Device and method for measuring mounting angle of stator blade of air compressor of aero-engine

Abstract

The invention relates to an aero-engine compressor stator blade mounting angle measuring device and method, and belongs to the technical field of aero-engines. The aero-engine compressor stator blade mounting angle measuring device comprises blade measuring assemblies arranged on the front edge and the rear edge of a blade and used for measuring all stages of stator blades; the high-resolution measuring head assembly is driven by a driving mechanism to rotate above the blade measuring assembly so as to quickly complete image shooting of the front edge and the rear edge of the full-stage blade and the blade measuring assembly; and the angle calculation assembly is used for receiving the image of the high-resolution measuring head assembly or carrying out image recognition and calculation to obtain the installation angle of each stage. During measurement, the distance between the front edge of the blade and the measuring head, the scale of the front edge of the whole-stage blade, the scale of the rear edge of the whole-stage blade and the distance between the rear edge of the blade and the measuring head are sequentially measured, and the mounting angle of each stage of stator blade is calculated through the data. By adopting the device and the method provided by the invention, the angle measurement work can be quickly completed, and the assembly efficiency of the stator blade is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of aeroengines, and in particular relates to a device and method for measuring the installation angle of a stator blade of an aeroengine compressor. Background Art

[0002] The stator blades of aircraft engine compressors are mainly used to change the air flow angle inside the components so that the air flow direction can meet the downstream requirements. The ability of the compressor stator blades to change the air flow angle is mainly determined by their installation angle. When the blade installation angle does not meet the requirements, it is easy to cause internal flow field turbulence, thereby reducing the compressor stability margin. Therefore, during the engine manufacturing and assembly process, the blade installation angle needs to be strictly controlled. There are two problems in actual manufacturing: ① For adjustable stator blades with variable installation angles, special tooling is often used to directly contact the leading and trailing edges of the blades to measure the installation angle. The measurement speed is slow, and the angle control accuracy is insufficient due to the manufacturing accuracy and measurement accuracy of the tooling, which makes the direct measurement of the angle accuracy insufficient; ② For stator blades with constant installation angles, most of them are brazing structures, and the blade installation angle is mostly determined by the positioning tooling during the welding process. Because the spacing between these blades is narrow, it is impossible to use a device to directly measure, and the installation angle is not measured after welding. The actual installation angle of the stator blade cannot be grasped, and the actual installation of the stator blade cannot be grasped.

[0003] Specifically, existing blade measuring devices are as follows: Figure 1 As shown in the figure, the device is fixed to the casing using the stator casing mounting side hole, and then the device probe is inserted into the channel between the blades to measure the blade installation angle. The measurement principle is as follows Figure 2 As shown, the device probe is zeroed before entering the inter-blade channel, and a mechanical dial or electronic angular displacement sensor is inside the device to ensure its zeroing. After the device probe is inserted into the inter-blade channel, the rotating device probe contacts the leading edge and trailing edge of the blade at the same time, and the angle value, i.e., the installation angle of the blade, is read from the mechanical dial or electronic angular displacement sensor. The device probe is then retracted and then inserted into other blade channels for measurement until all measurements are completed. Obviously, the measurement process of the original blade measuring device is complicated, requiring multiple insertions and retractions, and it is impossible to insert and measure inter-blade channels with large curvatures. Summary of the invention

[0004] In view of the deficiencies in the prior art, the present invention provides a device and method for measuring the installation angle of stator blades of an aircraft engine compressor, which uses an indirect measurement method to accurately measure the installation angle of the blades and can quickly complete the measurement of the entire stage of blades.

[0005] An aircraft engine compressor stator blade installation angle measuring device includes a blade measuring assembly arranged at the leading and trailing edges of the blade, and is used to measure stator blades of various levels;

[0006] A high-resolution probe assembly is driven by a driving mechanism to rotate above the blade measuring assembly to quickly complete the image capture of the leading and trailing edges of all blades and the blade measuring assembly;

[0007] The angle calculation component receives the image of the high-resolution probe component or performs image recognition and calculation to obtain the installation angles at various levels.

