CN107742011A - The design method of the micro- texture of impeller blade drag reduction - Google Patents
The design method of the micro- texture of impeller blade drag reduction Download PDFInfo
- Publication number
- CN107742011A CN107742011A CN201710880615.1A CN201710880615A CN107742011A CN 107742011 A CN107742011 A CN 107742011A CN 201710880615 A CN201710880615 A CN 201710880615A CN 107742011 A CN107742011 A CN 107742011A
- Authority
- CN
- China
- Prior art keywords
- micro
- texture
- blade
- section
- drag reduction
- 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
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Engineering & Computer Science (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Computational Mathematics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of design method of the micro- texture of blade surface drag reduction, belong to blade drag reduction field.According to impeller blade model, flow field domain is established；Convection current field domain carries out numbered analog simulation, obtains the motion pattern of blade height direction intermediate cross-section, determines therefrom that blade pressure surface, boundary layer separation region and suction surface recirculation zone as micro- texture placement region；It is close to vane airfoil profile in micro- texture placement region and arranges micro- texture section, and it is scanned into rib or groove along blade height direction over the paddle；Leaf model to having rib or the micro- texture of groove is obtained the placement location and cross sectional shape of the best micro- texture of drag reduction, the micro- texture of blade surface drag reduction is constructed with this using the placement location and cross sectional shape of the micro- texture of finite element simulation optimization.The micro- texture drag reduction of blade surface drag reduction of optimization reaches 5% to 10%, reduces energy expenditure, has saved fuel resource, and the design method of the micro- texture of drag reduction can promote the use of other fields.
Description
Technical field
The present invention relates to a kind of design method of the micro- texture of impeller blade drag reduction, the blade being related to is mainly wind-force leaf
Piece, speed of incoming flow belong to blade drag reduction field between 50m/s to 100m/s.
Background technology
Turbomachinery has a wide range of applications in fields such as Aeronautics and Astronautics, the energy, traffic, chemical industry and oil.Blade is boat
The vital part of the turbomachineries such as empty engine, gas turbine, blower fan, its pneumatic drag reduction performance directly affect the work of this kind of product
Make performance.In order to improve the pneumatic drag reduction performance of blade, domestic and international experts and scholars have made a large amount of to the optimization design aspect of blade
Research work, from blade construction optimization, blade surface texture design etc. carried out substantial amounts of exploration, it is intended to from design source
Head improves the pneumatic drag reduction performance of turbomachinery.In various drag reduction technologies, bionical micro- knot of minute manufacturing technology preparation is utilized
There is prominent drag-reduction effect on structure surface, and this design with bionical micro-nano texture can be applied to the needs such as blade of aviation engine
In the field of drag reduction, specific function and the performances such as drag reduction are obtained by special Surface Texture, improve the function and performance of product.
At present, micro- texture drag reduction technology is applied in wing etc. in a fluid on the surface of high-speed moving object, and in engine leaf mostly
Seldom applied on piece, because the current micro- texture of blade drag reduction is mainly designed to according to research experience in blade whole table
The triangular groove or rib of face arrangement certain law arrangement, or have difference small by additionally adhering to one layer in blade surface
The glued membrane of structure, a kind of structure with drag-reduction effect is then gone out by experiment screening.It is but original after flow field state changes
Drag-reduction effect is likely to disappear.Therefore these design methods lack to the universality under different flow field states, and this is not only wasted
Substantial amounts of resource and time, and lack of targeted and flexibility.
The content of the invention
The present invention seeks to overcome prior art defect, a kind of simple possible is proposed, can be according to the actual work of different leaves
Make environment, a kind of design method of micro- texture with resistance reducing performance is designed on blade, improve the micro- texture design of drag reduction
Efficiency and flexibility.
To reach above purpose of design, the present invention relates to design procedure it is as follows：
Step 1)：According to impeller blade model, flow field domain is established.The feature in flow field domain is：The width W in flow field domain is impeller
Twice of adjacent blades circumferential distance；Flow field domain height H is 1~1.1 times of blade height；Flow field geometric locus 1 is to pass through plan
Hinge bottom and two profile mean lines on leaf top, bisector is sought, then obtained 2~3 times of tea residue chord lengths are respectively extended before and after this bisector
's.Features above can make the flow field state of the flow field state more approaching to reality in the flow field domain of design.
