A turbine blade film hole structure parameter measuring device and method

Abstract

The application discloses a turbine blade gas film hole structure parameter measuring device and method, and belongs to the turbine blade gas film hole measuring technical field.The device comprises an air source supply unit, a blade clamping and air inlet module, a background auxiliary module, an auxiliary enhancement excitation control module, an infrared image and visible light image acquisition module and an image processing display and transmission module; the image processing display and transmission module is used for performing enhancement processing on the obtained infrared image and visible light image, and calculating the gas film hole permeability, size parameter and position degree parameter by using an inversion algorithm; the visible light-infrared image double-view fusion algorithm is used to realize the visual display of the gas film hole plume, the visible light picture and infrared picture information of the gas film hole measuring process are fused and displayed, and the gas film hole quality is obtained.The application improves the turbine blade gas film hole measuring efficiency, and further improves the performance and operation reliability of the heavy-duty gas turbine, reduces the accident rate and improves the production efficiency.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of turbine blade film hole structure parameter measurement, and particularly to a turbine blade film hole structure parameter measurement device and method. BACKGROUND

[0002] Heavy gas turbine is the most efficient heat-power conversion power generation equipment so far, and is the core equipment in the field of power generation and driving. Due to the great difficulty in design and manufacture, it reflects the industrial level of a country. The working temperature of F-class heavy gas turbine can reach 1300℃ or above. In order to ensure the safe and stable operation of high-temperature turbine blades above the melting point of metal, the high-temperature turbine blade is designed as a hollow structure. When the blade rotates at high speed, air enters the inside of the blade to form convection cooling. A large number of film cooling holes are processed on the blade body to realize film cooling at high speed. The film cooling hole has the characteristics of small aperture, large number, high depth-diameter ratio and complex space angle. Its processing difficulty is great, and the forming precision is high. The processing precision of the blade film cooling hole directly affects the cooling efficiency of the blade, and then directly affects the performance of the heavy gas turbine. Therefore, it is very important to realize the rapid measurement of the film cooling hole.

[0003] In the aspect of turbine blade film cooling hole diameter detection, according to the different detection methods, it can be roughly divided into two technical means of contact type and non-contact type detection; the three-coordinate measuring machine based on the contact probe contacts the surface of the measured workpiece through the probe with the probe, obtains the three-dimensional coordinates of the measured points, and then obtains the related geometric parameters of the measured workpiece. Due to the limitation of working principle, it is necessary to ensure that the probe diameter is smaller than the film hole diameter, so that the probe can enter the inside of the film hole for measurement, and the measurement efficiency is low; in the aspect of non-contact detection technology of turbine blade film cooling hole diameter, according to the different measurement principles, it can be roughly divided into non-optical detection and optical detection; the main non-optical detection means is computerized tomography (CT). Due to the high cost of industrial CT equipment, it is generally applied to precision measurement in professional detection institutions, and its application in production line is less; in the aspect of camera-based visual detection, it mainly uses CCD camera to shoot and obtain the surface image of the measured workpiece, and then calculates the geometric parameter size of the measured workpiece through image enlargement, enhancement, filtering, edge extraction and other operations. However, due to the limitation of factors such as CCD camera focal length, it is difficult to collect all the accurate image information of the film hole on the turbine blade curved surface in the same focal plane, resulting in low detection accuracy.

[0004] Infrared imaging technology, with its advantages of high efficiency and dynamic intuitiveness, has been widely used in various industries. Since its development and application, active thermal excitation imaging technology has usually been used for non-destructive testing of metals, non-metals, and various composite materials and defects. The analysis objects are the temperature changes of the material itself after excitation. It has not yet been applied to the field of film pore measurement and the characteristic identification and analysis of gas plumes. Summary of the Invention

[0005] To address the problems existing in the prior art, this invention proposes a device and method for measuring the structural parameters of film venting in turbine blades. This invention achieves rapid and efficient measurement of film venting structural parameters. The film venting measurement system has high measurement efficiency and reliable results, enabling comprehensive measurement of both the surface and internal structural information of the film venting, thus solving the problems of inaccurate measurement, low efficiency, and unclear measurement parameters in film venting measurements.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A device for measuring the air film pore structure parameters of a turbine blade includes:

[0008] The gas supply unit is used to supply gas to the turbine blades;

[0009] The blade clamping and air intake module is used to fix and adjust the position of the blades and connect to the air supply module.