[0008] The device also includes a device base, on which the blade measurement assembly is mounted.

[0009] The high-resolution probe assembly and the angle calculation assembly are mounted on a support plate on the device, and the support plate on the device is connected to a support column arranged at the center of the device base through a bearing.

[0010] The high-resolution probe assembly includes a high-resolution camera for capturing blade images and transmitting the capturing results to the angle calculation assembly.

[0011] The angle calculation component includes an image recognition module, which is used to perform image recognition on the pictures taken and transmitted by the high-resolution probe component, identify the leading edge scale and trailing edge scale measured by the dial, and transmit the identified scale value to the angle calculation module; the angle calculation module receives the information from the image recognition module, obtains the installation angle of the stator blade through a formula calculation, and outputs it.

[0012] The driving mechanism includes a driving motor, which is fixed on the supporting column. The output end of the driving motor is connected to the upper support plate of the device through a connecting rod, and the driving motor drives the rotation of the upper support plate of the device.

[0013] The blade measuring assembly comprises two scale plates, which are respectively mounted on the front and rear mounting surfaces of the casing assembly to be tested containing the stator blades; a scale plate clamping groove is provided on the base of the device for mounting one of the scale plates.

[0014] The two scale plates are respectively a first scale plate and a second scale plate, which are arranged up and down and aligned and fixed with each other; the two scale plates are both transparent scale plates, and arc length scales are marked on the radius circle.

[0015] A method for measuring the installation angle of a stator blade of an aircraft engine compressor, using the above-mentioned device for measuring the installation angle of a stator blade of an aircraft engine compressor, is specifically as follows:

[0016] S1: Assemble the casing assembly to be tested including the stator blades and install a dial;

[0017] S2: Measure the distance between the leading edge of the blade and the probe:

[0018] The drive motor starts, and the high-resolution probe assembly rotates to take pictures of the leading edge of the entire blade stage, and the distance between the leading edge of the entire blade stage and the probe is obtained through the angle calculation assembly;

[0019] S3: Measure the leading edge scale of the entire blade:

[0020] Another scale plate is installed on the front mounting surface of the casing assembly to be inspected containing the stator blades; the drive motor is started, the high-resolution probe assembly rotates to complete the image capture of each level of stator blades and the first scale plate, and the measurement of the leading edge scale of the entire level of blades is obtained through the angle calculation assembly;

[0021] S4: Measure the scale of the trailing edge of the entire blade:

[0022] Turn the casing assembly to be inspected containing the stator blades, and place the dial installed in step S1 downward into the base of the device; start the drive motor, rotate the high-resolution probe to complete the image of each level of stator blades and the second dial, and obtain the scale measurement of the trailing edge of the entire level of blades through the angle calculation component;

[0023] S5: Measure the distance between the trailing edge of the blade and the probe:

[0024] The dial installed in step S3 is removed from the rear mounting surface of the casing assembly to be inspected containing the stator blades, the drive motor is started, the high-resolution probe assembly rotates to complete the image capture of each level of stator blades, and the distance between the trailing edge of the entire level of blades and the probe is measured by the angle calculation assembly;

[0025] S6: Calculate the installation angle of each level of stator blades:

[0026] The angle calculation module calculates the installation angles of the stator blades at each level through the data obtained in steps S3 to S5.

[0027] The step S6 uses the arc tangent function to calculate the installation angle θ of each level of stator blades:

[0028]

[0029] Among them, L1i is the distance between the leading edge of each level of blade and the probe;

[0030] S1i is the leading edge scale of each level of blades;

[0031] S2i is the scale of the trailing edge of each level of blades;

[0032] L2i is the distance between the trailing edge of each level of blade and the measuring head;

[0033] i=1, 2, 3, ..., n; n is the number of stator blades in the casing assembly to be tested containing stator blades;

[0034] After the installation angle θi of each level of stator blades is obtained by the above method, a fitting function relationship between θi and the blade installation angle measured by the method of the prior art is established, and θi is corrected by the fitting function relationship.