Step 2)：The gas-flow resistance that mesh generation and numerical simulation blade are subject to is carried out to the flow field domain obtained by step 1).
Step 3)：According to the numerical simulation result in step 2), intermediate cross-section is established in blade height direction centre position,
Obtain the fluid velocity motion pattern in this section.Determine therefrom that in pressure face, boundary layer separation region and suction surface recirculation zone three
Micro- texture section is arranged in block region.
Why in blade height direction centre position section is taken, be because turbulent flow development herein is the most obvious, accordingly
The micro- texture drag-reduction effect determined is best.Boundary layer separation region is arranged on, is because micro- texture herein can change incoming
The angle of attack, the separation in tail end boundary layer can be delayed, help to suppress the generation of turbulent flow, meet Aerodynamics.Micro- texture
Cross sectional shape is triangle or quadrangle, and wherein a line is close in the section aerofoil profile.The height h of micro- texture is in the section
Turbulence vortex ties up to out to out H in blade normal orientationmax4%~7%, but minimum constructive height is not less than 0.05mm, maximum height
No more than 1mm；Micro- texture of pressure face is arranged in the region that blade inlet edge goes forward 50% to trailing edge direction, because pressing
To be held in face of power, direction of flow is smaller with leaf angle, and the pressure drag brought by increasing micro- texture is less than reduced viscous drag,
Therefore drag overall reduces；And in rear end, due to blade twist, the direction of incoming and blade surface angle are excessive, micro- by increasing
The pressure drag that texture is brought is more than the viscous drag reduced, therefore drag overall can increase.Micro- texture of suction surface is arranged in suction
Go forward in the range of 50%, can so reduce the negative sequence harmonic of suction surface, contribute to from backflow start to finish direction in power face
Suppress the diffusion of turbulent flow.A micro- texture is only arranged in boundary layer separation region.In the micro- of pressure face and suction surface recirculation zone
Texture, wherein in the heart away from 1.5~2.5 times that l is height h；Micro- texture meets stream side and direction of flow angle theta at 50 degree to 90 degree
Between；Micro- texture of pressure face is groove structure, i.e., micro- texture section is in the aerofoil profile because in pressure face, mainly with
Based on laminar flow, air-flow can form micro- whirlpool in groove, substantially reduce viscous drag.And boundary layer separation region and suction surface
Recirculation zone be rib structure, micro- texture section protrusion is outside aerofoil profile.
Step 4)：Using micro- texture section of step 3) arrangement as bus, scanned over the paddle along blade height direction
Into rib or groove.Detailed process is：Establish a projection plane in blade suction surface, the plane parallel to blade height direction,
And parallel to the chord length direction of vane airfoil profile in intermediate cross-section.The base midpoint that will be created in step 3), i.e. base is micro- texture
The section length of side is located at one side in aerofoil profile.Make upright projection to projection plane.Make to pass through above subpoint in the projection plane
Straight parallel wire harness.The straight parallel wire harness start from tea residue to the high direction of leaf 5% position, end at 95% opening position.So
The straight parallel wire harness is projected to blade afterwards, obtains drop shadow curve.Using these drop shadow curves as guide line, with micro- texture section
For bus, groove and rib are scanned into, completes the establishment of micro- texture.
Step 5)：Numerical simulation is re-started to the leaf model that rib and the micro- texture of groove are had in step 4), calculated
The resistance that model is subject to, and the resistance with obtaining before is made comparisons.By constantly adjusting position and the cross sectional shape of micro- texture, with
Given drag reduction is used for optimization aim, the final micro- texture arrangement obtained with optimal resistance reducing performance.
Through Simulation, gas-flow resistance that micro- texture that the method is designed can be subject to blade reduces 5% and arrived
10%, therefore energy resource consumption is greatly reduced, save resource.