[0010] The background auxiliary module is used to provide different background plates for the measurement of the film film aperture of the blade. By clamping the blade and rotating the blade through the air inlet module, images of the plume out of the film film aperture at different angles are obtained.

[0011] An auxiliary enhancement excitation and control module is used to change the radiation intensity of the environment around the air film pore using a photothermal pulse source;

[0012] Infrared and visible light image acquisition modules are used to image the film gas vents and the plume formed by the outflowing gas;

[0013] The image processing, display, and transmission module is used to acquire the image storage data from the infrared and visible light image acquisition modules. It enhances the obtained infrared and visible light images and uses an inversion algorithm to calculate the permeability, size parameters, and positional parameters of the film pore. It extracts complementary information from the natural light and visible light images and uses a visible-infrared image dual-view fusion algorithm to visualize the film pore plume. It fuses and displays the visible light and infrared image information from the film pore measurement process to obtain the film pore quality status.

[0014] As a further improvement of the present application, the gas source supply module comprises an air compressor, a gas cylinder, a gas heater, a pressure regulating valve, a gas flow meter and a fluid control valve, which provide gas for the turbine blade.

[0015] As a further improvement of the present application, the blade clamping and air inlet module comprises a lifting unit, a gas source interface, a rotating unit and a blade clamp unit, the rotating unit is arranged on the lifting unit, the blade clamp unit is arranged on the rotating unit, the rotating unit is provided with a through hole in the center, and the gas source interface is arranged at the bottom of the blade clamp unit and placed in the through hole; the blade clamp unit has a mortise and tenon joint for quick clamping and fixing of the blade, and the gas source interface is connected to the blade clamp unit through integrated design.

[0016] As a further improvement of the present application, the background auxiliary module comprises a replaceable background plate, a background plate clamp unit and a temperature regulator, the measured blade and the replaceable background plate are fixed and kept in relative position by the background plate clamp unit, and the temperature regulator is arranged on one side of the replaceable background plate.

[0017] As a further improvement of the present application, the auxiliary enhancement excitation control module comprises a pulse excitation array, a pulse excitation control unit and a synchronous trigger unit; the pulse excitation array is composed of an array of xenon lamp tubes, the pulse excitation control unit controls the trigger power and trigger frequency of the pulse excitation array, and the synchronous trigger unit controls the time interval between the start of the pulse excitation array and the infrared image and visible light image acquisition module.

[0018] As a further improvement of the present application, the infrared image and visible light image acquisition module comprises a visible light imager, an infrared imager and an image data storage and transmission unit, the infrared imager receives the enhanced infrared radiation field generated by the joint action of the background auxiliary module and the auxiliary enhancement excitation control module, and images the gas film hole outflow plume, and the image data storage and transmission unit stores and transmits the images collected by the visible light imager and the infrared imager to the image processing display and transmission module.

[0019] As a further improvement of the present application, the image processing display and transmission module comprises an image enhancement and noise reduction unit, an image feature extraction unit, a gas film hole structure parameter inversion unit, an image fusion unit and a display screen transmission unit; after the images transmitted from the image data storage and transmission unit pass through the image enhancement and noise reduction unit, the image feature extraction unit extracts the gas film hole plume features, the gas film hole structure parameters are obtained by using the gas film hole structure parameter inversion unit, the visible light image and the infrared image are input into the image fusion unit, the measurement results are visualized, and the visualized results are input into the display screen transmission unit, and the measurement results are uploaded to the measurement center.

[0020] As a further improvement of the application, in the image processing display and transmission module, the gas film hole outflow gas plume image information is used to inversely calculate the gas film hole permeability, aperture and position degree parameters, including:

[0021] According to the standard hole outflow image modeling, the plume angle and area function of different apertures are obtained, and the equivalent aperture is inversely calculated according to the correlation model; the infrared image is first processed for noise reduction and enhancement, the image segmentation algorithm is used to segment the airflow image part in the image, the gas film hole area is segmented by using the adaptive piecewise linear transformation according to the gray distribution characteristics of the image, the permeability is judged according to the area threshold of the plume of the outflow area corresponding to each gas film hole, then the characteristic information of the gas plume part is extracted, the characteristic information is input into the correlation model, and the aperture and position degree parameters of the gas film hole are output according to the characteristic information; the gas film hole position extraction data of the visible light image is obtained, the gas film hole distribution position coordinates are obtained, and the position degree parameters are obtained.

