CN117571192A - Blade surface pressure measurement method and system based on quick response PSP - Google Patents
Blade surface pressure measurement method and system based on quick response PSP Download PDFInfo
- Publication number
- CN117571192A CN117571192A CN202311507083.9A CN202311507083A CN117571192A CN 117571192 A CN117571192 A CN 117571192A CN 202311507083 A CN202311507083 A CN 202311507083A CN 117571192 A CN117571192 A CN 117571192A
- Authority
- CN
- China
- Prior art keywords
- psp
- pressure
- test
- temperature
- images
- 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.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 49
- 230000004044 response Effects 0.000 title claims abstract description 20
- 238000009530 blood pressure measurement Methods 0.000 title abstract description 17
- 238000012360 testing method Methods 0.000 claims abstract description 66
- 238000005259 measurement Methods 0.000 claims abstract description 28
- 230000035945 sensitivity Effects 0.000 claims abstract description 22
- 230000003287 optical effect Effects 0.000 claims abstract description 11
- 238000012545 processing Methods 0.000 claims abstract description 5
- 238000009596 phenolsulfonphthalein test Methods 0.000 claims description 24
- 230000003068 static effect Effects 0.000 claims description 11
- 230000008569 process Effects 0.000 claims description 10
- 230000001360 synchronised effect Effects 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 claims description 4
- 239000013307 optical fiber Substances 0.000 claims description 4
- 238000005507 spraying Methods 0.000 claims description 4
- 238000012886 linear function Methods 0.000 claims description 3
- 238000004020 luminiscence type Methods 0.000 claims description 2
- 230000005284 excitation Effects 0.000 claims 1
- 230000001276 controlling effect Effects 0.000 description 6
- 230000008901 benefit Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000005279 excitation period Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000003973 paint Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
- G01L11/02—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00 by optical means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The application provides a blade surface pressure measurement method and a PSP measurement system based on a quick response PSP, wherein the method comprises the following steps: step 1: obtaining the pressure sensitivity of PSP by using a PSP calibration method; step 2: constructing a PSP measurement system, wherein the PSP measurement system comprises a laser, a CCD camera, a lens, an optical filter, a synchronizer and a computer; step 3: acquiring test data by using a PSP measurement system; step 4: data processing is performed on the test data according to the pressure sensitivity of the PSP.
Description
Technical Field
The invention belongs to the technical field of helicopter rotor wing tests, and relates to a blade surface pressure measurement method and a PSP measurement system based on a quick response PSP.
Background
The pressure pulsation on the surface of the helicopter rotor blade directly affects the vibration and noise level of equipment, the surface pressure distribution of the blade can well reflect the surface pneumatic load distribution condition of the blade, and the pressure value is often closely related to vibration, pneumatic elasticity, pneumatic noise level and the like. Therefore, obtaining the surface pressure distribution of the helicopter rotor blade rotating at a high speed is a basis for researching vibration, aeroelasticity rules and pneumatic noise mechanisms and further developing vibration reduction and noise reduction technologies.
The traditional contact pressure measuring method mainly comprises two steps of opening pressure measuring holes on the surface of a rotor blade of a helicopter model and arranging miniature pressure sensors. The first method of opening pressure taps is only suitable for pressure measurement in steady-state flow fields, and if pressure measurement of the entire blade surface is to be achieved, hundreds or thousands of pressure taps are typically required, and the pressure measurement process is time-consuming and labor-consuming. The second method for arranging the miniature pressure sensor can realize the measurement of the unsteady pressure on the surface of the blade, has the advantage of high response speed, but is limited by the problems of installation and signal transmission when being applied to rotating blades, has extremely limited spatial resolution, and is difficult to support the deep study on the complex flow problem.
Disclosure of Invention
The purpose of the invention is that: the surface unsteady pressure measurement of the helicopter model rotor blade is realized, and test data support is provided for the aerodynamic elasticity law and aerodynamic noise mechanism research of the helicopter rotor blade.