Brief description of the drawings
Fig. 1 is blade and flow field domain model figure；
Fig. 2 is intermediate cross-section motion pattern；
Fig. 3 is micro- texture layout drawing；
Fig. 4 is pressure face groove drag reduction mechanism；
Fig. 5 is the micro- texture illustraton of model of triangle rib of blade suction surface；
In figure：
W- flow fields field width degree；
H- flow fields domain height；
L- micro- texture sections base centre-to-centre spacing；
The micro- texture height of h-；
HmaxOut to out of the turbulent flow vortex system along aerofoil profile normal direction at-intermediate cross-section；
The angle of θ-air flow direction and micro- texture fluoran stream surface；
1- flow fields geometric locus；
2- profile mean lines；
The bisector that 3- is tried to achieve by being fitted profile mean line (2)；
4- intermediate cross-sections；
5- airfoil pressure sides；
6- boundary layer separations region；
7- airfoil suction sides；
8- aerofoil profiles；
9- Fig. 3 region；
10- aerofoil profile leading edges；
11- airfoil trailing edges；
12- flows back；
The micro- texture sections of 13-；
The micro- texture of 14- ribs；
15- projection planes；
16- straight parallel wire harness；
Embodiment
The blade of table 1 demonstrate,proves the point coordinate data of example
The numerical simulator parameter of table 2
| Title | Parameter |
| Entrance velocity (m/s) | 75 |
| Fluid | Perfect gas |
| Temperature (k) | 300 |
| Turbulence model | k-ε(2eqn)；Realizable |
| Wall-function | Enhanced Wall Treatment |
The micro- texture height h of table 3 and drag-reduction effect experimental result
| Micro- texture height h and HmaxRatio/% | Percent drag reduction/% |
| 3.6 | 3.1 |
| 4 | 5 |
| 4.4 | 6.1 |
| 4.8 | 6 |
| 5.2 | 5.5 |
| 5.6 | 4 |
| 6 | 3.1 |
| 6.4 | 1.1 |
| 6.8 | 0.5 |
| 7.2 | -1.3 |
The micro- texture center spacing l of table 4 and drag-reduction effect experimental result
5 micro- texture of table meets stream side and direction of flow angle theta and the experimental result of drag-reduction effect
| Micro- texture meet stream side and direction of flow angle theta/° | Percent drag reduction/% |
| 45 | 0.2 |
| 65 | 1.5 |
| 85 | 3.5 |
Below by taking a certain free form surface blade as an example, its point data is shown in Table 1.It is micro- to blade drag reduction of the present invention with reference to accompanying drawing
Texture design method is illustrated：
1) according to impeller blade model, flow field domain is established；
Such as Fig. 1, the width W in flow field domain is twice of impeller adjacent blades circumferential distance；Flow field domain height H is blade height
1.05 times；Flow field geometric locus 1 is by being fitted tea residue and two, leaf top profile mean line 2, trying to achieve bisector 3, then this is put down
Respectively extend what 2 times of tea residue chord lengths obtained before and after separated time 3.Features above can be such that the flow field state in the flow field domain of design more approaches
Real flow field state.
2) gas-flow resistance that mesh generation and numerical simulation blade are subject to is carried out to the flow field domain obtained by step 1).
The boundary condition and turbulence model that present case uses are shown in Table 2, and drag evaluation result is 41.692N.
3) according to the numerical simulation result in step 2), intermediate cross-section 4 is established in blade height direction centre position, is obtained
The fluid velocity motion pattern in this section, such as Fig. 2.Determine therefrom that in pressure face 5, boundary layer separation region 6 and suction surface recirculating zone
The 7 three pieces of regions in the domain micro- texture section of arrangement triangle.