[0022] As a further improvement of the application, in the image processing display and transmission module, the complementary information of the natural light image and the visible light image is extracted, the visible light-infrared image double-view fusion algorithm is used to realize the visual display of the gas film hole plume, and the visible light picture and infrared picture information of the gas film hole measurement process are fused and displayed, including:

[0023] The coordinates of the visible light and infrared images are aligned, the images are registered, the infrared image pixels are interpolated and supplemented, and the visible light image and infrared image pixels are aligned; the weight is determined according to the activity of different pixels, and the visible light-infrared image is fused and displayed based on the adaptive weight distribution fusion algorithm.

[0024] A turbine blade gas film hole structure parameter measurement method, comprising:

[0025] Compressed gas is introduced into the turbine blade, and the background auxiliary module and the auxiliary enhancement excitation and control module emit light-heat pulse excitation to enhance the infrared radiation difference between the outflow gas plume and the gas-free area; the infrared image and visible light image acquisition module are used to image the gas film hole outflow gas plume, the image processing display and transmission module processes the obtained infrared image, extracts the morphological characteristics of the gas plume, inversely calculates the gas film hole structure parameters, uses visible light to measure the gas film hole distribution, fuses the measurement results, visually displays the measurement results on the display screen, and realizes qualitative and quantitative measurement of the gas film hole permeability and structure parameters.

[0026] Compared with the prior art, the advantages of the present application are:

[0027] The turbine blade gas film hole structure parameter measuring device of the application utilizes the mode of active pulse light heat excitation combined with auxiliary background to enhance the infrared radiation difference between the gas film hole outflow gas plume and the surrounding air and the background, the infrared thermal image of the gas film hole outflow gas plume of the excited area is collected through the wide-wavelength infrared image collection module, the collected infrared image and visible light image are filtered, denoised, image rendered, image segmented, and the plume area is calibrated through the image processing display and wireless transmission module, and then displayed on the display screen; at the same time, the data obtained by processing is transmitted to the external server for receiving in real time through the wireless transmission unit, and the turbine blade gas film hole processing quality is reflected in real time. Through the steps of application of the light heat pulse source, infrared image collection and processing, fusion of the infrared image and the visible light image, and wireless transmission of the fused image, the measurement of the gas film hole structure parameter is realized. The application has wide application range and can be used for the measurement of the structure parameters of micro-apertures in the power industry, the aerospace industry, the traditional manufacturing industry and other industries, has wide application prospect and strong popularization value. BRIEF DESCRIPTION OF DRAWINGS

[0028] The drawings described herein are for illustrative purposes only and are not intended to limit the scope of the present disclosure in any way. In addition, the shapes and scale sizes of the components in the drawings are only illustrative and are used to help understand the present application and are not specific limitations on the shapes and scale sizes of the components of the present application. Those skilled in the art can select various possible shapes and scale sizes to implement the present application according to specific circumstances under the teaching of the present application. In the drawings:

[0029] Figure 1 A turbine blade gas film hole structure parameter measuring device principle diagram is given for the embodiment of the present application;

[0030] Figure 2 A general working process of the measuring system is given for the embodiment of the present application;

[0031] Figure 3 A cross-sectional view of the front view of the blade clamp and the air inlet module is given for the embodiment of the present application;

[0032] Figure 4 A front view of the relative position of the background plate and the temperature controller and the blade is given for the embodiment of the present application;

[0033] Figure 5 A top view of the relative position of the background plate and the temperature controller and the blade is given for the embodiment of the present application;

[0034] Figure 6 A diagram of the background plate fixing clamp of the present application is given;

[0035] Wherein: 1-gas source supply module, 100-air compressor, 101-gas cylinder, 102-gas heater, 103-pressure regulating valve, 104-gas flow meter, 105-and fluid control valve; 2-blade clamping and air intake module, 200-lifting unit, 201-gas source interface, 202-rotary unit, 203-blade clamp unit; 3-background auxiliary module, 300-replaceable background plate, 301-background plate clamp unit, 302-temperature regulator; 4-assisted enhanced excitation and control module, 400-pulse excitation array, 401-pulse excitation control unit, 402-synchronous trigger unit; 5-infrared image and visible light image acquisition module, 500-visible light imager, 501-infrared imager, 502-image data storage and transmission unit; 6-image processing display and transmission module, 600-image enhancement and noise reduction unit, 601-image feature extraction unit, 602-gas film hole structure parameter inversion unit, 603-image fusion unit, 604-display screen transmission unit. Specific embodiments

[0036] In order to make the technical personnel in the technical field better understand the technical solutions in the present application, the technical solutions in the embodiments of the present application will be described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, not all. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor shall belong to the scope of protection of the present application.