In a first aspect, the present application provides a method for measuring blade surface pressure and a PSP measurement system based on a fast response PSP, the method comprising:
step 1: obtaining the pressure sensitivity of PSP by using a PSP calibration method;
step 2: constructing a PSP measurement system, wherein the PSP measurement system comprises a laser, a CCD camera, a lens, an optical filter, a synchronizer and a computer;
step 3: acquiring test data by using a PSP measurement system;
step 4: data processing is performed on the test data according to the pressure sensitivity of the PSP.
Specifically, step 1 includes:
step 11: setting a pressure control range and a temperature control range of a static pressure calibration system;
step 12: when PSP is calibrated, placing a sample wafer sprayed with PSP in a calibration box;
step 13: the pressure controller and the temperature controller are respectively utilized to adjust the pressure and the temperature in the calibration box to the reference value;
step 14: when the temperature of the calibration box reaches the reference temperature and the pressure reaches the reference pressure and is stable, waiting for a preset time to ensure that the calibration box fully reaches the heat balance, then exciting the PSP by using a laser, and continuously acquiring two PSP reference images under the pressure and the temperature by using a CCD camera;
step 15: setting a set of temperature and pressure values;
step 16: the pressure controller and the temperature controller are respectively utilized to adjust the pressure and the temperature in the calibration box to set values;
step 17: when the temperature of the calibration box reaches the set temperature and the pressure reaches the set pressure and is stable, waiting for a preset time to ensure that the calibration box fully reaches thermal balance, then exciting the PSP by using a laser, and continuously acquiring two PSP test images under the pressure and the temperature by using a CCD camera;
step 18: repeating the steps 16 and 17 until the PSP test image acquisition under all the set temperatures and the set pressures is completed;
step 19: calculating the light intensity ratio of two PSP reference images which are continuously acquired, calculating the light intensity ratio of two PSP test images which are continuously acquired, calculating the light intensity ratio of the PSP reference images to the PSP test images, and calculating the pressure ratio of the set pressure to the reference pressure;
step 20: performing linear fitting on the light intensity ratio and the corresponding pressure ratio under different test states to obtain the pressure sensitivity of the PSP;
wherein the ratio of the light intensities of the two PSP reference images is (I 2 /I 1 ) ref The light intensity ratio of the two PSP test images is I 2 /I 1 The light intensity ratio of the PSP reference image to the PSP test image is as followsThe pressure ratio of the set pressure to the reference pressure is +.>A linear function can be obtained after linear fitting, the expression is shown in the formula, A (T) and B (T) in the formula are constants related to temperature, A (T) and B (T) can be obtained through calibration, and B (T) is the pressure sensitivity of PSP.
Specifically, step 3 includes:
step 31: spraying the quick response PSP and TSP on the surfaces of two different paddles respectively;
step 32: manually marking a plurality of marking points at the front edge and the rear edge of the surface of the blade;
step 33: exciting PSP and TSP to emit light by using a laser;
step 34: continuously acquiring two reference images of PSP and TSP in a static state;
step 35: starting a rotor wing, providing a trigger signal by using a photoelectric sensor arranged on a rotor wing test stand, and continuously acquiring two test images by using a computer control camera under a fixed phase;
step 36: and under the same phase, the computer is used for controlling the camera to acquire test images of a plurality of periods.
Specifically, step 4 includes:
step 41: performing deblurring treatment on the test image acquired in the test state by adopting an image deblurring algorithm;
step 42: carrying out image registration on the reference image and the test image acquired in the test state by adopting an image registration algorithm based on the mark points;
step 43: calculating the light intensity ratio of two reference images continuously collected in a test state, calculating the light intensity ratio of two test images continuously collected in a plurality of periods in the test state, respectively calculating the light intensity ratio of the PSP reference image and the PSP test image, and calculating the pressure ratio of the set pressure to the reference pressure;
step 44: and calculating according to the pressure sensitivity of the PSP obtained by calibration and a formula to obtain the blade surface pressure value in the test state.