[0035] The beneficial effects of the present invention are as follows: the present invention adopts indirect measurement of the arc length covered by the leading and trailing edges of the blade to calculate the installation angle of the stator blade, thereby solving the problem of insufficient accuracy of direct angle measurement; the present invention adopts a rotatable high-resolution probe assembly for continuous shooting, and an angle calculation assembly performs real-time image recognition and angle calculation, thereby quickly completing angle measurement, thereby solving the problem of slow measurement speed.

[0036] Since the arc length is easier to measure accurately than the direct angle measurement, the device improves the accuracy of blade installation angle measurement. The indirect measurement method can measure the stator blades with smaller spacing, solving the problem that the existing device cannot measure.

[0037] The device can quickly complete the angle measurement work and improve the assembly efficiency of the stator blades. By accurately measuring and controlling the installation angle of the stator blades, the problems of insufficient performance and insufficient stability margin of the compressor components can be effectively solved, and the engine reliability can be improved. This blade installation angle measurement device can be widely used in the assembly process of stator blades of various aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 It is a schematic diagram of the existing measuring device;

[0039] Figure 2 It is the measurement principle diagram of the existing measurement device;

[0040] Figure 1-Figure 2 middle:

[0041] 01- measuring device, 02- blade to be measured;

[0042] A-blade leading edge, B-blade trailing edge, C-device probe, S-blade to be measured, θ-blade installation angle;

[0043] Figure 3 A schematic diagram of the installation angle measuring device for the stator blades of an aircraft engine compressor provided by the present invention;

[0044] Figure 4 It is the measurement principle diagram of the present invention;

[0045] Figure 3-Figure 4 middle:

[0046] 1-device upper support plate, 2-driving motor, 3-angle calculation component, 4-high-resolution probe component, 5-first scale plate, 6-casing component to be tested containing stator blades, 7-second scale plate, 8-device base, 9-stator blades, 10-measuring component. DETAILED DESCRIPTION

[0047] In order to better explain the present invention and facilitate understanding, the technical solutions and effects of the present invention are described in detail below through specific implementation modes in conjunction with the accompanying drawings.

[0048] like Figure 3 As shown, a device for measuring the installation angle of a stator blade of an aircraft engine compressor includes a device base 8 and a device upper support plate 1, wherein the device upper support plate 1 is connected to a support column arranged at the center of the device base 8 through a bearing. A blade measurement assembly is arranged on the device base 8, which is used to install and measure stator blades 9 of various stages. An angle calculation assembly 3 and a high-resolution probe assembly 4 electrically connected thereto are installed on the device upper support plate 1, which is driven by a driving mechanism fixed on the device upper support plate 1 to quickly complete the image capture of the leading and trailing edges of all stages of stator blades 9 and two scale plates.

[0049] The high-resolution probe component 4 includes a high-resolution camera and a laser rangefinder, which are used to capture and measure the image of the stator blades 9 and transmit the capture and measurement results to the angle calculation component 3 .

[0050] The angle calculation component 3 includes an image recognition module and an angle calculation module. The image recognition module is used to perform image recognition on the pictures taken and transmitted by the high-resolution probe component 4, identify the leading edge scale and the trailing edge scale measured by the dial, and transmit the identified scale value to the angle calculation module. The angle calculation module receives the information from the image recognition module, obtains the installation angle of the stator blade 9 through a formula calculation, and outputs the installation angle of the stator blades 9 of the entire stage.

[0051] The driving mechanism includes a driving motor 2, which is fixed on the supporting column. The output end of the driving motor 2 is connected to the upper support plate 1 of the device through a connecting rod, and the driving motor 2 drives the rotation of the upper support plate 1 of the device.