Why in blade height direction centre position take intermediate cross-section 4, be because turbulent flow development herein is the most obvious,
The micro- texture drag-reduction effect determined therefrom that is best.Boundary layer separation region 6 is arranged on, is because micro- texture herein can change
The angle of attack of stream, the separation in tail end boundary layer can be delayed, help to suppress the generation of turbulent flow, meet Aerodynamics.It is micro- to knit
The cross sectional shape of structure is triangle, and wherein a line is close in the section aerofoil profile 8.As Fig. 3, the height h of micro- texture cut for this
Turbulence vortex ties up to out to out H in blade normal orientation in piecemax5%, be 0.2mm.Micro- texture of pressure face side is arranged in
In the region that blade inlet edge 10 goes forward 50% to the direction of trailing edge 11, because in pressure face front end, direction of flow is pressed from both sides with blade
Angle is smaller, and the pressure drag brought by increasing micro- texture is less than reduced viscous drag, therefore drag overall reduces；And in rear end,
Due to blade twist, the direction of incoming and blade surface angle are excessive, and the pressure drag brought by increasing micro- texture, which is more than, to be subtracted
Small viscous drag, therefore drag overall can increase.Micro- texture of suction surface recirculation zone is arranged in this region from backflow 12
Start to finish direction go forward 50% scope, can so reduce the negative sequence harmonic of suction surface, help to suppress the expansion of turbulent flow
Dissipate.A micro- texture is only arranged at boundary layer separation.Micro- texture of pressure face and suction surface recirculation zone, wherein being away from l in the heart
Height h 2 times of arrangements, meet the stream side and direction of flow angle theta of micro- texture are 60 degree.Micro- texture of pressure face is groove structure,
I.e. the micro- texture section of triangle is in aerofoil profile 8.Because in pressure face, mainly based on laminar flow, air-flow can be in groove
Micro- whirlpool is formed, substantially reduces viscous drag, such as Fig. 4.Micro- texture of boundary layer separation region and suction surface recirculation zone is
The micro- texture section of rib structure, i.e. triangle is in outside aerofoil profile.
4) swept over the paddle along blade height direction for bus with the micro- texture section 13 of triangle of step 3) arrangement
Plunder into triangle rib 14 or groove.
A projection plane 15 is established in blade suction surface side, the plane is parallel to blade height direction, and parallel in
Between in section 4 vane airfoil profile chord length direction.The triangle base midpoint that will be created in step 3), i.e. base is located at for triangle
One side in aerofoil profile.Make upright projection to projection plane 15.Make the straight parallel wire harness 16 by above subpoint in the plane.
The straight parallel wire harness start from tea residue to the high direction of leaf 5% position, end at 95% opening position.Then by the parallel lines
Beam projects to blade, obtains drop shadow curve.It is mother with the micro- texture section 13 of triangle using these drop shadow curves as guide line
Line, triangular groove and rib 14 are scanned into, complete the establishment of micro- texture, such as Fig. 5.
5) numerical simulation is re-started to the leaf model that triangle rib and the micro- texture of groove are had in step 4), calculated
The resistance that blade is subject to is 39.004N, reduces 6.447% compared with the resistance 41.692N obtained before.By by above-mentioned original
Position and the cross sectional shape of micro- texture are then adjusted, result is optimized, its optimal drag reducing efficiency can bring up to 8%.
What deserves to be explained is why flow field domain height H is arranged to 1~1.1 times of blade height, and flow field track song
Extending length of the line 1 on the both sides of bisector 3 is 2~3 times of tea residue chord length, is because when more than this scope, is obtained
As a result it is larger with true difference of comparing, even if still there is drag-reduction effect in this case.Drag reduction is imitated to probe into micro- texture height h
The influence of fruit, 8 groups of checking examples are carried out herein for case blade, the results are shown in Table 3.To probe into l pairs of micro- texture center spacing
The influence of drag-reduction effect, 7 groups of checking examples are carried out herein for case blade, the results are shown in Table 4.Stream side is met to probe into micro- texture
With the influence of the angle theta of direction of flow to drag-reduction effect, 5 groups of checking examples are carried out herein for case blade, the results are shown in Table
5.Using parameter above as when probing into object, other parameters are constant, and value is identical with case.Other types of blade has done similar calculation
Example checking, drag-reduction effect conclusion are similar.
The embodiment of the present invention is described above, but the present invention is not limited to above description.For this
For the technical staff in field, any equal modification and replacement to the technical program is all within the scope of the invention.Cause
This, the impartial conversion made without departing from the spirit and scope of the invention and modification, all should be contained within the scope of the invention.