[0037] It should be noted that when an element is referred to as "disposed on" another element, it can be directly on the other element or there can be an intervening element. When an element is referred to as "connected" to another element, it can be directly connected to the other element or there can be an intervening element. The terms "vertical", "horizontal", "left", "right", and similar expressions used herein are for illustrative purposes only and are not intended to be limiting.

[0038] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description of the application herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.

[0039] The present application will be further described in conjunction with specific examples and drawings, which are an explanation of the present application and not a limitation.

[0040] As Figure 1The first object of the present application is to provide a turbine blade gas film hole structure parameter measuring device, comprising: a gas source supply module 1, a blade clamping and air inlet module 2, a background auxiliary module 3, an auxiliary enhancement excitation and control module 4, an infrared image and visible light image acquisition module 5, an image processing display and transmission module 6;

[0041] The gas source supply module 1 is used to provide gas for the turbine blade; the turbine blade is provided with gas of specified temperature, specified pressure and flow rate, and air, nitrogen, carbon dioxide can be used according to the situation;

[0042] The blade clamping and air inlet module 2 is used to fix and adjust the position of the blade and communicate with the gas source supply module 1; specifically, it is used to fix and adjust the position of the blade and is provided with a gas source interface 201 to communicate with the gas source supply module 1, so as to realize the fixation, lifting and rotation of the blade, and the turbine blade is fixed by using the mortise and tenon structure;

[0043] The background auxiliary module 3 is used to provide different background plates for blade gas film hole measurement, and the images of different angles of the gas film hole outflow plume are obtained by rotating the blade through the blade clamping and air inlet module 2; specifically, different background plates 300 are provided for blade gas film hole measurement, and the relative position of the blade and the background plate 300 is fixed, and the images of different angles of the gas film hole outflow plume are obtained by rotating the blade;

[0044] The auxiliary enhancement excitation and control module 4 is used to image the plume formed by the gas film hole and the outflow gas; the radiation intensity of the environment around the gas film hole is changed by using a high-power flash lamp to improve the infrared imaging quality of the gas film hole outflow plume;

[0045] The infrared image and visible light image acquisition module 5 images the plume formed by the gas film hole and the outflow gas by using an infrared imager 501 and a visible light imager 500, and stores and sends the obtained images to the image processing display and transmission module 6;

[0046] The image processing display and transmission module 6 is used to obtain the image storage data of the infrared image and visible light image acquisition module 5, to enhance the obtained infrared image and visible light image, and to calculate the gas film hole permeability, size parameter and position degree parameter by using an inversion algorithm; the complementary information of the natural light image and the visible light image is extracted, the visible light-infrared image double-view fusion algorithm is used to realize the visualization display of the gas film hole plume, the visible light picture and infrared picture information of the gas film hole measurement process is fused and displayed, and the quality of the gas film hole is obtained.

[0047] Wherein, as a specific scheme, the air source supply module 1 includes an air compressor 100, a gas cylinder 101, a gas heater 102, a pressure regulating valve 103, a gas flow meter 104 and a fluid control valve 105, the air compressor 100, the gas cylinder 101, the gas heater 102, the pressure regulating valve 103, the gas flow meter 104 and the fluid control valve 105 are connected in sequence, the air compressor 100 provides compressed air for the gas cylinder 101, the gas cylinder 101 ensures the stability of the air source during use, the compressed gas from the gas cylinder 101 passes through the pressure regulating valve 103 and the gas flow meter 104 to provide stable pressure and stable flow of the gas for the turbine blade, according to the experimental environment, the gas can also be heated by the gas heater 102, and the fluid control valve 105 can select continuous gas supply or pulse gas supply.

