CN113111599B - High-precision hybrid testing method for global flow field of wind power blade - Google Patents
High-precision hybrid testing method for global flow field of wind power blade Download PDFInfo
- Publication number
- CN113111599B CN113111599B CN202110262400.XA CN202110262400A CN113111599B CN 113111599 B CN113111599 B CN 113111599B CN 202110262400 A CN202110262400 A CN 202110262400A CN 113111599 B CN113111599 B CN 113111599B
- Authority
- CN
- China
- Prior art keywords
- flow field
- wind power
- power blade
- test
- blade
- 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.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 94
- 238000004364 calculation method Methods 0.000 claims abstract description 59
- 238000000034 method Methods 0.000 claims abstract description 28
- 230000002093 peripheral effect Effects 0.000 claims abstract description 4
- 230000008859 change Effects 0.000 claims description 9
- 239000002245 particle Substances 0.000 claims description 7
- 239000012530 fluid Substances 0.000 claims description 6
- 230000010354 integration Effects 0.000 claims description 3
- 230000008569 process Effects 0.000 claims description 2
- 238000010998 test method Methods 0.000 abstract description 6
- 238000005259 measurement Methods 0.000 abstract description 3
- 238000012545 processing Methods 0.000 abstract description 2
- 238000000917 particle-image velocimetry Methods 0.000 description 28
- 238000011160 research Methods 0.000 description 7
- 238000002474 experimental method Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 238000004088 simulation Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/06—Wind turbines or wind farms
Abstract
The embodiment of the application provides a high-precision hybrid test method for a global flow field of a wind power blade, which belongs to the technical field of wind power blade measurement and comprises the following steps: performing external flow field test by adopting PIV test technology, selecting PIV experimental test parameters, and obtaining peripheral flow field test data of the rotating wind power blade; calculating a boundary layer flow field of a near-wall region by adopting a CFD calculation method, determining an initial boundary condition, and combining a flow field N-S momentum equation representing the rotating wind power blade to finish the calculation of the boundary layer flow field of the near-wall region; carrying out flow field reconstruction of the overlapped area by adopting a least square method and a poisson equation; and combining flow field test data around the rotating wind power blade, near-wall area boundary layer flow field data and reconstructed flow field data to obtain a global flow field of the rotating wind power blade. According to the processing scheme, the convenience of calculating the flow field values around the wind power blade and the accuracy of calculation results are improved, and the workload of testing the flow field of the blade is effectively reduced.
Description
Technical Field
The application relates to the technical field of wind power blade measurement, in particular to a high-precision hybrid testing method for a global flow field of a wind power blade.
Background
In the field of rotating machinery such as wind turbines and propellers, the aerodynamic performance of the blades directly affects the power output and stable operation of the rotating mechanism. The running environments of the blades in different rotating mechanical fields are complex and changeable, so that the flowing states of the surfaces of the blades are different, the speed fields of the boundary layer around the rotating blades and the surface can be accurately and effectively obtained, and the method is a basis for realizing the pneumatic design and flow mechanism research of the blades in the rotating mechanical fields such as wind turbines, propellers and the like.
At present, the experimental flow field test and flow field numerical calculation are two main research means, however, the two methods have respective problems and defects: for the experimental test method of the rotating blade flow field, PIV (Particle Image Velocimetry ) is a non-contact flow field test technology, can well obtain flow field data in a two-dimensional plane and a three-dimensional space, and is widely applied to the rotating blade flow field test. However, the flow field test accuracy of the PIV technology is affected by many factors, such as laser intensity, laser quality, trace particle type, concentration, and synchronous matching accuracy of a camera and laser, etc., and the PIV test equipment has more severe requirements on experimental environment, and the test result is greatly affected by the flow field state. Due to the rotation effect of the wind power blade, the concentration of trace particles on the surface of the blade is often obviously reduced, and when the rotation speed of the blade is higher, the concentration of trace particles on the surface of the blade is difficult to meet the experimental requirement, so that the accuracy of a flow field test result on the surface of the rotating blade is greatly influenced. In addition, the PIV technology needs to project laser to the surface of the blade, obvious reflection phenomenon can occur in the near-wall area of the blade, and the flow field of the near-wall area of the blade cannot be clearly obtained due to stronger reflection, so that research work on flow near the boundary layer of the surface of the rotating wind power blade cannot be carried out.
For the numerical calculation method of the rotating wind power blade flow field, different numerical calculation methods can be adopted according to different calculation precision requirements and different flow structure dimensions, and speed field results with higher precision in the periphery of the blade and the surface boundary layer can be obtained. However, when the flow field of the rotating wind power blade is acquired by using a numerical calculation method, more problems exist, firstly, the division of the calculation grid is the work which needs to be completed at first by numerical simulation, because the wind power blade has a complex three-dimensional structure appearance, obvious torsion angle changes exist from the blade tip to the blade root, and the chord lengths of the blades at different spreading positions are not the same, so that great difficulty is brought to the division of the calculation grid. In addition, in order to improve the accuracy of the calculation result, the special position grids need to be encrypted, so that the calculated grid quantity is increased to a great extent, the calculated quantity is greatly increased, and the calculation time is prolonged; secondly, due to the complexity of the three-dimensional blade shape, the quality of grid division at all positions is difficult to ensure, and the poor grid quality directly influences the calculation accuracy and the accuracy of the calculation result; finally, in order to obtain the whole flow field information around the rotating wind power blade, the calculation domain area needs to be enlarged, and the calculation grid quantity is directly increased, so that the calculation quantity and the calculation time are greatly increased.
Disclosure of Invention
In view of this, the embodiments of the present application provide a high-precision hybrid testing method for a global flow field of a wind power blade, which at least partially solves the problems existing in the prior art. The method is applicable to flow field tests of the dynamic rotation two-dimensional wind power wing section, the dynamic rotation three-dimensional wind power wing section and the dynamic rotation three-dimensional wind power blade.
The embodiment of the application provides a high-precision hybrid test method for a global flow field of a wind power blade, which comprises the following steps:
determining an external flow field test area, a near-wall area boundary layer flow field calculation area and a flow field reconstruction area of an overlapping area of the external flow field test and the near-wall area boundary layer flow field calculation of the rotating wind power blade;
performing the external flow field test, adopting an PIV test technology, selecting PIV experimental test parameters, and obtaining peripheral flow field test data of the rotating wind power blade;
calculating the boundary layer flow field of the near-wall region, determining an initial boundary condition by adopting a CFD calculation method, and combining a flow field N-S momentum equation representing the rotating wind power blade, wherein the formula is as follows:
wherein, v is the flow velocity,the velocity is the change quantity with time, v is the fluid viscosity, ρ is the fluid density, f is the external acting force, p is the pressure born by the flow, deltav is the velocity change quantity, and then the calculation of the boundary layer flow field of the near-wall region is completed;
performing flow field reconstruction of the overlapped area, taking the surrounding flow field test data corresponding to the overlapped area as an initial speed value, performing node speed reconstruction, and finishing new linear weight combination between data of a speed vector of the overlapped area calculated by a boundary layer of a near-wall area and the surrounding flow field test data corresponding to the CFD calculation time step to obtain reconstructed flow field data;
and combining the flow field test data around the rotating wind power blade, the near-wall area boundary layer flow field calculation data and the reconstructed flow field data to obtain the global flow field of the rotating wind power blade.
According to a specific implementation manner of the embodiment of the application, the PIV experimental test parameters include laser energy, high-speed camera acquisition frequency and trace particle concentration.
According to a specific implementation manner of the embodiment of the application, in the external flow field testing process, a two-dimensional PIV testing technology or a three-dimensional PIV testing technology is selected according to the structure of the rotating wind power blade.
According to a specific implementation manner of the embodiment of the application, when the rotating wind power blade is a two-dimensional wind power wing profile, a two-dimensional PIV test technology is selected; when wind power wing segments or wind power blades with three-dimensional change along the flow direction or the expanding direction are adopted, the three-dimensional PIV test technology is selected.
According to a specific implementation manner of the embodiment of the application, the least square method and the poisson equation are adopted when the node speed is reconstructed.
According to a specific implementation manner of the embodiment of the application, the testing method further comprises the steps of calculating time and space derivatives of the rotating wind power blade, reconstructing pressure gradients and pressure fields on the surface of the blade, and obtaining aerodynamic force distribution.
According to a specific implementation manner of the embodiment of the application, a poisson method, a Bernoulli method or a direct integration method is adopted when the pressure gradient and the pressure field of the blade surface are reconstructed.
According to a specific implementation manner of the embodiment of the application, the pneumatic force distribution is obtained by applying a volume fraction or a surface fraction.
According to a specific implementation manner of the embodiment of the application, the CFD calculation method includes DNS, RANS and LES.
Advantageous effects
The high-precision hybrid testing method for the global flow field of the wind power blade can be used for carrying out high-precision testing work of the three-dimensional speed field of the surface of the wind power blade with a complex structure, and provides technical support for related research work of the flow mechanism of the surface of the wind power blade; the high-precision flow field testing method provided by the invention can effectively improve the testing precision of the flow field of the near-wall area boundary layer of the surface of the rotating wind power blade and different areas around the blade, effectively reduce the grid quantity of the flow field around the rotating blade calculated by the CFD calculation method, and greatly reduce the workload and calculation time of the numerical calculation of the flow field of the rotating blade; in addition, the flow field test method can conveniently develop the influence research of the flow field, the pneumatic force field and the sound field from the global angle, has great advantages compared with the traditional test means such as local pressure test, whole aerodynamic force measurement and noise, and can effectively replace the traditional test methods such as a pressure scanning valve, a force measuring balance, a wake rake and a microphone.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a method for testing a global flow field of a rotating wind blade according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of an overlap region flow field reconstruction method according to an embodiment of the present invention;
FIG. 3 is a graph of flow field test results of an airfoil surrounding PIV experiment in accordance with one embodiment of the present invention;
FIG. 4 is a grid-partition diagram of an airfoil near-wall region flow field calculation according to an embodiment of the invention;
FIG. 5 is a graph of global flow field results around an airfoil according to an embodiment of the invention.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concepts of the application by way of illustration, and only the components related to the application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The embodiment of the application provides a high-precision hybrid testing method for a global flow field of a wind power blade, and the testing method is specifically described below with reference to a schematic diagram of fig. 1. The test method comprises the following steps:
and determining an external flow field test area, a near-wall area boundary layer flow field calculation area and a flow field reconstruction area of an overlapping area of the external flow field test and the near-wall area boundary layer flow field calculation of the rotating wind power blade.
In the embodiment, based on a rotating wind power blade experimental platform, PIV test technology is adopted to select PIV experimental test parameters, and peripheral flow field test data of the rotating wind power blade are obtained. The PIV experimental test parameters comprise laser energy, high-speed camera acquisition frequency, trace particle concentration and the like, and the quality of laser on the surface of the blade and the concentration of the trace particles are required to be ensured, so that the test requirement of the rotating wind power blade flow field is met to the greatest extent.
Further, according to different wind power blades with different complex structures, PIV experimental flow field test schemes are different, and for a two-dimensional wind power wing profile with a simpler structure, a two-dimensional PIV can be selected for flow field test to obtain two-dimensional plane flow field data; aiming at wind power wing segments and wind power blades with three-dimensional change along the flow direction or the expanding direction, a three-dimensional PIV is adopted to perform flow field test, so that the three-dimensional flow field change condition of the blade surface can be obtained; for the condition that a wind power blade with a special structure or a aerodynamic accessory with a complex structure exists on the surface of the blade, the three-dimensional PIV can be adopted to carry out flow field test; in addition, for the research of analyzing the internal flow structure of the three-dimensional complex flow field, a three-dimensional PIV test technology is mostly selected. That is, an appropriate PIV test scheme can be selected for external flow field testing of the rotating wind power blade according to different test environments.
Carrying out the calculation of the boundary layer flow field of the near wall region, and adopting a CFD calculation method, wherein the CFD calculation and the PIV flow field test experiment adopt the same rotating wind power blade; determining an initial boundary condition, and combining a flow field N-S momentum equation representing the rotating wind power blade, wherein the formula is as follows:
wherein, v is the flow velocity,as the change of the speed with time, deltav is the speed change, v is the fluid viscosity, ρ is the fluid density, f is the external acting force, and p is the pressure of the flow, thus completing the calculation of the boundary layer flow field of the near wall region.
In this embodiment, the CFD calculation method may be DNS (Direct Numerical Simulation ), RANS (Reynolds averaged Navier Stokes, reynolds average), LES (Large Eddy Simulation, large vortex simulation), or the like.
And carrying out flow field reconstruction in the overlapped area, taking the surrounding flow field test data corresponding to the overlapped area as an initial speed value, carrying out node speed reconstruction, so that the reconstructed rotating speed field can meet the calculation requirement of a continuity equation, and finishing the new combination of linear weights between the data obtained by calculating the speed vector of the overlapped area by the boundary layer of the near-wall area and the surrounding flow field test data corresponding to the CFD calculation time step to obtain the reconstructed flow field data.
It should be noted that, the flow field data after reconstruction can be used as the initial boundary conditions of the boundary layer flow field of the near wall region of the rotating blade and the flow field around the rotating blade at the same time, so that the flow field of different regions around the rotating blade can be ensured to have high space-time resolution equivalent to the CFD calculation.
In this embodiment, the overlapped area flow field reconstruction is performed by using a least square method and a poisson equation, and the specific method refers to fig. 2, wherein Δt is an acquisition time interval of an experiment in a PIV test experiment, and Δt is a time step of CFD calculation in CFD calculation, and the overlapped area flow field reconstruction is a new linear weight combination of flow field data obtained by performing PIV test corresponding to the overlapped area and flow field data obtained by performing CFD calculation by using the least square method and the poisson equation.
It should be explained that the reconstructed overlap region flow field data may be input into the CFD as an initial boundary condition for numerical calculations. In addition, the flow field data of the overlapped area after reconstruction can be used as the initial boundary conditions of the boundary layer flow field of the near-wall area of the rotating blade and the flow field around the rotating blade at the same time, so that the flow field of different areas around the rotating blade can be ensured to have high space-time resolution equivalent to the CFD calculation.
And combining the flow field test data around the rotating wind power blade, the flow field data of the boundary layer of the near-wall region and the reconstructed flow field data to obtain the global flow field of the rotating wind power blade.
Furthermore, on the basis of acquiring global flow field data of the rotating wind power blade, space and time derivatives are calculated, then the blade surface pressure gradient and pressure field are reconstructed by a poisson method, a Bernoulli method or a direct integration method and the like, and aerodynamic distribution is obtained by applying volume integral or area. In addition, the speed field data of the overlapped area obtained by reconstruction can be used as an initial boundary condition of a flow field around the rotating blade according to the requirement, and the grid quantity of CFD calculation can be greatly reduced under the condition of ensuring a high-precision flow field result.
In one embodiment, taking a two-dimensional dynamic wind wing type flow field test as an example, a rotating wind power blade global flow field test is performed:
s1, acquiring integral flow field data of a surrounding area C of a rotary airfoil by adopting PIV test technology, wherein the area of a shooting area C is 18 multiplied by 20cm, and the result is shown in figure 3;
s2, selecting a boundary layer area A of the near-wall area of the airfoil, dividing a calculation grid with the calculation area of 7 multiplied by 13cm, and obtaining a high-precision flow field result of the boundary layer area A of the near-wall area of the airfoil in a CFD numerical calculation mode, wherein in the embodiment, a RANS method is adopted as the CFD numerical calculation method as shown in FIG. 4;
s3, respectively extracting flow field data of an overlapping part B region between the PIV experiment C region and the CFD numerical calculation A region, as shown in FIG. 5;
s4, carrying out reconstruction and synthesis processing by using flow field data of the overlapping part B region, and finally merging flow field results of the PIV flow field experiment C region and the CFD numerical calculation A region to obtain global high-precision flow field data around the two-dimensional rotating airfoil, as shown in FIG. 5.
According to the embodiment provided by the invention, the method for testing the global flow field of the rotating wind power blade with high efficiency and high precision is provided, the testing work of the flow field on the surface of the blade with a complex appearance structure can be carried out according to the method, the high-precision flow field result is obtained, the pressure field and aerodynamic force distribution condition on the surface of the rotating blade are obtained on the basis, and technical support is provided for the related research work of aerodynamic force characteristics and flow field characteristics of the rotating wind power blade. In addition, the testing method improves the convenience of calculating the flow field values around the wind power blade and the accuracy of calculation results, and effectively reduces the workload of testing the flow field of the blade.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. The high-precision hybrid testing method for the global flow field of the wind power blade is characterized by comprising the following steps of:
determining an external flow field test area, a near-wall area boundary layer flow field calculation area and a flow field reconstruction area of an overlapping area of the external flow field test and the near-wall area boundary layer flow field calculation of the rotating wind power blade;
performing the external flow field test, and selecting PIV experimental test parameters by adopting PIV test technology to obtain peripheral flow field test data of the rotating wind power blade, wherein the PIV experimental test parameters comprise laser energy, high-speed camera acquisition frequency and trace particle concentration;
calculating the boundary layer flow field of the near-wall region, determining an initial boundary condition by adopting a CFD calculation method, and combining a flow field N-S momentum equation representing the rotating wind power blade, wherein the formula is as follows:
，
wherein,for flow rate>For the change of speed over time, +.>For fluid viscosity->For fluid density->For external forces +.>For the pressure to which the flow is subjected,/->The velocity variation is used for completing the calculation of the boundary layer flow field of the near-wall region;
performing flow field reconstruction of the overlapped area, using the surrounding flow field test data corresponding to the overlapped area as an initial speed value, performing node speed reconstruction, and corresponding to the time step of CFD calculation, completing new linear weight combination between data obtained by calculating a speed vector of the overlapped area by a boundary layer of a near-wall area and the surrounding flow field test data, and obtaining reconstructed flow field data, wherein a least square method and a Poisson equation are adopted when the node speed reconstruction is performed;
combining flow field test data around the rotating wind power blade, near wall area boundary layer flow field calculation data and reconstructed flow field data to obtain a global flow field of the rotating wind power blade;
the testing method further comprises the steps of calculating time and space derivatives of the rotating wind power blade, and reconstructing pressure gradients and pressure fields on the surface of the blade to obtain aerodynamic force distribution.
2. The high-precision hybrid testing method for the global flow field of the wind power blade according to claim 1, wherein in the external flow field testing process, a two-dimensional PIV testing technology or a three-dimensional PIV testing technology is selected according to the structure of the rotating wind power blade.
3. The high-precision hybrid testing method for the global flow field of the wind power blade according to claim 2, wherein a two-dimensional PIV testing technology is selected when the rotating wind power blade is a two-dimensional wind power wing profile; when wind power wing segments or wind power blades with three-dimensional change along the flow direction or the expanding direction are adopted, the three-dimensional PIV test technology is selected.
4. The high-precision hybrid testing method for the global flow field of the wind power blade according to claim 1, wherein a poisson method, a Bernoulli method or a direct integration method is adopted when the pressure gradient and the pressure field of the surface of the blade are reconstructed.
5. The method for high-precision hybrid testing of a global flow field of a wind power blade according to claim 1, wherein the aerodynamic profile is obtained by applying a volume fraction or a surface fraction.
6. The high precision hybrid testing method for a global flow field of a wind power blade according to claim 1, wherein the CFD calculation method comprises DNS, RANS and LES.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110262400.XA CN113111599B (en) | 2021-03-10 | 2021-03-10 | High-precision hybrid testing method for global flow field of wind power blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110262400.XA CN113111599B (en) | 2021-03-10 | 2021-03-10 | High-precision hybrid testing method for global flow field of wind power blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113111599A CN113111599A (en) | 2021-07-13 |
| CN113111599B true CN113111599B (en) | 2024-01-19 |
Family
ID=76711273
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110262400.XA Active CN113111599B (en) | 2021-03-10 | 2021-03-10 | High-precision hybrid testing method for global flow field of wind power blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113111599B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005321290A (en) * | 2004-05-10 | 2005-11-17 | Railway Technical Res Inst | Aerodynamic sound source probe system and aerodynamic sound source probe method |
| JP2010243309A (en) * | 2009-04-06 | 2010-10-28 | Japan Aerospace Exploration Agency | Measuring method of fluid force distribution and measuring device |
| CN102608917A (en) * | 2012-02-19 | 2012-07-25 | 中国科学院工程热物理研究所 | Method for simulating high-temperature phase change heat storage value with hole under microgravity condition |
| JP2012251877A (en) * | 2011-06-03 | 2012-12-20 | Ihi Corp | Method and device for measuring shear stress distribution of flow field |
| CN104777164A (en) * | 2015-03-30 | 2015-07-15 | 天津大学 | Large-size measuring experimental apparatus and method for air flow in cabin based on PIV |
| CN106870247A (en) * | 2017-02-28 | 2017-06-20 | 哈尔滨工业大学 | A kind of draft cone drilling method based on hydraulic turbine whole flow field three-dimensional simulation method |
| CN107290130A (en) * | 2017-06-23 | 2017-10-24 | 吉林大学 | A kind of propeller blade External airflow field particle image velocimetry experimental rig |
| US10118696B1 (en) * | 2016-03-31 | 2018-11-06 | Steven M. Hoffberg | Steerable rotating projectile |
| CN112199777A (en) * | 2020-10-23 | 2021-01-08 | 中国科学院工程热物理研究所 | Method suitable for modeling bionic leading edge flow field characteristics |
| CN112632726A (en) * | 2020-12-30 | 2021-04-09 | 中国科学院工程热物理研究所 | Flow field reconstruction method for aeroelasticity simulation of impeller mechanical blade |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2050074A2 (en) * | 2006-07-13 | 2009-04-22 | The Regents Of The University Of Colorado | Echo particle image velocity (epiv) and echo particle tracking velocimetry (eptv) system and method |
| US7774171B2 (en) * | 2007-05-11 | 2010-08-10 | General Electric Company | Methods for optimizing parameters of gas turbine engine components |
-
2021
- 2021-03-10 CN CN202110262400.XA patent/CN113111599B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005321290A (en) * | 2004-05-10 | 2005-11-17 | Railway Technical Res Inst | Aerodynamic sound source probe system and aerodynamic sound source probe method |
| JP2010243309A (en) * | 2009-04-06 | 2010-10-28 | Japan Aerospace Exploration Agency | Measuring method of fluid force distribution and measuring device |
| JP2012251877A (en) * | 2011-06-03 | 2012-12-20 | Ihi Corp | Method and device for measuring shear stress distribution of flow field |
| CN102608917A (en) * | 2012-02-19 | 2012-07-25 | 中国科学院工程热物理研究所 | Method for simulating high-temperature phase change heat storage value with hole under microgravity condition |
| CN104777164A (en) * | 2015-03-30 | 2015-07-15 | 天津大学 | Large-size measuring experimental apparatus and method for air flow in cabin based on PIV |
| US10118696B1 (en) * | 2016-03-31 | 2018-11-06 | Steven M. Hoffberg | Steerable rotating projectile |
| CN106870247A (en) * | 2017-02-28 | 2017-06-20 | 哈尔滨工业大学 | A kind of draft cone drilling method based on hydraulic turbine whole flow field three-dimensional simulation method |
| CN107290130A (en) * | 2017-06-23 | 2017-10-24 | 吉林大学 | A kind of propeller blade External airflow field particle image velocimetry experimental rig |
| CN112199777A (en) * | 2020-10-23 | 2021-01-08 | 中国科学院工程热物理研究所 | Method suitable for modeling bionic leading edge flow field characteristics |
| CN112632726A (en) * | 2020-12-30 | 2021-04-09 | 中国科学院工程热物理研究所 | Flow field reconstruction method for aeroelasticity simulation of impeller mechanical blade |
Non-Patent Citations (6)
| Title |
|---|
| CFD simulation and PIV measurement of the flow fieldgenerated by modified pitched blade turbine impellers;Chun-Yan Ge 等;Chemical Engineering Research and Design;第1-10页 * |
| 基于ＰＩＶ技术的压力场重构算法实现与研究;刘顺等;实验流体力学;第30卷(第4期);第56-65页 * |
| 基于网格/无网格的三维超音速流场数值模拟;蔡晓伟等;工程力学;第31卷(第12期);第17-22、39页 * |
| 基于致动面模型的风力机尾流数值研究;周洋等;工程热物理学报;第38卷(第03期);第535-540页 * |
| 翼型桨叶片尾涡结构的PIV实测与LES模拟研究;蔡清白等;过程工程学报;第11卷(第04期);第541-548页 * |
| 边界元法风力机近尾迹区域气动噪声研究;代元军等;中国测试;第41卷(第01期);第100-103页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113111599A (en) | 2021-07-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Jacob et al. | A rod-airfoil experiment as a benchmark for broadband noise modeling | |
| Troldborg et al. | Actuator line simulation of wake of wind turbine operating in turbulent inflow | |
| Hodson et al. | The role of transition in high-lift low-pressure turbines for aeroengines | |
| Gorle et al. | Flow and performance analysis of H-Darrieus hydroturbine in a confined flow: A computational and experimental study | |
| Bear et al. | Experimental investigation of total pressure loss development in a highly loaded low-pressure turbine cascade | |
| Villegas et al. | Evaluation of unsteady pressure fields and forces in rotating airfoils from time-resolved PIV | |
| Keller et al. | Examination of propeller sound production using large eddy simulation | |
| Rahmati et al. | Nonlinear time and frequency domain methods for multirow aeromechanical analysis | |
| Hergt et al. | The present challenge of transonic compressor blade design | |
| Hergt et al. | The effect of an eroded leading edge on the aerodynamic performance of a transonic fan blade cascade | |
| Rahmatian et al. | Numerical and experimental study of the ducted diffuser effect on improving the aerodynamic performance of a micro horizontal axis wind turbine | |
| Ross et al. | An experimental evaluation of blockage effects on the wake of a cross-flow current turbine | |
| CN113111599B (en) | High-precision hybrid testing method for global flow field of wind power blade | |
| Lynch III et al. | Turbulence correlation length-scale relationships for the prediction of aeroacoustic response | |
| Wenger et al. | Wake of a compressor cascade with tip gap, part 3: Two point statistics | |
| Guérin et al. | Open-rotor noise prediction with a RANS-informed analytical method | |
| Infantino et al. | Phase-Locked Investigation of Secondary Flows Perturbed by Passing Wakes in a High-Lift LPT Turbine Cascade | |
| Bai et al. | Prediction of slat broadband noise with RANS results | |
| Zhang et al. | Aerodynamic topology optimization on tip configurations of turbine blades | |
| Lindgren et al. | Evaluation of a new wind tunnel with expanding corners | |
| Hergt et al. | The present challenge of transonic compressor blade design | |
| Varshney | Characteristics of helical tip vortices in a wind turbine near wake | |
| Góralczyk et al. | Model of a ducted axial-flow hydrokinetic turbine–results of experimental and numerical examination | |
| Grasso et al. | Influence of the noise prediction model on the aeroacoustic optimization of a contra-rotating fan | |
| Finez et al. | Experimental investigation of trailing-edge noise from a linear cascade of cambered airfoils |
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 |