Claims (1)
1. a kind of design method of the micro- texture of impeller blade drag reduction, it is characterised in that comprise the following steps：
Step 1)：According to impeller blade model, flow field domain is established, the feature in flow field domain is：The width W in flow field domain is that impeller is adjacent
Twice of blade circumferential distance；Flow field domain height H is 1~1.1 times of blade height；Flow field geometric locus (1) is to pass through fitting
Tea residue and two, leaf top profile mean line (2), bisector (3) is tried to achieve, then will respectively extend 2~3 times of tea residue strings before and after this bisector (3)
What length obtained；
Step 2)：Numerical simulation is carried out to the flow field domain obtained by step 1), and calculates the gas-flow resistance that blade is subject to；
Step 3)：According to the numerical simulation result in step 2), intermediate cross-section (4) is established in blade height direction centre position,
The velocity profile figure in this section is obtained, is determined therefrom that in pressure face (5), boundary layer separation region (6) and suction surface recirculation zone
Micro- texture section (13) is arranged in (7) three pieces of regions；The cross sectional shape and particular location of micro- texture be：The cross sectional shape of micro- texture is
Triangle or quadrangle, and wherein a line is close in the section aerofoil profile (8)；The height h of micro- texture is turbulence vortex in the section
Tie up to out to out H in blade normal orientationmax4%~7%, but minimum constructive height is not less than 0.05mm, and maximum height is no more than
1mm；Micro- texture of pressure face is arranged in the region that blade inlet edge (10) goes forward 50% to trailing edge (11) direction；Suction surface it is micro-
Texture is arranged in suction surface and gone forward from backflow start to finish direction in the range of 50%；A cloth in boundary layer separation region (6)
Put a micro- texture；In pressure face and micro- texture of suction surface recirculation zone, wherein in the heart away from 1.5~2.5 times that l is height h；
Micro- texture meets stream side and direction of flow angle theta between 50 degree to 90 degree；Micro- texture of pressure face is groove structure, i.e., micro- to knit
Structure section is in aerofoil profile (8), and the recirculation zone of boundary layer separation region and suction surface is rib structure, i.e., micro- texture section
Protrude in aerofoil profile (8) outside；
Step 4)：With micro- texture section (13) of step 3) arrangement for bus, scanned over the paddle along blade height direction
It is into rib (14) or groove, detailed process：A projection plane (15) is established in blade suction surface, the plane is parallel to blade height
Direction is spent, and parallel to the chord length direction of vane airfoil profile in intermediate cross-section (4)；The base midpoint that will be created in step 3), base
It is located at one side in aerofoil profile for micro- texture section length of side；Make upright projection to projection plane (15)；In the projection plane (15)
Make by the straight parallel wire harness (16) of above subpoint, the straight parallel wire harness start from tea residue to the high direction of leaf 5% position,
End at 95% opening position, then the straight parallel wire harness projected to blade, obtains drop shadow curve, using these drop shadow curves as
Guide line, with micro- texture section (13) for bus, groove and rib (14) are scanned into, completes the establishment of micro- texture；
Step 5)：Numerical simulation, computation model are re-started to the leaf model that rib and the micro- texture of groove are had in step 4)
The resistance being subject to, and the resistance with obtaining before is made comparisons；By constantly adjusting position and the cross sectional shape of micro- texture, with given
Drag reduction be used for optimization aim, it is final to obtain micro- texture with optimal resistance reducing performance and arrange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710880615.1A CN107742011B (en) | 2017-09-26 | 2017-09-26 | Design method of impeller blade drag reduction micro-texture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710880615.1A CN107742011B (en) | 2017-09-26 | 2017-09-26 | Design method of impeller blade drag reduction micro-texture |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107742011A true CN107742011A (en) | 2018-02-27 |
| CN107742011B CN107742011B (en) | 2020-12-11 |