Specifically, the acquisition time of the first test image is a pulse excitation period, and the acquisition time of the second test image is a luminescence response attenuation process.
Specifically, the pressure control range is 0-2 times standard atmospheric pressure, and the temperature control range is 0-80 ℃.
Specifically, the reference temperature at the time of static calibration of PSP was 25℃and the reference pressure was 100kPa.
In a second aspect, the present application provides a PSP measurement system, the PSP measurement system comprising a laser, a CCD camera, a lens, an optical filter, a synchronizer, and a computer, wherein:
the CCD camera is connected with the lens, an optical filter is arranged in front of the lens, the computer is connected with the CCD camera through an optical fiber and used for realizing test data transmission, and the computer is connected with the synchronizer through a signal wire and used for controlling the test data acquisition process; the laser generator is connected with the synchronizer through a signal wire and is used for realizing synchronous control of the laser and the camera and synchronous acquisition of images.
In summary, the blade surface pressure measurement method based on the quick response PSP provided by the invention is a continuous large-view-field controllable non-contact pressure measurement method, and the quick response PSP is calibrated to obtain the pressure sensitivity of the quick response PSP; then constructing a helicopter model rotor blade surface pressure measurement system based on a quick response PSP, and carrying out a test on a helicopter model rotor test bed by using a bearingless model rotor blade with the diameter of 4m to obtain a blade surface pressure distribution image; then, performing deblurring treatment on the blade surface pressure image by adopting an image deblurring algorithm, and matching the blade surface pressure image under different working conditions by adopting an image registration algorithm based on mark points; and finally, calculating to obtain the blade surface pressure distribution condition by combining the calibration data. The method can meet the requirements of unsteady wind tunnel tests and large-area pressure pulsation capture, and can provide global pressure distribution data and flow display images for researching complex aerodynamic phenomena such as paddle vortex interference, airflow separation point positions, pneumatic noise and pressure distribution relation and the like.
Drawings
FIG. 1 is a static pressure calibration result of PSP.
Fig. 2 is a schematic diagram of a PSP measurement system.
Detailed Description
Aiming at the problem of unsteady pressure measurement of the surface of a rotor blade of a helicopter model, the invention provides a blade surface pressure measurement method and a PSP measurement system based on a quick response PSP.
The present invention will be described in further detail below.
Example 1
The application provides a blade surface pressure measurement method and a PSP measurement system based on a quick response PSP, wherein the method comprises the following steps:
step 1: obtaining the pressure sensitivity of PSP by using a PSP calibration method;
specifically, step 1 includes:
step 11: setting the pressure control range of the static pressure calibration system to be 0-2 times of standard atmospheric pressure, and setting the temperature control range to be 0-80 ℃;
step 12: when PSP is calibrated, placing a sample wafer sprayed with PSP in a calibration box;
step 13: the pressure controller and the temperature controller are respectively utilized to adjust the pressure and the temperature in the calibration box to set values;
step 14: when the temperature of the calibration box reaches the reference temperature and the pressure reaches the reference pressure and is stable, waiting for a preset time to ensure that the calibration box fully reaches the heat balance, then exciting the PSP by using a laser, and continuously acquiring two PSP reference images under the pressure and the temperature by using a CCD camera;
wherein, the reference temperature is 25 ℃ and the reference pressure is 100kPa when PSP is statically calibrated. The laser comprises a 532nm laser. The CCD camera comprises a 14-bit CCD camera. The preset time includes 5 minutes.
Step 15: setting a set of temperature and pressure values;
step 16: the pressure controller and the temperature controller are respectively utilized to adjust the pressure and the temperature in the calibration box to set values;
step 17: when the temperature of the calibration box reaches the set temperature and the pressure reaches the set pressure and is stable, waiting for a preset time to ensure that the calibration box fully reaches thermal balance, then exciting the PSP by using a laser, and continuously acquiring two PSP test images under the pressure and the temperature by using a CCD camera;
step 18: repeating the steps 16 and 17 until the PSP test image acquisition under all the set temperatures and the set pressures is completed;
step 19: calculating the light intensity ratio of two PSP reference images which are continuously acquired, calculating the light intensity ratio of two PSP test images which are continuously acquired, calculating the light intensity ratio of the PSP reference images to the PSP test images, and calculating the pressure ratio of the set pressure to the reference pressure;
step 20: and performing linear fitting on the light intensity ratio and the corresponding pressure ratio under different test states to obtain the pressure sensitivity of the PSP.
Wherein the ratio of the light intensities of the two PSP reference images is (I 2 /I 1 ) ref The light intensity ratio of the two PSP test images is I 2 /I 1 The light intensity ratio of the PSP reference image to the PSP test image is as followsThe pressure ratio of the set pressure to the reference pressure is +.>A linear function can be obtained after linear fitting, the expression is shown in the formula, A (T) and B (T) in the formula are constants related to temperature, A (T) and B (T) can be obtained through calibration, and B (T) is the pressure sensitivity of PSP.
For example, the PSP pressure sensitivity is 1%/kPa, calculated from the calibration results.
It should be noted that, the static calibration is mainly used to obtain the pressure sensitivity of the PSP, so as to finally convert the light intensity ratio into the pressure ratio.
Step 2: constructing a PSP measurement system;
the PSP measurement system comprises a laser, a CCD camera, a lens, an optical filter, a synchronizer and a computer, wherein: the CCD camera is connected with the lens, an optical filter is arranged in front of the lens, the computer is connected with the CCD camera through an optical fiber and used for realizing test data transmission, and the computer is connected with the synchronizer through a signal wire and used for controlling the test data acquisition process; the laser generator is connected with the synchronizer through a signal wire and is used for realizing synchronous control of the laser and the camera and synchronous acquisition of images.
Wherein the laser comprises a 532nm high energy pulsed laser generator.
Step 3: acquiring test data by using a PSP measurement system;
specifically, step 3 includes:
step 31: spraying the quick response PSP and TSP on the surfaces of two different paddles respectively;
step 32: manually marking a plurality of marking points at the front edge and the rear edge of the surface of the blade;
step 33: exciting PSP and TSP to emit light by using a laser;
step 34: continuously acquiring two reference images of PSP and TSP in a static state;
step 33: the rotor wing is started, a photoelectric sensor arranged on a rotor wing test stand is utilized to provide a trigger signal, and a computer is utilized to control a camera to continuously acquire two test images under a fixed phase, wherein the acquisition time of a first image is a pulse excitation period, and the acquisition time of a second image is a luminous response attenuation process.
Step 34: and under the same phase, the computer is used for controlling the camera to acquire test images of a plurality of periods.
The laser emitted by the laser is regulated by the reflector and uniformly covers the paint spraying area on the surface of the blade after being expanded by the beam expander. After the PSP and TSP are excited, two frames of images are continuously acquired using a CCD camera having a double exposure mode. A filter with a central wavelength of 600nm is arranged in front of the camera lens to filter out background light interference. The camera and the laser are controlled by a synchronizer. During the test, firstly, reference images of PSP and TSP in a static state are acquired, then a rotor is started, a photoelectric sensor arranged on a rotor test stand is used for providing a trigger signal, and the PSP and TSP images are respectively acquired by adjusting the delay of the acquisition of the images by a camera. Under the same phase, the camera can be controlled to acquire images of a plurality of periods, and the average result of the phases of the plurality of periods is calculated to improve the signal to noise ratio of measurement.
In practical application, the PSP data acquisition method mainly comprises a light intensity method and a service life method. The lifetime method is effective for the acquisition of surface pressure data of the rotating blade and can overcome the problem of blade deformation. Therefore, a single pulse life method is adopted in the test process to realize PSP data acquisition.
Step 4: data processing is performed on the test data according to the pressure sensitivity of the PSP.
Specifically, step 4 includes:
step 41: performing deblurring treatment on the test image acquired in the test state by adopting an image deblurring algorithm;
step 42: carrying out image registration on the reference image and the test image acquired in the test state by adopting an image registration algorithm based on the mark points;
step 43: calculating the light intensity ratio of two reference images continuously collected in a test state, calculating the light intensity ratio of two test images continuously collected in a plurality of periods in the test state, respectively calculating the light intensity ratio of the PSP reference image and the PSP test image, and calculating the pressure ratio of the set pressure to the reference pressure;
step 44: and calculating according to the pressure sensitivity of the PSP obtained by calibration and a formula to obtain the blade surface pressure value in the test state.
The method is characterized in that a blur kernel in the PSP image blurring process is calculated based on the attenuation law of the PSP luminous life and the motion law of the rotating blades, and deconvolution operation is carried out on the generated blur kernel image, so that a clear image is restored. Before the test, a plurality of mark points are marked on the surface of the blade manually, and then an image matching algorithm based on the mark points is carried out on PSP images under different working conditions. The algorithm can effectively solve the problem of image mismatch caused by phase difference between the PSP reference image and the test image, blade waving deformation and the like.
Example two
As shown in FIG. 1, the present application provides a static pressure calibration result for PSP, wherein the abscissa in the graphRepresenting the ratio of the set pressure to the reference pressure, the ordinate/>Representing the ratio of the light intensities of the PSP reference image and the PSP test image, (I) 2 /I 1 ) ref Representing the light intensity ratio of two PSP test images, I 2 /I 1 The light intensity ratio of the two PSP test images is shown, the slope of the straight line after linear fitting is the pressure sensitivity of the PSP, and the pressure sensitivity of the PSP is calculated to be 1%/kPa.
As shown in fig. 2, the present application provides a blade surface pressure measurement method based on a fast response PSP, and the method is applied to a PSP measurement system; the PSP measurement system comprises a laser, a CCD camera, a lens, an optical filter, a synchronizer and a computer, wherein: the CCD camera is connected with the lens, an optical filter is arranged in front of the lens, the computer is connected with the CCD camera through an optical fiber and used for realizing test data transmission, and the computer is connected with the synchronizer through a signal wire and used for controlling the test data acquisition process; the laser generator is connected with the synchronizer through a signal wire and is used for realizing synchronous control of the laser and the camera and synchronous acquisition of images.
Wherein the laser comprises a 532nm high energy pulsed laser generator.
Preferably, a PCO.1600 camera is selected to be matched with a 50mm fixed-focus lens to realize PSP image acquisition, and the pixels of the camera are 1600 multiplied by 1200 and 14b it images. The 532nm high energy pulsed laser generator is capable of generating a pulsed laser beam of sufficient intensity for illuminating the PSP and TSP coated blade surfaces. The synchronizer is used for controlling the camera and the laser generator to realize synchronous acquisition. The computer is mainly used for storing and processing the acquired PSP image and completing the flow display of blade surface pressure.
In summary, the invention realizes the acquisition of the unsteady pressure data of the blade surface by using the PSP pressure measurement technology, processes the blade surface pressure image by adopting an image deblurring algorithm and an image registration algorithm, and reduces the influence of image quality on the blade surface pressure measurement result. Compared with the traditional pressure measuring method, the method provided by the invention has the advantages of high measurement precision, high spatial resolution and visual measurement result, and can provide accurate data support for helicopter aerodynamics research.
Claims (8)
1. A method for measuring blade surface pressure based on a fast response PSP, the method comprising:
step 1: obtaining the pressure sensitivity of PSP by using a PSP calibration method;
step 2: constructing a PSP measurement system, wherein the PSP measurement system comprises a laser, a CCD camera, a lens, an optical filter, a synchronizer and a computer;
step 3: acquiring test data by using a PSP measurement system;
step 4: data processing is performed on the test data according to the pressure sensitivity of the PSP.
2. The method of claim 1, wherein step 1 comprises:
step 11: setting a pressure control range and a temperature control range of a static pressure calibration system;
step 12: when PSP is calibrated, placing a sample wafer sprayed with PSP in a calibration box;
step 13: the pressure controller and the temperature controller are respectively utilized to adjust the pressure and the temperature in the calibration box to the reference value;
step 14: when the temperature of the calibration box reaches the reference temperature and the pressure reaches the reference pressure and is stable, waiting for a preset time to ensure that the calibration box fully reaches the heat balance, then exciting the PSP by using a laser, and continuously acquiring two PSP reference images under the pressure and the temperature by using a CCD camera;
step 15: setting a set of temperature and pressure values;
step 16: the pressure controller and the temperature controller are respectively utilized to adjust the pressure and the temperature in the calibration box to set values;
step 17: when the temperature of the calibration box reaches the set temperature and the pressure reaches the set pressure and is stable, waiting for a preset time to ensure that the calibration box fully reaches thermal balance, then exciting the PSP by using a laser, and continuously acquiring two PSP test images under the pressure and the temperature by using a CCD camera;
step 18: repeating the steps 16 and 17 until the PSP test image acquisition under all the set temperatures and the set pressures is completed;
step 19: calculating the light intensity ratio of two PSP reference images which are continuously acquired, calculating the light intensity ratio of two PSP test images which are continuously acquired, calculating the light intensity ratio of the PSP reference images to the PSP test images, and calculating the pressure ratio of the set pressure to the reference pressure;
step 20: performing linear fitting on the light intensity ratio and the corresponding pressure ratio under different test states to obtain the pressure sensitivity of the PSP;
wherein the ratio of the light intensities of the two PSP reference images is (I 2 /I 1 ) ref The light intensity ratio of the two PSP test images is I 2 /I 1 The light intensity ratio of the PSP reference image to the PSP test image is as followsThe ratio of the set pressure to the reference pressure isA linear function can be obtained after linear fitting, the expression is shown in the formula, A (T) and B (T) in the formula are constants related to temperature, A (T) and B (T) can be obtained through calibration, and B (T) is the pressure sensitivity of PSP.
3. The method of claim 1, wherein step 3 comprises:
step 31: spraying the quick response PSP and TSP on the surfaces of two different paddles respectively;
step 32: manually marking a plurality of marking points at the front edge and the rear edge of the surface of the blade;
step 33: exciting PSP and TSP to emit light by using a laser;
step 34: continuously acquiring two reference images of PSP and TSP in a static state;
step 35: starting a rotor wing, providing a trigger signal by using a photoelectric sensor arranged on a rotor wing test stand, and continuously acquiring two test images by using a computer control camera under a fixed phase;
step 36: and under the same phase, the computer is used for controlling the camera to acquire test images of a plurality of periods.
4. The method of claim 1, wherein step 4 comprises:
step 41: performing deblurring treatment on the test image acquired in the test state by adopting an image deblurring algorithm;
step 42: carrying out image registration on the reference image and the test image acquired in the test state by adopting an image registration algorithm based on the mark points;
step 43: calculating the light intensity ratio of two reference images continuously collected in a test state, calculating the light intensity ratio of two test images continuously collected in a plurality of periods in the test state, respectively calculating the light intensity ratio of the PSP reference image and the PSP test image, and calculating the pressure ratio of the set pressure to the reference pressure;
step 44: according to the pressure sensitivity of PSP obtained by calibration, the method is as followsAnd calculating to obtain the blade surface pressure value in the test state.
5. A method according to claim 3, wherein the first test image is acquired at a time during the pulse excitation and the second test image is acquired at a time during the decay of the luminescence response.
6. The method of claim 2, wherein the pressure is controlled in the range of 0-2 times the standard atmospheric pressure and the temperature is controlled in the range of 0-80 degrees celsius.
7. The method of claim 2, wherein the reference temperature at which the PSP is statically calibrated is 25 ℃ and the reference pressure is 100kPa.
8. A PSP measurement system, characterized in that the PSP measurement system comprises a laser, a CCD camera, a lens, an optical filter, a synchronizer and a computer, wherein:
the CCD camera is connected with the lens, an optical filter is arranged in front of the lens, the computer is connected with the CCD camera through an optical fiber and used for realizing test data transmission, and the computer is connected with the synchronizer through a signal wire and used for controlling the test data acquisition process; the laser generator is connected with the synchronizer through a signal wire and is used for realizing synchronous control of the laser and the camera and synchronous acquisition of images.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311507083.9A CN117571192A (en) | 2023-11-13 | 2023-11-13 | Blade surface pressure measurement method and system based on quick response PSP |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311507083.9A CN117571192A (en) | 2023-11-13 | 2023-11-13 | Blade surface pressure measurement method and system based on quick response PSP |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117571192A true CN117571192A (en) | 2024-02-20 |
Family
ID=89861766
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311507083.9A Pending CN117571192A (en) | 2023-11-13 | 2023-11-13 | Blade surface pressure measurement method and system based on quick response PSP |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117571192A (en) |
-
2023
- 2023-11-13 CN CN202311507083.9A patent/CN117571192A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106501227B (en) | Measurement method based on pressure sensitive coating probe molecule fluorescence lifetime | |
| Kavandi et al. | Luminescent barometry in wind tunnels | |
| Wong et al. | Blade tip pressure measurements using pressure-sensitive paint | |
| JPH0712661A (en) | Method for measuring pressure of gas containing oxygen on surface, method for visualizing gas containing oxygen on surface and pressure sensitive composition | |
| CN111458101A (en) | Method for measuring surface pulsating pressure of wind tunnel fixed wing model | |
| EP0990130B1 (en) | Method for determining pressure | |
| CN111707382B (en) | Dynamic optical compensation method and device for synchronous measurement of temperature deformation | |
| CN114739626B (en) | Rotating blade grid pressure measurement test method based on quick response pressure-sensitive paint | |
| CN109253992A (en) | A kind of plasma fluorescence lifetime measurement device and method | |
| CN114061894B (en) | Cavity model pulsating pressure and noise measurement system | |
| Morris et al. | Aerodynamic measurements based on photoluminescence | |
| JP4953245B2 (en) | Temperature dependence correction method by time-series temperature change of pressure sensitive paint measurement method | |
| Bell | Pressure-sensitive paint measurements on the NASA common research model in the NASA 11-ft transonic wind tunnel | |
| CN117571192A (en) | Blade surface pressure measurement method and system based on quick response PSP | |
| CN112197713B (en) | Device and method for synchronously measuring deformation and surface pressure of helicopter rotor blade | |
| CN114354036B (en) | Method and device for synchronously measuring surface pressure and three-dimensional shape of motion model | |
| CN114061895B (en) | Image acquisition method for measuring pulsating pressure and noise of cavity model | |
| Morris et al. | Application of pressure-and temperature-sensitive paints to high-speed flows | |
| Murakami et al. | Implementation of the Lifetime Method in Unsteady Pressure-Sensitive Paint Measurements | |
| Peng et al. | Development of a grid PSP/TSP system for unsteady measurements on rotating surfaces | |
| Dong et al. | Pressure-sensitive paint integrated with digital image correlation for instantaneous measurement on rotating blades | |
| Chana et al. | Infrared temperature measurements on high pressure turbine blades in the Oxford Turbine Research Facility: calibration and image processing techniques | |
| CN114152210A (en) | Synchronous measurement system for surface deformation and pressure distribution of rotating part | |
| Li et al. | A dual-camera single-shot lifetime method with fully controllable exposure gates for pressure-sensitive paint measurements on fast-rotating surfaces | |
| Jiao et al. | Lifetime-based PSP and TSP measurements on rotating blades with high rotation rate |
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 |