[0048] Wherein, the blade clamping and air inlet module 2, as shown in Figure 3 From bottom to top in sequence are a lifting unit 200, a rotating unit 202, an air source interface 201 and a blade clamp unit 203, the rotating unit 202 is arranged on the lifting unit 200, the blade clamp unit 203 is arranged on the rotating unit 202, the rotating unit 202 is provided with a through hole in the center, the air source interface 201 is arranged at the bottom of the blade clamp unit 203 and is arranged in the through hole. The different units between the modules adopt an integrated design, the air source interface 201 is connected to the blade clamp through the directly below, the lifting and rotation of the blade will not affect the air path, the fixing mode of the blade clamp unit adopts a mortise and tenon structure, which can realize rapid positioning and clamping, the position of the blade is adjusted by the lifting unit 200 and the rotating unit 202, and the film hole at different positions of the turbine blade blade body is measured.

[0049] Wherein, the background auxiliary module 3, the relative position of the blade and the background plate 300 is as shown in Figure 4 And Figure 5 The temperature regulator 302 is fixed to the back of the replaceable background plate 300 and is used to control the temperature of the background plate 300; as shown in Figure 6 The replaceable background plate 300 is fixed to the blade blade body through the background plate clamp unit 301.

[0050] Wherein, the auxiliary enhancement excitation control module 4 includes a pulse excitation array 400, a pulse excitation control unit 401 and a synchronous trigger unit 402, the pulse excitation array 400 is composed of a group of xenon lamp tube arrays, the trigger power and the start frequency of the pulse excitation array 400 are controlled by the pulse excitation control unit 401, the synchronous trigger unit 402 controls the start time interval between the pulse excitation array 400 and the infrared image and visible light image acquisition module, and ensures that the obtained infrared image is at the best excitation moment.

[0051] The infrared image and visible light image acquisition module 5 comprises a visible light imager 500, an infrared imager 501 and an image data storage and transmission unit 502, the infrared imager 501 receives the enhanced infrared radiation field generated by the joint action of the background auxiliary module 3 and the auxiliary enhancement excitation control module, and images the gas film hole outflow plume, and the image data storage and transmission unit 502 stores the images acquired by the visible light imager 500 and the infrared imager 501 and transmits the images to the image processing display and transmission module 6.

[0052] The image processing display and transmission module 6 comprises an image enhancement and noise reduction unit 600, an image feature extraction unit 601, a gas film hole structure parameter inversion unit 602, an image fusion unit 603 and a display screen transmission unit 604; after the images transmitted from the image data storage and transmission unit 502 pass through the image enhancement and noise reduction unit 600, the gas film hole plume features are extracted by the image feature extraction unit 601, the structure parameters of the gas film hole are obtained by the gas film hole structure parameter inversion unit 602, the visible light image and the infrared image are input into the image fusion unit 603, the measurement results are visualized, and the visualized results are input into the display screen transmission unit 604, the measurement results are uploaded to the measurement center, and the measurement is completed.

[0053] Further, by using the technical means such as active thermal excitation, infrared imaging, background assistance and image recognition method, the recognition accuracy is high, the range is wide, the results are comprehensive and accurate, and the efficient measurement of the gas film hole structure parameters of the turbine blade can be realized, and the problems of inaccurate measurement and low measurement efficiency of the gas film hole direct measurement are solved.

[0054] The application also provides a turbine blade gas film hole structure parameter measurement method, as shown in Figure 2 The general working process of the test device comprises the following steps:

[0055] The compressed gas is introduced into the turbine blade, the background auxiliary module 3 and the auxiliary enhancement excitation and control module 4 emit light-heat pulse excitation to enhance the infrared radiation difference between the outflow gas plume and the gas-free area; the infrared image and visible light image acquisition module 5 images the gas film hole outflow gas plume, the image processing display and transmission module 6 processes the obtained infrared image, extracts the morphological features of the gas plume, inversely measures the gas film hole structure parameters, measures the gas film hole distribution by using visible light, fuses the measurement results, and visually displays the measurement results on the display screen, so that the qualitative and quantitative measurement of the gas film hole permeability and structure parameters is realized.

