Composite engine blade trailing edge delamination damage test device and test method

Abstract

The present invention belongs to the technical field of foreign object impact on composite material blades of aircraft engines, and specifically discloses a composite material engine blade trailing edge delamination damage test device and test method, the device includes a foreign object impact launch subsystem, a blade typical part test bench and a high-speed camera monitoring subsystem; the foreign object impact launch subsystem is used to launch birdshot; the blade typical part test bench is used to fix the blade typical part so that it is impacted by the birdshot; the high-speed camera monitoring subsystem is used to monitor the birdshot impact process and record the birdshot impact test data. The present invention realizes the control and adjustment of the bird cutting angle, bird impact height and bird cutting amount by designing an adjustable tooling and a detachable typical part fixture of the blade typical part test bench, which solves the problem that the existing technology cannot simultaneously realize the adjustment of the impact height, impact angle and bird cutting amount, and the test research plan is limited by the equipment, and it is difficult to accurately control the impact working condition.

Description

Technical Field

[0001] The invention belongs to the technical field of foreign object impact on composite material blades of aircraft engines, and in particular relates to a trailing edge delamination damage test device and a test method for a typical composite material engine blade. Background Art

[0002] During the flight, the blades of aircraft engines are in high-speed motion. When foreign objects sucked into the engine collide with them, the blades are easily damaged and broken, which can lead to major accidents such as "aircraft destruction and death". This type of damage can be roughly divided into soft impact damage and hard impact damage according to the source of damage: when the foreign object is a low-hardness material such as a bird or ice, it is usually called a "soft" impact.

[0003] Composite fan blades have been widely used in new generation aircraft engines due to their high specific strength and specific modulus characteristics compared to metal blades. Composite fan blades are prone to delamination damage at the trailing edge of the blade after being impacted by soft objects such as birds. This damage will greatly shorten the life of the blade, increase economic costs, and seriously threaten personnel safety and engine operation reliability. In order to improve the bird impact resistance and delamination damage resistance of composite blades, it is necessary to optimize the materials used for composite blades and optimize the layup method and structure. To achieve the above purpose, it is necessary to first design a soft bird bullet high-speed impact test method for typical blade parts to achieve a single-sided delamination damage condition at the trailing edge, and then complete the comparative verification of the impact resistance of different selected materials.

[0004] One solution in the prior art solves the problem that the bird-cutting load history cannot be accurately measured in the existing engine fan blade bird strike research due to the coupling of the dynamic deformation of the bird body and the deformation of the blade by combining an air cannon and a wedge-shaped head Hopkinson rod. However, this method cannot further realize the clamping and impact of typical blade parts after completing the bird-cutting. Another solution uses an impulse conversion device as an impulse conversion medium to transfer the impulse of the projectile fired by the air cannon to the test blade, and completes the bird-cutting simulation by the blade impacting the test bird body. It is not necessary to directly shoot the test blade out of the barrel, which improves the convenience and accuracy of the anti-bird strike blade test method. However, in this method, the blade is restricted in the slide rail and cannot complete bird-cutting at a specific angle or posture. In the third solution, the aircraft engine blade bird strike test simulation fixture can change the angle of the blade facing the bird by adjusting the circumferential installation angle of the mounting seat and the lower bracket, without the need to re-disassemble the test piece blade, and can achieve quick and simple operation. However, this fixture cannot adjust the impact height when the bullet path is determined, and cannot be used to complete impacts at different blade height positions.

[0005] In general, the above-mentioned technical solutions and devices cannot simultaneously meet the requirements of clamping and adjusting the test pieces in the bird cutting test of blades or typical blade parts, and are limited to high-precision monitoring and control of parameters such as impact velocity, bird mounting height and bird cutting amount. The above-mentioned parameters have a direct impact on the prefabricated position and size of the trailing edge delamination damage. Therefore, there is currently no relevant technical solution for the prefabrication of delamination damage on the trailing edge of a typical blade part caused by soft impact. Summary of the invention

[0006] The purpose of the present invention is to solve the problem that the prior art cannot simultaneously adjust the impact height, impact angle and bird cutting amount, and the test research scheme is limited by the equipment and it is difficult to accurately control the impact conditions. A test device and test method for the trailing edge delamination damage of a typical composite engine blade are proposed.