[0052] The blade measuring assembly includes two scale plates, which are respectively mounted on the front and rear mounting surfaces of the casing assembly 6 to be tested containing the stator blades, and are used to measure the scales of the leading edge and the trailing edge of the blade. A scale plate clamping groove is provided on the base 8 of the device, which is used to install one of the scale plates, and the scale plate is installed in the scale plate clamping groove.

[0053] The two scale plates are respectively the first scale plate 5 and the second scale plate 7, which are arranged up and down, aligned and fixed with each other, and respectively mounted on the front and rear mounting surfaces and the rear mounting surface of the casing assembly to be tested 6 containing the stator blades. Both of the scale plates are transparent scale plates, and are marked with scales on the radius circle, so that the arc length information can be directly read.

[0054] Combined with Figure 4 The measurement principle shown in the figure is a method for measuring the installation angle of the stator blades of an aircraft engine compressor using the above-mentioned aircraft engine compressor stator blade installation angle measurement device, which is specifically as follows:

[0055] S1: Assemble the casing assembly 6 to be tested containing the stator blades and install the dial:

[0056] After the assembly of the casing assembly 6 to be inspected including the stator blades is completed, the second scale plate 7 is installed on the rear mounting surface of the casing assembly 6 to be inspected including the stator blades, and the second scale plate 7 is placed in the device base 8.

[0057] S2: Measure the distance between the leading edge of the blade and the probe:

[0058] Start the measurement program, start the drive motor 2, drive the high-resolution probe assembly 4 to rotate through the upper support plate 1 of the device, and complete the photography of the leading edge of the entire blade. During the rotation of the high-resolution probe assembly 4, the high-resolution camera captures the images of the stator blades at each level, and the laser rangefinder measures the distance between the leading edge of the blade and the probe and numbers it as i (i=1, 2, 3, ..., n; wherein n is the number of stator blades 9 in the casing assembly 6 to be detected containing stator blades), and transmits the result to the angle calculation assembly 3, wherein the image recognition module is used to perform image recognition on the pictures photographed and transmitted by the high-resolution probe assembly 4, and the laser rangefinder measures and obtains the distance L1i (i=1, 2, 3, ..., n; wherein n is the number of stator blades 9 in the casing assembly 6 to be detected containing stator blades) between the leading edge of each blade and the probe, and transmits the result to the angle calculation module, thereby completing the measurement of the distance between the leading edge of the entire blade and the probe.

[0059] S3: Measure the leading edge scale of the entire blade:

[0060] The first scale plate 5 is installed on the front mounting surface of the casing assembly 6 to be inspected containing the stator blades, and then the measurement program is started, the driving motor 2 is started, and the high-resolution probe assembly 4 is driven to rotate through the upper support plate 1 of the device to complete the photographing of the leading edge of the entire blade stage and the first scale plate 5. During the rotation process, the high-resolution probe assembly 4 takes images of the stator blades of each stage and the first scale plate 5 and numbers them as i (i=1, 2, 3, ..., n; wherein n is the number of the stator blades 9 in the casing assembly 6 to be inspected containing the stator blades), and transmits the results to the angle calculation assembly 3, wherein the image recognition module is used to perform image recognition on the pictures taken and transmitted by the high-resolution probe assembly 4, recognize the leading edge scales S1i (i=1, 2, 3, ..., n; wherein n is the number of the stator blades 9 in the casing assembly 6 to be inspected containing the stator blades) of each stage, and transmit the results to the angle calculation module, thereby completing the measurement of the leading edge scales of the entire blade stage.