[0056] The principle of the method is: the compressed gas is introduced into the turbine blade, the infrared radiation difference between the outflow gas plume and the gas-free area is enhanced by the auxiliary background plate 300 and the light-heat pulse excitation; the infrared imaging instrument 501 is used to image the gas film hole outflow gas plume, the obtained infrared image is denoised and enhanced, the morphological characteristics of the gas plume are extracted, and input into the correlation model to inversely measure the gas film hole structure parameters; the visible light is used to image the blade surface, the two-dimensional information of the blade gas film hole is extracted, and the distribution information of the gas film hole on the blade surface is obtained; the measurement results of visible light and infrared are fused, and the measurement results are visualized on the display screen, realizing the qualitative and quantitative measurement of the gas film hole permeability and structure parameters.

[0057] Specifically includes the following steps:

[0058] First, the measured blade and the auxiliary background are fixed by the clamp unit, the gas source supply module 1 is opened, the gas pressure, gas temperature, gas flow are set and the gas valve is opened, after the gas flow is stabilized, the auxiliary enhancement excitation module emits pulse excitation to the gas film hole area, after excitation enhancement and background enhancement, the infrared radiation difference is obviously enhanced, the excitation is applied at a certain frequency, and the infrared camera captures the infrared image of the gas film hole gas outflow area, at the same time, the visible light camera acquires the visible light picture of the blade, the captured picture is transmitted to the image processing display and transmission module 6 for processing analysis, and then input to the correlation model to inversely measure the structure information of the gas film hole, the measurement results of visible light and infrared image are fused to obtain the final measurement information, the measurement information is transmitted to the database for saving and display, the measurement is completed, and the next measured blade is replaced.

[0059] It should be understood that the above description is for illustration purposes only and is not intended to be limiting. Many embodiments and many applications other than the examples provided would be apparent to those of ordinary skill in the art from the above description. The scope of the present teachings should not be limited to the examples described above, but should be given the full scope of the metes and bounds of the claims and any equivalents thereof. The disclosures of all articles and references, including patent applications and publications, are incorporated by reference for all purposes. Any aspect of the subject matter disclosed herein that is not claimed is intended to be omitted from the subject matter sought to be patented.

Claims

1. A device for measuring the air film pore structure parameters of a turbine blade, characterized in that, include: Gas supply unit (1) is used to supply gas to turbine blades; The blade clamping and air intake module (2) is used to fix and adjust the position of the blade and connect to the air supply unit (1). Background auxiliary module (3) is used to provide different background plates for the measurement of the air film pores of the blade. By rotating the blade through the blade clamping and air intake module (2), images of the outflow plume from the air film pores at different angles can be obtained. The auxiliary enhancement excitation and control module (4) is used to change the radiation intensity of the environment around the air film pore using a photothermal pulse source; Infrared and visible light image acquisition module (5) is used to image the gas film aperture and the plume formed by the outflowing gas; The image processing, display and transmission module (6) is used to acquire the image storage data of the infrared image and visible light image acquisition module (5), enhance the obtained infrared image and visible light image, and use the inversion algorithm to calculate the permeability, size parameters and position parameters of the air film aperture; extract the complementary information of the natural light image and the visible light image, use the visible light-infrared image dual-view fusion algorithm to realize the visualization of the air film aperture plume, fuse the visible light image and infrared image information in the air film aperture measurement process, and obtain the air film aperture quality status; The image processing, display and transmission module (6) includes an image enhancement and noise reduction unit (600), an image feature extraction unit (601), an air film pore structure parameter inversion unit (602), an image fusion unit (603), and a display screen transmission unit (604). The image transmitted from the image data storage and transmission unit (502) is processed by the image enhancement and noise reduction unit (600). The image feature extraction unit (601) extracts the air film pore plume features, and the air film pore structure parameter inversion unit (602) obtains the air film pore structure parameters. The visible light image and the infrared image are input into the image fusion unit (603) to visualize the measurement results. The visualized results are then input into the display screen transmission unit (604) to upload the measurement results to the measurement center. In the image processing, display, and transmission module (6), the permeability, pore size, and position parameters of the film pore are calculated by inverting the image information of the gas plume outflow from the film pore, including: Modeling is performed based on standard orifice outflow images to obtain plume angles and area functions for different orifice diameters. The equivalent orifice diameter is then inferred from the correlation model. First, the infrared image is denoised and enhanced. An image segmentation algorithm is used to segment the airflow image portion of the image. Based on the image's grayscale distribution characteristics, an adaptive piecewise linear transformation is used to segment the film membrane orifice region. The permeability is determined based on the area threshold of the plume in the outflow region corresponding to each film membrane orifice. Then, feature information of the gas plume portion is extracted and input into the correlation model. Based on the feature information, the orifice diameter and positional parameters of the film membrane orifice are output. Finally, data on the film membrane orifice positions in the visible light image is extracted to obtain the coordinates of the film membrane orifice distribution, thus obtaining the positional parameters. In the image processing, display, and transmission module (6), complementary information from natural light and visible light images is extracted, and a visible-infrared image dual-view fusion algorithm is used to visualize the film aperture plume. The visible light and infrared image information of the film aperture measurement process are fused and displayed, including: The visible light and infrared images are aligned in coordinates and registered. The infrared image pixels are interpolated and supplemented to align the visible light and infrared image pixels. The weights are determined based on the activity of different pixels, and the visible light and infrared images are fused and displayed based on an adaptive weight allocation fusion algorithm.

2. The device for measuring the air film pore structure parameters of a turbine blade according to claim 1, characterized in that, The gas supply unit (1) includes an air compressor (100), a gas storage cylinder (101), a gas heater (102), a pressure regulating valve (103), a gas flow meter (104), and a fluid control valve (105). The air compressor (100), the gas storage cylinder (101), the gas heater (102), the pressure regulating valve (103), the gas flow meter (104), and the fluid control valve (105) provide gas to the turbine blades.

3. The device for measuring the air film pore structure parameters of a turbine blade according to claim 1, characterized in that, The blade clamping and air intake module (2) includes a lifting unit (200), an air source interface (201), a rotating unit (202), and a blade clamping unit (203). The rotating unit (202) is mounted on the lifting unit (200), and the blade clamping unit (203) is mounted on the rotating unit (202). The rotating unit (202) has a through hole at its center. The air source interface (201) is located at the bottom of the blade clamping unit (203) and is placed in the through hole. The blade clamping unit (203) has a tenon and mortise interface for quick clamping and fixing of the blade. The air source interface (201) is connected to the blade clamping unit (203) through an integrated design.

4. The device for measuring the air film pore structure parameters of a turbine blade according to claim 1, characterized in that, The background auxiliary module (3) includes a replaceable background plate (300), a background plate clamping unit (301), and a temperature regulator (302). The blade under test and the replaceable background plate (300) are fixed and kept in relative position by the background plate clamping unit (301), and the temperature regulator (302) is located on one side of the replaceable background plate (300).

5. The device for measuring the air film pore structure parameters of a turbine blade according to claim 1, characterized in that, The auxiliary enhancement excitation and control module (4) includes a pulse excitation array (400), a pulse excitation control unit (401), and a synchronous triggering unit (402). The pulse excitation array (400) consists of a set of xenon lamp arrays. The pulse excitation control unit (401) controls the triggering power and triggering frequency of the pulse excitation array (400). The synchronous triggering unit (402) controls the triggering time interval between the pulse excitation array (400) and the infrared image and visible light image acquisition module (5).

6. The device for measuring the air film pore structure parameters of a turbine blade according to claim 1, characterized in that, The infrared and visible light image acquisition module (5) includes a visible light imager (500), an infrared imager (501), and an image data storage and transmission unit (502). The infrared imager (501) receives the enhanced infrared radiation field generated by the combined action of the background auxiliary module (3) and the auxiliary enhancement excitation and control module (4) to image the outflow plume from the film vent. The image data storage and transmission unit (502) stores the images acquired by the visible light imager (500) and the infrared imager (501) and sends them to the image processing, display and transmission module (6).

7. A method for measuring the air film pore structure parameters of a turbine blade, comprising using the air film pore structure parameter measuring device of any one of claims 1 to 6, characterized in that, include: Compressed gas is introduced into the turbine blade, and photothermal pulse excitation is emitted through the background auxiliary module (3) and the auxiliary enhancement excitation and control module (4) to enhance the infrared radiation difference between the outflow gas plume and the area without gas. The outflow gas plume from the film pore is imaged by the infrared image and visible light image acquisition module (5). The image processing, display and transmission module (6) processes the obtained infrared image, extracts the morphological features of the gas plume, inverts and measures the structural parameters of the film pore, measures the distribution of the film pore using visible light, and fuses the measurement results. The measurement results are then visualized on the display screen to achieve qualitative and quantitative measurement of the permeability and structural parameters of the film pore.

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