Family
ID=61235411
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710880615.1A Active CN107742011B (en) | 2017-09-26 | 2017-09-26 | Design method of impeller blade drag reduction micro-texture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107742011B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109543362A (en) * | 2019-01-25 | 2019-03-29 | 南京航空航天大学 | A kind of imitative sand dune micro-structure and its optimum design method with highly effective air anti-drag function |
| CN109597355A (en) * | 2018-11-02 | 2019-04-09 | 南京航空航天大学 | The design method of the micro- texture numerical control processing generating tool axis vector of curved surface |
| CN110410156A (en) * | 2019-08-02 | 2019-11-05 | 中国科学院工程热物理研究所 | The method of blade and its promotion load based on flow separation |
| CN110866351A (en) * | 2019-09-27 | 2020-03-06 | 南京航空航天大学 | Resistance-increasing micro-texture design of wing spoiler and manufacturing method based on CFRP material |
| CN111104716A (en) * | 2019-12-09 | 2020-05-05 | 北京航空航天大学 | Automatic generation method of groove type resistance reducing structure based on thermal diffusion facing to blade |
| CN111159850A (en) * | 2019-12-09 | 2020-05-15 | 北京航空航天大学 | Automatic generation method of flow-direction-following groove blade grid for planar scatter data |
| CN111723447A (en) * | 2020-06-30 | 2020-09-29 | 扬州大学 | Drag reduction design method for dynamic and static cavity flow micro-grooves |
| CN113111453A (en) * | 2021-03-30 | 2021-07-13 | 南京航空航天大学 | Numerical simulation simplification method for drag reduction performance of rotating blade microtexture |
| CN113139236A (en) * | 2021-04-26 | 2021-07-20 | 上海攀升数字科技有限责任公司 | Modeling method for turbulence ribs of inner-cooling turbine blade based on sweep curve |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101942638A (en) * | 2010-09-30 | 2011-01-12 | 中国科学院宁波材料技术与工程研究所 | Preparation method of bionic controllable adhesive hydrophobic gold surface |
| CN104595245A (en) * | 2015-01-04 | 2015-05-06 | 南京航空航天大学 | Last-stage front half section adjustable stator blade for axial-flow compressor and working method thereof |
| CN106435158A (en) * | 2016-10-09 | 2017-02-22 | 南通大学 | Workpiece surface laser shocking process utilizing surface micro textures for removing residual stress holes |
| US20170107972A1 (en) * | 2015-10-14 | 2017-04-20 | King Fahd University Of Petroleum And Minerals | Vertical wind turbine |
| CN106735486A (en) * | 2016-11-16 | 2017-05-31 | 哈尔滨理工大学 | It is a kind of with the micro- rose cutter for knitting structure and air-cooling function of imitative biology |
| CN106919749A (en) * | 2017-02-24 | 2017-07-04 | 湖北工业大学 | A kind of low noise vane design of wind turbines method and low noise pneumatic equipment bladess |
-
2017
- 2017-09-26 CN CN201710880615.1A patent/CN107742011B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101942638A (en) * | 2010-09-30 | 2011-01-12 | 中国科学院宁波材料技术与工程研究所 | Preparation method of bionic controllable adhesive hydrophobic gold surface |
| CN104595245A (en) * | 2015-01-04 | 2015-05-06 | 南京航空航天大学 | Last-stage front half section adjustable stator blade for axial-flow compressor and working method thereof |
| US20170107972A1 (en) * | 2015-10-14 | 2017-04-20 | King Fahd University Of Petroleum And Minerals | Vertical wind turbine |
| CN106435158A (en) * | 2016-10-09 | 2017-02-22 | 南通大学 | Workpiece surface laser shocking process utilizing surface micro textures for removing residual stress holes |
| CN106735486A (en) * | 2016-11-16 | 2017-05-31 | 哈尔滨理工大学 | It is a kind of with the micro- rose cutter for knitting structure and air-cooling function of imitative biology |
| CN106919749A (en) * | 2017-02-24 | 2017-07-04 | 湖北工业大学 | A kind of low noise vane design of wind turbines method and low noise pneumatic equipment bladess |
Non-Patent Citations (1)
| Title |
|---|
| 张臣 等: "叶片表面减阻织构设计综述", 《航空制造技术》 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109597355A (en) * | 2018-11-02 | 2019-04-09 | 南京航空航天大学 | The design method of the micro- texture numerical control processing generating tool axis vector of curved surface |
| CN109543362A (en) * | 2019-01-25 | 2019-03-29 | 南京航空航天大学 | A kind of imitative sand dune micro-structure and its optimum design method with highly effective air anti-drag function |
| CN109543362B (en) * | 2019-01-25 | 2020-05-08 | 南京航空航天大学 | Sand dune-like microstructure with efficient air drag reduction function and optimization design method thereof |
| CN110410156A (en) * | 2019-08-02 | 2019-11-05 | 中国科学院工程热物理研究所 | The method of blade and its promotion load based on flow separation |