[0061] S4: Measure the scale of the trailing edge of the entire blade:

[0062] Turn the casing assembly 6 to be inspected containing the stator blades, and place the first scale plate 5 downward into the device base 8. Start the measurement program, start the drive motor 2, and drive the high-resolution probe assembly 4 to rotate through the upper support plate 1 of the device to complete the photography of the trailing edge of the entire blade. During the rotation of the high-resolution probe assembly 4, the high-resolution camera takes images of the stator blades at each level, and the laser rangefinder measures the distance between the leading edge of the blade and the probe and numbers it as i (i=1, 2, 3, ..., n; wherein n is the number of stator blades 9 in the casing assembly 6 to be inspected containing the stator blades), and transmits the result to the angle calculation component 3, wherein the image recognition module is used to perform image recognition on the pictures taken and transmitted by the high-resolution probe assembly 4, identify the trailing edge scales S2i (i=1, 2, 3, ..., n; wherein n is the number of stator blades 9 in the casing assembly 6 to be inspected containing the stator blades) at each level, and transmit the result to the angle calculation module, and complete the measurement of the trailing edge scales of the entire blade.

[0063] S5: Measure the distance between the trailing edge of the blade and the probe:

[0064] Remove the second scale plate 7 from the rear mounting surface of the casing assembly 6 to be inspected containing the stator blades. Start the measurement program, start the drive motor 2, and drive the high-resolution probe assembly 4 to rotate through the upper support plate 1 of the device to complete the photography of the trailing edge of the entire blade. During the rotation of the high-resolution probe assembly 4, the high-resolution camera captures the images of the stator blades at each level, and the laser rangefinder measures the distance between the leading edge of the blade and the probe and numbers it as i (i=1, 2, 3, ..., n; wherein n is the number of stator blades 9 in the casing assembly 6 to be inspected containing the stator blades), and transmits the result to the angle calculation assembly 3, wherein the image recognition module is used to perform image recognition on the pictures photographed and transmitted by the high-resolution probe assembly 4, and the laser rangefinder measures the distance L2i (i=1, 2, 3, ..., n; wherein n is the number of stator blades 9 in the casing assembly 6 to be inspected containing the stator blades) at each level and transmits the result to the angle calculation module, thereby completing the measurement of the distance between the trailing edge of the entire blade and the probe.

[0065] S6: Calculate the installation angle of each level of stator blades:

[0066] The angle calculation module calculates the installation angle θi of each level of stator blades through the data transmitted by steps S3 to S5 using formula (1), and makes corrections based on the test:

[0067]

[0068] Wherein, i=1, 2, 3, . . . , n; n is the number of stator blades 9 in the casing assembly 6 to be inspected that contains stator blades.

[0069] After obtaining the installation angle θi of each level of stator blades using the above method, a fitting function relationship between θi and the blade installation angle measured by the method of the prior art is established, and θi is corrected through the fitting function relationship, thereby adjusting the measurement precision and accuracy of the data obtained by this method, so as to expand it to the assembly process of stator blades of other types of aircraft engines.

Claims

1. An aircraft engine compressor stator blade installation angle measuring device, characterized in that: It includes a blade measuring assembly arranged at the leading and trailing edges of the blade, and is used to measure the stator blades at various levels; A high-resolution probe assembly is driven by a driving mechanism to rotate above the blade measuring assembly to quickly complete the image capture of the leading and trailing edges of all blades and the blade measuring assembly; The angle calculation component receives the image of the high-resolution probe component or performs image recognition and calculation to obtain the installation angles at various levels.

2. The device for measuring the installation angle of a stator blade of an aircraft engine compressor according to claim 1, characterized in that: The device also includes a device base, on which the blade measurement assembly is mounted.

3. The device for measuring the installation angle of a stator blade of an aircraft engine compressor according to claim 2, characterized in that: The high-resolution probe assembly and the angle calculation assembly are mounted on a support plate on the device, and the support plate on the device is connected to a support column arranged at the center of the device base through a bearing.

4. The device for measuring the installation angle of a stator blade of an aircraft engine compressor according to claim 1, characterized in that: The high-resolution probe assembly includes a high-resolution camera for capturing blade images and transmitting the capturing results to the angle calculation assembly.

5. The device for measuring the installation angle of a stator blade of an aircraft engine compressor according to claim 1, characterized in that: The angle calculation component includes an image recognition module, which is used to perform image recognition on the pictures taken and transmitted by the high-resolution probe component, identify the leading edge scale and trailing edge scale measured by the dial, and transmit the identified scale value to the angle calculation module; the angle calculation module receives the information from the image recognition module, obtains the installation angle of the stator blade through a formula calculation, and outputs it.

6. The device for measuring the installation angle of the stator blades of an aircraft engine compressor according to claim 3, characterized in that: The driving mechanism includes a driving motor, which is fixed on the supporting column. The output end of the driving motor is connected to the upper support plate of the device through a connecting rod, and the driving motor drives the rotation of the upper support plate of the device.

7. The device for measuring the installation angle of a stator blade of an aircraft engine compressor according to claim 1, characterized in that: The blade measuring assembly comprises two scale plates, which are respectively mounted on the front and rear mounting surfaces of the casing assembly to be tested containing the stator blades; a scale plate clamping groove is provided on the base of the device for mounting one of the scale plates.

8. The device for measuring the installation angle of the stator blades of an aircraft engine compressor according to claim 7, characterized in that: The two scale plates are respectively a first scale plate and a second scale plate, which are arranged up and down and aligned and fixed with each other; the two scale plates are both transparent scale plates, and arc length scales are marked on the radius circle.

9. A method for measuring the installation angle of a stator blade of an aircraft engine compressor, using the device for measuring the installation angle of a stator blade of an aircraft engine compressor according to any one of claims 1 to 8, characterized in that: The details are as follows: S1: Assemble the casing assembly to be tested including the stator blades and install a dial; S2: Measure the distance between the leading edge of the blade and the probe: The drive motor starts, and the high-resolution probe assembly rotates to take pictures of the leading edge of the entire blade stage, and the distance between the leading edge of the entire blade stage and the probe is obtained through the angle calculation assembly; S3: Measure the leading edge scale of the entire blade: Another scale plate is installed on the front mounting surface of the casing assembly to be inspected containing the stator blades; the drive motor is started, the high-resolution probe assembly rotates to complete the image capture of each level of stator blades and the first scale plate, and the measurement of the leading edge scale of the entire level of blades is obtained through the angle calculation assembly; S4: Measure the scale of the trailing edge of the entire blade: Turn the casing assembly to be inspected containing the stator blades, and place the dial installed in step S1 downward into the base of the device; start the drive motor, rotate the high-resolution probe to complete the image of each level of stator blades and the second dial, and obtain the scale measurement of the trailing edge of the entire level of blades through the angle calculation component; S5: Measure the distance between the trailing edge of the blade and the probe: The dial installed in step S3 is removed from the rear mounting surface of the casing assembly to be inspected containing the stator blades, the drive motor is started, the high-resolution probe assembly rotates to complete the image capture of each level of stator blades, and the distance between the trailing edge of the entire level of blades and the probe is measured by the angle calculation assembly; S6: Calculate the installation angle of each level of stator blades: The angle calculation module calculates the installation angles of the stator blades at each level through the data obtained in steps S3 to S5.

10. The method for measuring the installation angle of the stator blades of an aircraft engine compressor according to claim 9, characterized in that: The step S6 uses the arc tangent function to calculate the installation angle θ of each level of stator blades: Among them, L1i is the distance between the leading edge of each level of blade and the probe; S1i is the leading edge scale of each level of blades; S2i is the scale of the trailing edge of each level of blades; L2i is the distance between the trailing edge of each level of blade and the measuring head; i=1, 2, 3, ..., n; n is the number of stator blades in the casing assembly to be tested containing stator blades; After the installation angle θi of each level of stator blades is obtained by the above method, a fitting function relationship between θi and the blade installation angle measured by the method of the prior art is established, and θi is corrected by the fitting function relationship.

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