[0007] The technical scheme of the present invention is as follows: in the first aspect, a composite material engine blade typical part trailing edge delamination damage test device comprises an impact foreign object launch subsystem, a blade typical part test bench and a high-speed camera monitoring subsystem; the blade typical part test bench comprises a tooling, a typical part fixture and an adjustable slide rail on the ground; the tooling is connected to the adjustable slide rail on the ground; the typical part fixture is connected to the tooling;

[0008] The impact foreign object launching subsystem is used to launch birdshot;

[0009] The blade typical part test bench is used to fix the blade typical part so that the blade typical part is impacted by the birdshot;

[0010] The high-speed camera monitoring subsystem is used to monitor the birdshot impact process and record the birdshot impact test data;

[0011] The tooling is used to fix the typical part fixture and position the blade typical part to ensure that the blade typical part remains stable during the impact process;

[0012] The typical component fixture is used to fix the blade typical component and adjust the height and angle of the blade typical component;

[0013] The adjustable slide rail is an embedded lifting slide rail, which is used to fix the tooling horizontally on the ground or to move it horizontally above the ground, thereby adjusting the height and angle of the blade typical part to achieve the adjustment of the impact height and impact angle.

[0014] The beneficial effects of the present invention are:

[0015] The present invention designs tooling and typical component fixtures in a blade typical component test bench with adjustable multiple degrees of freedom, so that the impact height and impact angle can be adjusted simultaneously in the composite engine blade trailing edge delamination damage test, and the bird cutting amount can be adjusted according to the adjustment of the impact height and the impact angle, thereby achieving precise adjustment of key test parameters to meet various working conditions.

[0016] Preferably, the tooling comprises a trapezoidal base and a bottom plate located above the trapezoidal base; an adjustable slide rail connected to the ground below the trapezoidal base; and a long through hole and a positioning hole are provided on the bottom plate;

[0017] The long through hole is used to fix the bottom plate to the trapezoidal base;

[0018] The positioning hole is used to fix the typical part fixture and provide a preset impact angle.

[0019] Preferably, the typical fixture is a single-sided fixture, comprising a front cover plate and a rear bottom plate, and the front cover plate and the rear bottom plate are both in an "L" shape;

[0020] The front cover plate has two rows of threaded holes in the vertical direction, wherein the right row of threaded holes has one threaded hole at the top and one threaded hole at the bottom, which is used to provide the right clamping force of the clamping area; the bottom of the front cover plate has a row of waist holes in the horizontal direction, which is used to fix the front cover plate to the tooling;

[0021] The rear bottom plate has two rows of threaded holes in the vertical direction, and the left row of threaded holes is an embedded slot hole, which is used to connect with the front cover plate and fix the typical blade parts, and provide the left clamping force of the clamping area; the bottom of the rear bottom plate has three rows of threaded holes in the horizontal direction, which are used to connect the tooling fixing position.

[0022] Preferably, the impact foreign object launching subsystem comprises a gun barrel, a compressed gas tank and a projectile outlet;

[0023] The gun barrel is arranged outside the typical blade test bench, one end of the gun barrel is a loading port, the loading port is connected to the compressed gas tank, the other end of the gun barrel is a discharge port, and the discharge port is provided with a multi-stage ejection device; a bullet support is provided inside the gun barrel; and an inflation valve is provided on the compressed gas tank.

[0024] Preferably, the high-speed camera monitoring subsystem comprises 6 high-speed cameras, a plurality of light sources and a computer data acquisition unit arranged on the periphery of the blade typical component test bench; the computer data acquisition unit is electrically connected to the plurality of high-speed cameras and the plurality of light sources respectively;

[0025] The six high-speed cameras are:

[0026] The front camera is used to capture the birdshot impact process and detect whether there is any abnormality in the birdshot exiting the chamber;

[0027] Side camera, used to capture the flight path of birdshot, with a narrow and long field of view, the camera height is consistent with the height of the birdshot, and the impact velocity measurement is completed according to the pixel analysis method;

[0028] A camera is hung from the top to capture the process of the bird being cut by a typical piece jig;

[0029] The two cameras directly behind are used to calculate the out-of-plane deformation field of the typical blade during the impact process. Their placement is symmetrical with respect to the center line of the typical blade.

[0030] The side rear camera is used to capture the height position of the bird hitting the typical part fixture, and its placement angle is perpendicular to the typical part fixture surface.

[0031] The beneficial effects of the above preferred solution are:

[0032] 1. Through a row of waist holes at the bottom of the front cover, it is connected and fixed with the tooling on the one hand, and the position can be adjusted on the other hand, providing installation margin, which can be used to clamp typical blade parts of different thicknesses.

[0033] 2. The built-in slots on the rear bottom plate can limit the insertion depth of typical blade parts, thereby achieving precise adjustment of key test parameters.

[0034] 3. Use multiple high-speed cameras for monitoring, which can accurately measure the impact velocity of foreign objects, bird strike height, bird cut amount and out-of-plane deformation field. The layout of multi-point light sources provides illumination for the front, back and top of typical blade parts, which facilitates clear monitoring of parameters for subsequent data analysis.

[0035] In a second aspect, a method for testing the trailing edge delamination damage of a typical composite engine blade comprises the following steps:

[0036] S1. Build a test device for the trailing edge delamination damage of a typical composite engine blade, and conduct pre-test preparation and debugging;

[0037] S2. Calibrate the measuring device, wherein the measuring device is a plurality of high-speed cameras;

[0038] S3. Conduct a typical blade delamination damage test using the debugged composite engine blade typical trailing edge delamination damage test device, and record the test data using the calibrated measurement device;

[0039] S4. Process the test data recorded during the test to complete the trailing edge delamination damage test of a typical composite blade component with controllable damage position and damage area.

[0040] Preferably, the step S1 specifically includes the following sub-steps:

[0041] Connect the loading port to the compressed gas tank and seal it, and install a multi-stage ejection device at the ejection port;

[0042] Mount the trapezoidal base to the floor adjustable slide rails, and mount the typical piece clamp to the base plate and secure it to the trapezoidal base;

[0043] Use laser positioning to align the horizontal and vertical center axes of the muzzle, move the trapezoidal base along the horizontal slide rail, align the center line of the trapezoidal base with the horizontal center axis of the muzzle, and complete the horizontal exit position calibration; at the same time, complete the bullet exit height calibration based on the vertical center axis on the typical part fixture.

[0044] Preferably, the calibration of the measuring device in step S2 includes field of view adjustment and image calibration.

[0045] Preferably, the step S3 specifically includes the following sub-steps:

[0046] Adjust the base position and the clamping height of the blade typical parts according to the preset bird cutting amount and bird striking height;

[0047] Turn on the light source, and set the high-speed camera and computer data acquisition unit to the trigger-ready state;

[0048] After installing the protection and energy absorption module on the high-speed camera monitoring subsystem and marking the characteristic points of the birdshot, the birdshot is placed on the sabot and loaded into the gun barrel;

[0049] Open the inflation valve, and when the pressure gauge indicates the specified air pressure, close the inflation valve;

[0050] Start the impact foreign object launch subsystem and trigger the high-speed camera and computer data acquisition unit to start monitoring the birdshot impact process;

[0051] After the impact, save the first two frames of image data recorded by the high-speed camera on the typical blade parts of the bird bomb impact, remove the protection and energy absorption modules in turn, clean the multi-stage ejection device, and take out the bullet support and the typical blade parts;

[0052] Record the delamination damage of typical blade parts, analyze the impact process of typical blade parts, record the delamination damage data of typical blade parts, take pictures of the working conditions, and shut down the test equipment.

[0053] Preferably, the test data recorded during the test is processed in step S4, including calculation of birdshot impact velocity, bird strike height and bird cut amount;

[0054] The birdshot impact velocity calculation comprises the following steps:

[0055] The high-speed camera is calibrated in pixels, specifically: a scale is placed in the field of view and photographed to obtain a photographed image;

[0056] According to the pictures taken, the actual length Corresponding pixels and , the actual distance corresponding to each pixel difference can be obtained :

[0057] ;

[0058] According to the displacement coordinate information of the marking points in the experiment at two different time frames, they are and , then the birdshot impact velocity The calculation formula is:

[0059] ;

[0060] in, Represents the difference between two time frames, Indicates the camera sampling frame rate;

[0061] The bird strike height calculation is specifically as follows: observe the leading edge line of the bird body that first contacts the typical component fixture from the speed measuring camera of the high-speed camera; observe the intersection of the leading edge line of the bird body and the scale line on the typical component fixture in the side and rear camera field of view of the high-speed camera, and add the distance from the upper edge of the blade typical component to the scale line to obtain the distance from the bird bullet impact point to the upper edge of the simulation component, which is the bird strike height;

[0062] The bird cut amount calculation is specifically as follows: after the birdshot is accelerated and separated from the barrel, it will hit the column surface of the vertical typical part fixture, be cut by the edge line, a part of it will fly obliquely along the original speed direction and finally hit the blade typical part, and the other part will fly sideways in a direction perpendicular to the speed; according to the image of the top camera of the high-speed camera, the percentage of the cut birdshot to the original birdshot is calculated to obtain the bird cut amount. BRIEF DESCRIPTION OF THE DRAWINGS

[0063] Figure 1 Shown is a schematic structural diagram of a typical composite material engine blade trailing edge delamination damage test device provided in Example 1 of the present invention.

[0064] Figure 2 Shown is a schematic diagram of the tooling structure provided in Example 1 of the present invention.

[0065] Figure 3 Shown is a schematic diagram of a typical fixture structure provided in Example 1 of the present invention.

[0066] Figure 4 Shown is a top view of a typical fixture structure provided in Example 1 of the present invention.

[0067] Figure 5Shown is a schematic diagram of the front cover plate and rear base plate of a typical fixture provided in Example 1 of the present invention.

[0068] Figure 6 Shown is a flow chart of the composite material engine blade trailing edge delamination damage test method provided in Example 2 of the present invention.

[0069] Figure 7 The figure is a schematic diagram of the birdshot impact velocity calculation principle provided in Example 2 of the present invention.

[0070] Figure 8 The figure is a schematic diagram of the bird strike height calculation principle provided in Example 2 of the present invention.

[0071] Fig. 9 The figure shows a schematic diagram of the bird cutting amount calculation principle provided in Example 2 of the present invention.

[0072] Figure numerals: 1. tooling; 2. adjustable slide rail; 3. typical parts fixture; 4. inflation valve; 5. compressed gas tank; 6. loading port; 7. gun barrel; 8. bullet support; 9. multi-stage bullet removal device; 10. light source; 11. high-speed camera; 12. base plate; 13. trapezoidal base; 14. front cover plate; 15. rear base plate. DETAILED DESCRIPTION

[0073] Now, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be understood that the embodiments shown and described in the accompanying drawings are only exemplary and are intended to explain the principles and spirit of the present invention, rather than to limit the scope of the present invention.

[0074] Before describing the specific embodiments of the present invention, in order to make the scheme of the present invention more clear and complete, the definitions of key terms appearing in the present invention are first explained:

[0075] Soft impact: When an aircraft engine is in flight, the composite fan blades are in high-speed operation, which can easily inhale foreign objects and collide with them, thus damaging the blades. When the foreign objects are made of materials with lower hardness, such as birds, it is usually called a "soft" impact.

[0076] Air cannon: An experimental cannon that uses compressed gas as the launching medium to accelerate the test projectile in the barrel and make the projectile obtain the required high speed at the muzzle.

[0077] Soft birdshot: refers to a projectile made of gelatin and other materials that simulates the body of a real bird.

[0078] Trailing edge position: refers to the free end of the blade away from the clamping position.

[0079] Typical blade parts: refers to the equivalent flat plate parts that simulate engine blades.

[0080] Bird cutting and bird cutting amount: The leading edge of the engine blade cuts the bird body sucked in by the engine inlet at a certain angle. After being cut, the bird body will be separated into two parts and continue to hit the surface of the typical part of the blade and other parts, which is called "bird cutting". The percentage of the part of the bird body that hits the surface of the typical part after being cut is called "bird cutting amount".

[0081] Bird strike height: refers to the vertical distance between the position where the bird body strikes the tooling when being cut and the upper edge of the typical blade part.

[0082] Embodiment 1:

[0083] like Figure 1 As shown, a composite engine blade typical part trailing edge delamination damage test device includes an impact foreign object launching subsystem, i.e., an air cannon, a blade typical part test bench, and a high-speed camera monitoring subsystem;

[0084] The impact foreign object launching subsystem is used to launch birdshot;

[0085] The blade typical part test bench is used to fix the blade typical part so that the blade typical part is impacted by the birdshot;

[0086] The high-speed camera monitoring subsystem is used to monitor the birdshot impact process and record the birdshot impact test data;

[0087] The tooling 1 is used to fix the typical component fixture 3 and position the blade typical component to ensure that the blade typical component remains stable during the impact process;

[0088] The typical component fixture 3 is used to fix the blade typical component and adjust the height and angle of the blade typical component;

[0089] The adjustable slide rail 2 is an embedded lifting slide rail, which is used to fix the tooling 1 horizontally on the ground or to move it horizontally above the ground, thereby adjusting the height and angle of the blade typical part to achieve the adjustment of the impact height and impact angle.

[0090] In this embodiment, the blade typical part test bench includes a tooling 1, a typical part fixture 3 and an adjustable slide rail 2 on the ground; the tooling 1 is connected to the adjustable slide rail 2 on the ground; the typical part fixture 3 is connected to the tooling 1; the adjustable slide rail 2 is an embedded lifting slide rail.

[0091] In this embodiment, if Figure 2 As shown, the tooling 1 includes a trapezoidal base 13 and a bottom plate 12 located above the trapezoidal base 13; the trapezoidal base 13 is formed by welding in one piece, and an adjustable slide rail 2 connected to the ground below the trapezoidal base 13 can be fixed horizontally on the ground or moved horizontally after being raised above the ground; the bottom plate 12 is provided with a long through hole and a positioning hole;

[0092] The long through hole is used to fix the bottom plate 12 to the trapezoidal base 13;

[0093] The positioning hole is used to fix the typical component fixture 3 and provide a preset impact angle.

[0094] In this embodiment, if Figure 3 , Figure 4 and Figure 5 As shown, the typical fixture 3 is a single-sided clamp, comprising a front cover plate 14 and a rear bottom plate 15, and the front cover plate 14 and the rear bottom plate 15 are both in an "L" shape;

[0095] The front cover plate 14 has two rows of threaded holes in the vertical direction, wherein the right row of threaded holes has one threaded hole at the top and one threaded hole at the bottom, which are used to provide the right clamping force of the clamping area; the bottom of the front cover plate 14 has a row of waist holes in the horizontal direction, which are connected and fixed to the tooling 1 on the one hand, and can be adjusted on the other hand, providing installation margin, and can be used to clamp typical blades of different thicknesses;

[0096] The rear bottom plate 15 has two rows of threaded holes in the vertical direction, and the left row of threaded holes is an embedded slot hole, which is used to connect with the front cover plate 14 and fix the typical blade parts, and provide the left clamping force of the clamping area. At the same time, the embedded slot hole design limits the insertion depth of the typical blade parts; the bottom of the rear bottom plate 15 has three rows of threaded holes in the horizontal direction, which are used to connect the tooling 1 to a fixed position.

[0097] In this embodiment, the impact foreign object launching subsystem includes a gun barrel 7, a compressed gas tank 5 and a bullet outlet;

[0098] The gun barrel 7 is arranged outside the blade typical part test bench, one end of the gun barrel 7 is a loading port 6 for loading birdshot, the birdshot is a soft birdshot, the loading port 6 is connected to the compressed gas tank 5, and is used for inflating and releasing high-pressure gas; the other end of the gun barrel 7 is a discharge port, which is the discharge position of the soft birdshot, and the discharge port is provided with a multi-stage ejection device 9, which is used to separate the birdshot and the sabot 8 that are about to fly out of the muzzle, so as to prevent the sabot 8 from impacting the blade together with the projectile as an unexpected non-impact object, making it difficult to decouple and quantitatively analyze the results; a sabot 8 is provided inside the gun barrel 7, and the sabot 8 is a special 3D printed sabot for carrying soft birdshot; an inflation valve 4 is provided on the compressed gas tank 5.

[0099] In this embodiment, the high-speed camera monitoring subsystem includes 6 high-speed cameras 11, a plurality of light sources 10 and a computer data acquisition unit arranged on the periphery of the blade typical component test bench; the computer data acquisition unit is electrically connected to the plurality of high-speed cameras 11 and the plurality of light sources 10 respectively;

[0100] The six high-speed cameras 11 are respectively:

[0101] The front camera is used to capture the birdshot impact process and detect whether there is any abnormality in the birdshot exiting the chamber;

[0102] Side camera, used to capture the flight path of birdshot, with a narrow and long field of view, the camera height is consistent with the height of the birdshot, and the impact velocity measurement is completed according to the pixel analysis method;

[0103] A camera is hung on the top to capture the process of the bird body being cut by the typical fixture 3;

[0104] The two cameras directly behind are used to calculate the out-of-plane deformation field of the typical blade during the impact process. Their placement is based on the center line of the typical blade and is as symmetrical as possible. At the same time, the placement and shooting field of view are adjusted to ensure that the displacement field data of the entire typical blade can be obtained.

[0105] The side rear camera is used to capture the height position of the bird hitting the typical fixture 3, and its placement angle is perpendicular to the typical fixture 3 surface. Multiple high-speed cameras 11 are used for monitoring to measure information including foreign object impact speed, bird impact height, bird cut amount and out-of-plane deformation field. The layout of multi-point light sources provides illumination for the front, back and top of the blade typical part, which facilitates clear monitoring of parameters for subsequent data analysis.

[0106] Embodiment 2:

[0107] Based on Example 1, this example proposes a test method for the delamination damage of the trailing edge of a typical composite engine blade. Figure 6 As shown, the method comprises the following steps:

[0108] S1. Build a test device for the trailing edge delamination damage of a typical composite engine blade, and conduct pre-test preparation and debugging;

[0109] S2. Calibrate the high-speed camera monitoring subsystem;

[0110] S3. Conduct a typical blade delamination damage test using the debugged composite engine blade typical trailing edge delamination damage test device, and record the test data using the calibrated high-speed camera monitoring subsystem;

[0111] S4. Process the test data recorded during the test to complete the trailing edge delamination damage test of a typical composite blade component with controllable damage position and damage area.

[0112] In this embodiment, step S1 specifically includes the following sub-steps:

[0113] Connect the loading port 6 to the compressed gas tank 5 and seal them, and install a multi-stage ejection device 9 at the ejection port;

[0114] Install the trapezoidal base 13 to the ground adjustable slide rail 2, and install the typical part fixture 3 to the bottom plate 12 and fix it to the trapezoidal base 13;

[0115] Laser positioning is used to align the horizontal and vertical center axes of the muzzle, and the trapezoidal base 13 is moved along the horizontal slide rail to align the center line of the trapezoidal base 13 with the horizontal center axis of the muzzle, completing the horizontal discharge position calibration, which is convenient for subsequent adjustment of different bird cutting amounts; at the same time, the vertical center axis is aligned with the vertical center axis on the typical part fixture 3 to complete the bullet discharge height calibration, which is used for subsequent adjustment of the bird cutting height; finally, high-speed cameras 11 with multiple camera positions are set up and protected with bulletproof glass.

[0116] In this embodiment, the calibration of the high-speed camera monitoring subsystem described in step S2 includes field of view adjustment and image calibration. The field of view adjustment varies according to the placement of different cameras. The embodiment of the present invention involves a total of 6 high-speed cameras 11: the front camera is used to capture the birdshot impact process and detect whether there is any abnormality in the birdshot exiting the barrel; the side camera is used to capture the flight path of the birdshot, the field of view is narrow and long, the camera height is consistent with the birdshot height, and the impact velocity measurement is completed according to the pixel analysis method; the top hanging camera is used to capture the process of the bird body being cut by the fixture. When placed, try to make the vertical line of the side of the fixture in the top view state larger, so as to facilitate the subsequent calculation of the bird cutting amount according to the image method. The two cameras directly behind are used to calculate the out-of-plane deformation field of the typical blade part during the impact process. The placement position is based on the center line of the typical blade part to keep it as symmetrical as possible. At the same time, the placement position and shooting field of view are adjusted to ensure that the displacement field data of the entire typical blade part can be obtained. The side rear camera is used to capture the height position of the bird body hitting the fixture. The placement angle is as perpendicular to the fixture surface as possible to identify the scale position of the impact height with higher accuracy.

[0117] In this embodiment, step S3 specifically includes the following sub-steps:

[0118] S31. According to the preset bird cutting amount and bird strike height, adjust the base position and the clamping height of the typical blade parts;

[0119] S32. Turn on the light source 10, set the high-speed camera 11 and the computer data acquisition unit to be triggered;

[0120] S33. After installing the protection and energy absorption module on the high-speed camera monitoring subsystem and marking the characteristic points of the birdshot, the birdshot is placed on the butt 8 and loaded into the gun barrel 7;

[0121] S34. Open the inflation valve 4. When the pressure gauge indicates the specified pressure, close the inflation valve 4;

[0122] S35. Start the impact of foreign objects launching subsystem and trigger the high-speed camera 11 and computer data acquisition unit to start monitoring the bird bomb impact process;

[0123] S36. After the impact, save the high-speed camera 11 to record the first two frames of image data of the typical blade member impacted by the bird bomb, remove the protection and energy absorption modules in turn, clean the multi-stage ejection device 9, and remove the cartridge 8 and the typical blade member;

[0124] S37. Record the delamination damage of typical blade parts, analyze the impact process of typical blade parts, record the delamination damage data of typical blade parts, take photos of the working conditions, and shut down the test equipment.

[0125] In this embodiment, the test data recorded during the test is processed in step S4, including calculation of birdshot impact velocity, bird strike height and bird cut amount;

[0126] The birdshot impact velocity calculation comprises the following steps:

[0127] The high-speed camera 11 is calibrated in pixels, specifically: a scale is placed in the field of view and photographed to obtain a photographed image;

[0128] like Figure 7 As shown in the picture, the actual length Corresponding pixels and , the actual distance corresponding to each pixel difference can be obtained :

[0129] ;

[0130] According to the displacement coordinate information of the marking points in the experiment at two different time frames, they are and , then the birdshot impact velocity The calculation formula is:

[0131] ;

[0132] in, Represents the difference between two time frames, Indicates the camera sampling frame rate.

[0133] The bird strike height calculation needs to be combined with the side speed camera and the side rear camera, such as Figure 8 As shown, specifically: observe the leading edge line of the bird body that first contacts the typical fixture 3 from the speed measuring camera, such as Figure 8Then, in the side rear camera field of view, observe the intersection of the extension line of scale No. 4 and the scale line on the typical component fixture 3, and add the distance from the upper edge of the blade typical component to the scale line to obtain the distance from the birdshot impact point to the upper edge of the simulation component, which is the bird strike height.

[0134] The bird cutting amount is calculated as follows: Fig. 9 As shown, specifically: after the birdshot is accelerated and separated from the barrel 7, it will hit the column surface of the vertical typical component fixture 3, be cut by the edge line, a part of it will fly obliquely along the original speed direction and finally hit the blade typical component, and the other part will fly sideways along the direction perpendicular to the speed. According to the image of the top camera, the percentage of the cut birdshot to the original birdshot can be calculated, and the amount of birdshot cut can be obtained.

[0135] Those skilled in the art will appreciate that the embodiments described herein are intended to help readers understand the principles of the present invention, and should be understood that the protection scope of the present invention is not limited to such specific statements and embodiments. Those skilled in the art can make various other specific variations and combinations that do not deviate from the essence of the present invention based on the technical revelations disclosed by the present invention, and these variations and combinations are still within the protection scope of the present invention.

Claims

1. A composite engine blade typical trailing edge delamination damage test device, characterized in that: The invention comprises an impact foreign object launch subsystem, a blade typical component test bench and a high-speed camera monitoring subsystem; the blade typical component test bench comprises a tooling (1), a typical component fixture (3) and an adjustable slide rail (2) on the ground; the tooling (1) is connected to the adjustable slide rail (2) on the ground; and the typical component fixture (3) is connected to the tooling (1); The impact foreign object launching subsystem is used to launch birdshot; The blade typical part test bench is used to fix the blade typical part so that the blade typical part is impacted by the birdshot; The high-speed camera monitoring subsystem is used to monitor the birdshot impact process and record the birdshot impact test data; The tooling (1) is used to fix the typical component fixture (3) and position the blade typical component to ensure that the blade typical component remains stable during the impact process; The typical component fixture (3) is used to fix the blade typical component and adjust the height and angle of the blade typical component; The adjustable slide rail (2) is an embedded lifting slide rail, which is used to fix the tooling (1) horizontally on the ground or above the ground and then translate it horizontally, thereby adjusting the height and angle of the blade typical part, thereby achieving adjustment of the impact height and impact angle; The typical component clamp (3) is a single-sided clamp, comprising a front cover plate (14) and a rear bottom plate (15), wherein the front cover plate (14) and the rear bottom plate (15) are both in an "L" shape; The front cover plate (14) has two rows of threaded holes in the vertical direction, wherein the row of threaded holes on the right side has one threaded hole at the top and one threaded hole at the bottom, for providing a right side clamping force for the clamping area; the bottom of the front cover plate (14) has a row of waist holes in the horizontal direction, for fixing the front cover plate (14) to the tooling (1); The rear bottom plate (15) has two rows of threaded holes in the vertical direction, and the left row of threaded holes is an embedded slot hole, which is used to connect with the front cover plate (14) and fix the blade typical part, and provide the left clamping force of the clamping area; the bottom of the rear bottom plate (15) has three rows of threaded holes in the horizontal direction, which are used to connect the tooling (1) to the fixed position.

2. The composite material engine blade typical part trailing edge delamination damage test device according to claim 1 is characterized in that: The tooling (1) comprises a trapezoidal base (13) and a bottom plate (12) located above the trapezoidal base (13); an adjustable slide rail (2) connected to the ground below the trapezoidal base (13); and a long through hole and a positioning hole are provided on the bottom plate (12); The long through hole is used to fix the bottom plate (12) to the trapezoidal base (13); The positioning hole is used to fix the typical component fixture (3) and provide a preset impact angle.

3. The composite material engine blade typical part trailing edge delamination damage test device according to claim 1 is characterized in that: The impact foreign object launching subsystem comprises a gun barrel (7), a compressed gas tank (5) and a projectile outlet; The gun barrel (7) is arranged outside the blade typical component test bench, one end of the gun barrel (7) is a loading port (6), the loading port (6) is connected to the compressed gas tank (5), the other end of the gun barrel (7) is a bullet discharge port, and the bullet discharge port is provided with a multi-stage bullet release device (9); a bullet support (8) is provided inside the gun barrel (7); and an air charging valve (4) is provided on the compressed gas tank (5).

4. The composite material engine blade typical trailing edge delamination damage test device according to claim 1 is characterized in that: The high-speed camera monitoring subsystem comprises six high-speed cameras (11) arranged on the periphery of a typical blade component test bench, a plurality of light sources (10) and a computer data acquisition unit; the computer data acquisition unit is electrically connected to the plurality of high-speed cameras (11) and the plurality of light sources (10) respectively; The six high-speed cameras (11) are respectively: The front camera is used to capture the birdshot impact process and detect whether there is any abnormality in the birdshot exiting the chamber; Side camera, used to capture the flight path of birdshot, with a narrow and long field of view, the camera height is consistent with the height of the birdshot, and the impact velocity measurement is completed according to the pixel analysis method; A camera is hung from the top to capture the process of the bird body being cut by the typical fixture (3); The two cameras directly behind are used to calculate the out-of-plane deformation field of the typical blade during the impact process. Their placement is symmetrical with respect to the center line of the typical blade. The side rear camera is used to capture the height position of the bird body hitting the typical component fixture (3), and its placement angle is perpendicular to the surface of the typical component fixture (3).

5. A test method based on the trailing edge delamination damage test device for a typical composite material engine blade according to any one of claims 1 to 4, characterized in that: The following steps are involved: S1. Build a test device for the trailing edge delamination damage of a typical composite engine blade, and conduct pre-test preparation and debugging; S2. Calibrate the high-speed camera monitoring subsystem; S3. Conduct a typical blade delamination damage test using the debugged composite engine blade typical trailing edge delamination damage test device, and record the test data using the calibrated high-speed camera monitoring subsystem; S4. Process the test data recorded during the test to complete the trailing edge delamination damage test of a typical composite blade component with controllable damage position and damage area.

6. The test method of the composite engine blade typical trailing edge delamination damage test device according to claim 5 is characterized in that: The step S1 specifically includes the following sub-steps: The loading port (6) is connected to the compressed gas tank (5) and sealed, and a multi-stage ejection device (9) is installed at the ejection port; Mounting the trapezoidal base (13) to the adjustable slide rail (2) on the ground, and mounting the typical part fixture (3) to the base plate (12) and fixing it to the trapezoidal base (13); Laser positioning is used to align the central axis of the muzzle in the horizontal direction and the central axis in the vertical direction, and the trapezoidal base (13) is moved along the horizontal slide rail so that the center line of the trapezoidal base (13) is aligned with the central axis of the muzzle in the horizontal direction, thereby completing the horizontal discharge position calibration; at the same time, the bullet discharge height calibration is completed on the typical component fixture (3) according to the central axis in the vertical direction.

7. The test method of the composite material engine blade typical part trailing edge delamination damage test device according to claim 5 is characterized in that: The calibration of the high-speed camera monitoring subsystem in step S2 includes field of view adjustment and image calibration.

8. The test method of the composite engine blade typical trailing edge delamination damage test device according to claim 5 is characterized in that: The step S3 specifically includes the following sub-steps: Adjust the base position and the clamping height of the blade typical parts according to the preset bird cutting amount and bird striking height; Turning on the light source (10), and setting the high-speed camera (11) and the computer data acquisition unit to a trigger-ready state; Installing a protection and energy absorption module on the high-speed camera monitoring subsystem and marking the characteristic points of the birdshot, the birdshot is placed on a cartridge case (8) and loaded into a gun barrel (7); Open the inflation valve (4), and when the pressure gauge indicates a specified pressure, close the inflation valve (4); Starting the impact foreign object launch subsystem and triggering the high-speed camera (11) and the computer data acquisition unit to start monitoring the birdshot impact process; After the impact is over, the first two frames of image data of the typical blade component recorded by the high-speed camera (11) before the birdshot impact is saved, the protection and energy absorption modules are removed in sequence, the multi-stage ejection device (9) is cleaned, and the cartridge case (8) and the typical blade component are taken out; Record the delamination damage of typical blade parts, analyze the impact process of typical blade parts, record the delamination damage data of typical blade parts, take pictures of the working conditions, and shut down the test equipment.

9. The test method of the composite material engine blade typical part trailing edge delamination damage test device according to claim 5, characterized in that: Step S4 processes the test data recorded during the test, including calculation of birdshot impact velocity, bird strike height and bird cut amount; The birdshot impact velocity calculation comprises the following steps: The high-speed camera (11) is calibrated in pixels, specifically: a scale is placed in the field of view and photographed to obtain a photographed image; According to the pictures taken, the actual length Corresponding pixels and , the actual distance corresponding to each pixel difference can be obtained : ； According to the displacement coordinate information of the marking points in the experiment at two different time frames, they are and , then the birdshot impact velocity The calculation formula is: ； in, Represents the difference between two time frames, Indicates the camera sampling frame rate; The bird strike height is calculated specifically as follows: observing the leading edge line of the bird body that first contacts the typical component fixture (3) from the speed measuring camera of the high-speed camera (11); observing the intersection of the leading edge line of the bird body and the scale line on the typical component fixture (3) in the side and rear camera field of view of the high-speed camera (11); adding the distance from the upper edge of the blade typical component to the scale line, and obtaining the distance from the bird bullet impact point to the upper edge of the simulation component, which is the bird strike height; The calculation of the bird cut amount is specifically as follows: after the birdshot is accelerated and separated from the barrel (7), it will hit the column surface of the vertical typical component fixture (3) and be cut by the edge line. A part of it will fly obliquely along the original speed direction and finally hit the blade typical component, and the other part will fly sideways in a direction perpendicular to the speed; based on the image of the top camera of the high-speed camera (11), the percentage of the cut birdshot to the original birdshot is calculated to obtain the bird cut amount.

Images