| CN110866351A (en) * | 2019-09-27 | 2020-03-06 | 南京航空航天大学 | Resistance-increasing micro-texture design of wing spoiler and manufacturing method based on CFRP material |
| CN110866351B (en) * | 2019-09-27 | 2021-07-27 | 南京航空航天大学 | Resistance-increasing micro-texture design of wing spoiler and manufacturing method based on CFRP material |
| CN111159850A (en) * | 2019-12-09 | 2020-05-15 | 北京航空航天大学 | Automatic generation method of flow-direction-following groove blade grid for planar scatter data |
| CN111159850B (en) * | 2019-12-09 | 2021-06-01 | 北京航空航天大学 | Automatic generation method of flow-direction-following groove blade grid for planar scatter data |
| CN111104716A (en) * | 2019-12-09 | 2020-05-05 | 北京航空航天大学 | Automatic generation method of groove type resistance reducing structure based on thermal diffusion facing to blade |
| CN111723447A (en) * | 2020-06-30 | 2020-09-29 | 扬州大学 | Drag reduction design method for dynamic and static cavity flow micro-grooves |
| CN111723447B (en) * | 2020-06-30 | 2023-11-14 | 扬州大学 | Dynamic and static cavity flow micro-groove drag reduction design method |
| CN113111453A (en) * | 2021-03-30 | 2021-07-13 | 南京航空航天大学 | Numerical simulation simplification method for drag reduction performance of rotating blade microtexture |
| CN113111453B (en) * | 2021-03-30 | 2023-04-25 | 南京航空航天大学 | Numerical simulation simplifying method for drag reduction performance of micro-texture of rotating blade |
| CN113139236A (en) * | 2021-04-26 | 2021-07-20 | 上海攀升数字科技有限责任公司 | Modeling method for turbulence ribs of inner-cooling turbine blade based on sweep curve |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107742011B (en) | 2020-12-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107742011A (en) | The design method of the micro- texture of impeller blade drag reduction | |
| Siddappaji et al. | General capability of parametric 3d blade design tool for turbomachinery | |
| Chen et al. | Location effect of boundary layer suction on compressor hub-corner separation | |
| CN105781626B (en) | Three-dimensional orthogonal unsteady design method of large meridian expansion turbine | |
| CN103410779B (en) | A kind of flow separation method for stationary cascade of high-load axial flow air compressor | |
| Ji et al. | Numerical studies on improving performance of rotor-67 by blended blade and endwall technique | |
| Wanjin et al. | Effects of leaning and curving of blades with high turning angles on the aerodynamic characteristics of turbine rectangular cascades | |
| CN111550363A (en) | Blade tip winglet, wind turbine blade and blade synergy calculation method thereof | |
| Tan et al. | Blade bowing effect on aerodynamic performance of a highly loaded turbine cascade | |
| CN109918778A (en) | Wind energy conversion system aerofoil with blunt tail edge optimum design method under the conditions of a kind of rime ice | |
| CN111706409A (en) | Corrugated air film hole with branch hole | |
| Liu et al. | A parametric investigation of endwall vortex generator jet on the secondary flow control for a high turning compressor cascade | |
| CN107284650A (en) | A kind of Supercritical Airfoils With Natural Laminar Flow applied to intermediate range civil aircraft swept back wing | |
| CN208216978U (en) | A kind of aircraft horizontal tail root vortex generator | |
| CN105298912A (en) | Bump front edge inlet guider blade | |
| Ling et al. | Relationship between optimum curved blade generate line and cascade parameters in subsonic axial compressor | |
| CN105787217B (en) | A kind of optimum design method of aircraft ripple aerofoil profile | |
| Dorfner et al. | Advanced non-axisymmetric endwall contouring for axial compressors by generating an aerodynamic separator—part i: principal cascade design and compressor application | |
| Li et al. | The use of blended blade and end wall in compressor cascade: Optimization design and flow mechanism | |
| CN103148015B (en) | Trailing edge negative load diffusion formula turbine blade | |
| CN106351872A (en) | Compressor rotor blade meeting both pneumatic and strength requirements | |
| CN112541231A (en) | Helicopter exhaust pipe shaping spoiler design method | |
| Ahmed et al. | Investigation of improved aerodynamic performance of isolated airfoils using circle method | |
| Wu et al. | Improvement of steam turbine blade foil with biomimetic design and its influence on aerodynamic performance | |
| CN203516191U (en) | Wind wheel blade and cross-flow wind wheel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |