Profile For Compressor Stator leaf grating of wide straight-line groove |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105179322A true CN105179322A (en) | 2015-12-23 |
| CN105179322B CN105179322B (en) | 2017-08-25 |
Family
ID=54901652
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510583792.4A Active CN105179322B (en) | 2015-09-14 | 2015-09-14 | Blade root opens up the Profile For Compressor Stator leaf grating of wide straight-line groove |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105179322B (en) |
Cited By (5)
| 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 |
| CN107152419A (en) * | 2017-07-24 | 2017-09-12 | 北京航空航天大学 | A kind of big bending angle compressor stator blade of root series connection multistage blade profile |
| CN107965473A (en) * | 2016-10-19 | 2018-04-27 | Ifp新能源公司 | Diffuser for a fluid compression device comprising at least one blade with an opening |
| CN111271322A (en) * | 2018-12-05 | 2020-06-12 | 中国航发商用航空发动机有限责任公司 | Adjustable stationary blade, air compressor and blade tip flow field adjusting method |
| CN112228401A (en) * | 2020-09-30 | 2021-01-15 | 大连海事大学 | Slotted vane diffuser |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 CN201510583792.4A patent/CN105179322B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 (3)
| Title |
|---|
| 周敏,: "静子叶片开槽处理对单机压气机特性影响的数值研究", 《空气动力学学报》 * |
| 王靖超: "端部开槽叶栅流场及强度分析", 《硕士论文集》 * |
| 穆小强、陆利蓬: "叶根开槽叶栅对角区分离的控制", 《燃气涡轮试验与研究》 * |
Cited By (7)
| 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 |
| CN107965473A (en) * | 2016-10-19 | 2018-04-27 | Ifp新能源公司 | Diffuser for a fluid compression device comprising at least one blade with an opening |
| US10995770B2 (en) | 2016-10-19 | 2021-05-04 | IFP Energies Nouvelles | Diffuser for a fluid compression device, comprising at least one vane with opening |
| CN107965473B (en) * | 2016-10-19 | 2021-07-27 | Ifp新能源公司 | Diffuser for a fluid compression device comprising at least one blade with an opening |
| CN107152419A (en) * | 2017-07-24 | 2017-09-12 | 北京航空航天大学 | A kind of big bending angle compressor stator blade of root series connection multistage blade profile |
| CN111271322A (en) * | 2018-12-05 | 2020-06-12 | 中国航发商用航空发动机有限责任公司 | Adjustable stationary blade, air compressor and blade tip flow field adjusting method |
| CN112228401A (en) * | 2020-09-30 | 2021-01-15 | 大连海事大学 | Slotted vane diffuser |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105179322B (en) | 2017-08-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106250652B (en) | A kind of construction method and compressor blade of compressor blade blade profile | |
| CN105179322A (en) | Gas compressor stationary blade cascade with equal-width linear groove formed in blade root | |
| CN111255744B (en) | Micro-air injection method for controlling flow separation of suction surface of compressor/fan stator blade | |
| CN105756719B (en) | A kind of Profile For Compressor Stator blade root grooving method based on optimized algorithm | |
| Dinh et al. | Effects of a circumferential feed-back channel on aerodynamic performance of a single-stage transonic axial compressor | |
| CN103807201A (en) | Combined suction layout method for controlling compressor stator corner separation | |
| CN108661947A (en) | Using the axial flow compressor blade of Condar jet and using its axial flow compressor | |
| CN105156361A (en) | Compressor stator cascade with blade root provided with equal-width circular arc shaped channels | |
| CN105240322B (en) | A kind of axial-flow compressor stator leaf grating | |
| Hopfinger et al. | Preliminary design of a three-stage low-speed research compressor using tandem vanes | |
| Yang et al. | Numerical investigation of a cantilevered compressor stator at varying clearance sizes | |
| CN105156356B (en) | Blade root opens up the Profile For Compressor Stator leaf grating of wide broken line groove | |
| CN110030038A (en) | Consider the asymmetric stator design method of blade tip transonic fan of BLI inlet distortion effect | |
| Pham et al. | Parametric study on aerodynamic performance of a single-stage transonic axial compressor with recirculation-bleeding channels | |
| Agarwal et al. | Numerical investigation on the effect of vortex generator on axial compressor performance | |
| Sun et al. | Control of corner separation to enhance stability in a linear compressor cascade by boundary layer suction | |
| Teng et al. | The influence of geometry deformation on a multistage compressor | |
| Zhang et al. | Effect of axial short slot casing treatment and its center deviation on stability of a transonic axial flow compressor | |
| Vera et al. | Separation and Transition Control on an Aft-Loaded Ultra-High-Lift LP Turbine Blade at low Reynolds Numbers: High-Speed Validation | |
| Ma et al. | Impact of a combination of micro-vortex generator and boundary layer suction on performance in a high-load compressor cascade | |
| CN105298925A (en) | Blade root slotting gas compressor stator with gradual-contraction changes of slot span-wise height | |
| Saathoff et al. | Endwall boundary layer separation in a single-stage axial-flow low-speed compressor and a high-stagger compressor cascade | |
| Sun et al. | Influence of tip clearance on centrifugal compressor IGV regulation and improvement | |
| Tran et al. | Aerodynamic Performance of a Single-stage Transonic Axial Compressor using a Hybrid Inclined Groove-Recirculation Casing Treatment | |
| CN106351872A (en) | Compressor rotor blade meeting both pneumatic and strength requirements |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |