Test device and test method for prefabricating impact damage of engine blades and blisks

Abstract

The invention discloses a test device and a test method for prefabricating impact damage of engine blades and disks, belonging to the technical field of impact tests of engine blades and disks, and solving the problem of poor versatility of existing impact damage prefabrication test devices for blades and disks with complex geometric configurations; the test device for prefabricating impact damage of engine blades and disks includes a bench, on which a launching device and a fixture assembly are arranged, and the fixture assembly is located at the projectile outlet of the launching device; a blade or a disk is installed on the fixture assembly; a measurement system is arranged outside the bench. In the invention, when performing the damage prefabrication test, a projectile is launched by the launching device to impact the blade and the disk, so as to cause damage; the fixture assembly can clamp and fix the blade and the disk, realize the installation attitude adjustment of the blade and the disk in multiple degrees of freedom, meet the clamping requirements of the blade and the disk under various impact conditions, has strong versatility and a wide application range.

Description

Technical Field

[0001] The present invention relates to the technical field of impact tests for engine blades and disks, and particularly to a test device and a test method for prefabricating impact damage to engine blades and disks. Background Art

[0002] During the service process of an aeroengine, foreign objects inhaled by the engine collide with the engine blades, resulting in blade damage and failure. Foreign object impact can cause local damage such as notches, pits, and scratches to the blades and disks of an aeroengine. The stress concentration, cracks, etc. generated will further induce overall damage, seriously threatening the safe operation of the aeroengine. Therefore, airworthiness standards, design specifications, and manuals for aeroengines such as MIL-E-5007D, JSGS-87231A, GJB214-87, and CCAR-33 have stipulated the anti-foreign object impact performance of engine blades and the anti-fatigue performance of blades after impact damage.

[0003] Precisely controllable prefabrication of impact damage to individual blades and integral disks is a fundamental link in studying the anti-fatigue performance of blades after impact damage and formulating maintenance guidelines, and is also a key link in evaluating and verifying the anti-impact performance of engine blades. During the process of verifying the anti-foreign object impact performance of blades and disks, the test scheme is generally designed in combination with the blade damage statistical atlas during the service process of an aeroengine to study the impact response and damage law of blades and disks when foreign objects impact at different postures and positions. Due to the diverse models of aeroengine blades and disks, they have complex curved surface geometries under different aerodynamic shape requirements, and the foreign object impact damage positions and angles of blades and disks under actual service conditions also show diverse statistical distribution characteristics. Therefore, if the impact damage test is to efficiently reproduce the typical impact conditions of blades and disks, the following two key technical problems must be solved: one is that the impact degrees of freedom of the blades and disks are as many as possible during the prefabrication of impact damage; the other is that the test device and test method have good versatility for different types of blades and disks.

[0004] A Chinese invention patent with the authorization announcement number CN110823724B discloses an observation experimental device for impact damage of aeroengine blades; in this patent, a rotating blade impact test with a single launch angle adjustment can be realized through a lead screw, but this method is only applicable to the single-degree-of-freedom impact of a rotating disk and cannot achieve a higher degree of freedom of impact; due to the lack of protection for non-target positions of the disk and control of disk rotation in this observation experimental device for impact damage of aeroengine blades, the actual impact damage position is difficult to control.

[0005] In a Chinese invention patent with the authorization announcement number CN113495002B, a rotating impact test device for non-full-ring fan blades of an aeroengine is disclosed. In a Chinese invention patent with the authorization announcement number CN114646445B, a rotating blade impact test device and a rotating blade impact test method are disclosed. In the solutions of these two patents, when conducting a rotating blisk impact test, a rotor test bench is used to drive the blisk to rotate. However, in this solution, only tests on the blisk are carried out, which is not applicable to the impact test of a single blade and cannot achieve multi-degree-of-freedom adjustment.

[0006] In a Chinese invention patent with the authorization announcement number CN110470446B, an experimental device for the service reliability of composite blades under impact, vibration, and high-temperature excitation is disclosed. In this patent, the influence of test environments such as the temperature and vibration of the blade is considered. However, the tail of the barrel of the light gas gun is arranged on the short fixed plate through the barrel fixing seat, which can only achieve two-degree-of-freedom rotation, and the setting of the complex environment limits the installation of the blisk and the adjustment of the impact degrees of freedom, and it is not applicable to the multi-degree-of-freedom impact damage prefabrication test of the blisk.

[0007] In a Chinese utility model patent with the authorization announcement number CN216208272U, an aeroengine blade impact resistance test simulation device is disclosed. In this patent, three telescopic cylinders are used to drive the adjustment of the angle and height of the blade in a single plane. However, its controllable degrees of freedom are still two, and multi-degree-of-freedom adjustment cannot be achieved, and the clamping part is not applicable to the blisk impact test.

[0008] In summary, the existing test devices and test methods mainly have two problems: one is that the foreign object impact tests are mainly carried out on rotating blisks or stationary blades, and the test devices and test methods adopted lack generality and compatibility; the other is that only the adjustment of a small number of impact degrees of freedom can be achieved, and there is a lack of a foreign object impact damage test device that can adjust more than two impact degrees of freedom, and it is difficult to accurately control the impact damage position of complex blade surfaces. Therefore, designing a multi-degree-of-freedom foreign object impact damage prefabrication test device and test method that is compatible with single blades and integral blisks has important engineering value for the evaluation of aeroengine foreign object impact damage and the verification of aeroengine impact resistance performance. Summary of the Invention

[0009] Aiming at the deficiencies in the prior art, the present invention provides a test device and a test method for prefabricating impact damage of engine blades and blisks, which solve the problems of poor generality and low impact degrees of freedom existing in the existing impact damage prefabrication test devices for blades and blisks with complex geometric configurations.

[0010] In the first aspect, in order to achieve the above object, the technical solution adopted by the present invention is as follows:

[0011] An experimental device for prefabricating impact damage of engine blades and disks, comprising a bench, a launching device, a fixture assembly and a measurement system; a launching device is arranged at one end of the bench, a fixture assembly is arranged at the other end of the bench, and the fixture assembly is located at the projectile outlet of the launching device; a blade or a disk is installed on the fixture assembly; a measurement system is arranged outside the bench.

[0012] In this solution, when conducting the damage prefabrication test, the blade or disk is installed on the fixture assembly, and the projectile is launched by the launching device to impact the blade or disk to cause damage; the fixture assembly is applicable to the clamping and fixing of the blade or disk, with strong versatility and a wide application range; the impact freedom is high and can be used for different impact postures; the measurement system can collect the image information of the blade or disk during the impact test, which is convenient for subsequent analysis of the test results and evaluation of the effect of impact damage prefabrication.

[0013] Further, the launching device includes a high-pressure gas tank, which is fixedly connected to the end of the bench; a pressure gauge, an inflation valve and a launching switch are arranged on the high-pressure gas tank; one end of the high-pressure gas tank is connected with an air cannon barrel; the axis of the air cannon barrel is parallel to the length direction of the bench; a projectile holder for loading the projectile is slidably arranged inside the air cannon barrel; the end of the air cannon barrel far from the high-pressure gas tank is the air cannon muzzle, and a projectile detachment device is arranged at the air cannon muzzle.

[0014] In this solution, the high-pressure gas tank launches the projectile along the air cannon barrel through the action of air pressure. When the projectile reaches the position of the air cannon muzzle, the projectile holder for loading the projectile is blocked by the projectile detachment device; the projectile continues to move and impacts the blade or disk; the projectile detachment device can prevent the projectile holder from following the projectile as an unexpected impact object to impact the blade or disk.

[0015] Further, the fixture assembly includes a bottom plate, which is rectangular; the bottom plate is horizontally arranged on the upper surface of the bench on the side of the air cannon muzzle, and a number of long bottom plate holes are opened on the bottom plate, and each long bottom plate hole is perpendicular to the axis direction of the air cannon barrel; bottom plate bolts are arranged in the long bottom plate holes, and the bottom plate bolts penetrate through the long bottom plate holes and are threadedly connected to the bench;

[0016] A rotating plate is installed on the bottom plate, and the rotating plate is circular; the rotating plate is horizontally arranged on the upper surface of the bottom plate; a number of arc waist holes of the rotating plate are arranged in a circular array on the same circumference on the rotating plate; rotating plate bolts are arranged in the arc waist holes of the rotating plate, and the rotating plate bolts penetrate through the arc waist holes of the rotating plate and are threadedly connected to the bottom plate;

[0017] The upper surface of the rotating plate is connected with a clamping block, and a rectangular clamping cavity is formed in the middle of the clamping block; a top block is slidably arranged in the clamping cavity, and the length of the top block perpendicular to the axis of the air cannon barrel is the same as the length of the inner side wall of the clamping cavity perpendicular to the axis of the air cannon barrel; several clamping cavity threaded holes are arranged on the side wall of the clamping block away from the muzzle of the air cannon, and a clamping bolt is threadedly connected in the clamping cavity threaded hole, and one end of the clamping bolt located in the clamping cavity abuts against the top block; a blade or a blade mounting kit for fixing the blade disc is clamped between the top block and the inner wall of the clamping cavity.

[0018] In this solution, during the process of clamping a single blade, by adjusting the position of the bottom plate on the bench and the rotation orientation of the rotating plate relative to the bottom plate, the attitude of the blade in the horizontal plane can be changed, and by adjusting the depth of the end of the blade inserted into the clamping cavity, the adjustment of the blade in the vertical direction can be realized, and finally the multi-degree-of-freedom installation attitude adjustment during the prefabrication of the impact damage of a single blade can be realized.

[0019] Furthermore, the fixture assembly further includes a blade disc mounting kit;

[0020] The blade disc mounting kit includes a vertical plate, and the vertical plate is clamped between the top block and the inner wall of the clamping cavity; several vertical plate long holes are formed in the vertical plate in the vertical direction, and vertical plate bolts are arranged in the vertical plate long holes; a connecting flange is arranged on one side of the vertical plate close to the muzzle of the air cannon, and the vertical plate bolts penetrate through the vertical plate long holes and are threadedly connected with the connecting flange;

[0021] A blade disc mounting shaft is connected to the connecting flange through a connecting shaft, and the blade disc mounting shaft, the connecting shaft and the connecting flange are coaxial in the horizontal direction; the diameter of the blade disc mounting shaft is smaller than the diameter of the connecting shaft, and the blade disc is mounted on the blade disc mounting shaft.

[0022] In this solution, during the process of clamping the blade disc by the blade disc mounting kit, by adjusting the position of the bottom plate on the bench and the rotation orientation of the rotating plate relative to the bottom plate, the adjustment of the attitude of the blade disc in the horizontal plane can be realized; by adjusting the vertical height of the connecting flange on the vertical plate, the adjustment of the height of the blade disc in the vertical direction can be realized, which is convenient for carrying out a flexible and efficient multi-degree-of-freedom foreign object impact test on the blade disc.

[0023] Furthermore, a blade disc baffle is arranged on one side of the blade disc close to the muzzle of the air cannon, and the blade disc baffle is mounted on the blade disc mounting shaft; a fastening nut is threadedly connected to one side of the blade disc mounting shaft close to the muzzle of the air cannon; a hollowed-out notch is formed in the blade disc baffle, and the size of the hollowed-out notch matches the size of the sub-blades on the blade disc.

[0024] In this solution, a hollowed-out notch is formed in the blade disc baffle. By adjusting the position of the hollowed-out notch on the blade disc baffle, an impact test can be carried out on the sub-blades at specific positions on the blade disc during the static blade disc impact, avoiding damage to other parts of the blade disc.

[0025] Furthermore, the test device for prefabricating impact damage of engine blades and disks further includes a protection assembly; the protection assembly includes a protective shell and a buffer. The protective shell covers the fixture assembly; a passage for the projectile launched by the launching device to pass through is provided on one side of the protective shell close to the muzzle of the air cannon; the material of the protective shell is a transparent material;

[0026] The buffer is arranged inside the protective shell, and the buffer is located on the side of the fixture assembly away from the launching device; the bottom of the buffer is detachably connected to the upper surface of the bench.

[0027] In this solution, the buffer is used to absorb the remaining kinetic energy after the impact of the projectile. The protective shell can isolate the space where the fixture assembly is located from the outside world, preventing the projectile from rebounding or generating debris during the impact, etc., which poses a threat to the safety of personnel and equipment.

[0028] Furthermore, the test device for prefabricating impact damage of engine blades and disks further includes a positioning assembly; the positioning assembly includes a fixed seat and a laser locator. The fixed seat is detachably connected to the upper surface of the bench and is located on the side of the fixture assembly away from the launching device; a laser locator is installed on the fixed seat, and the laser emission path of the laser locator coincides with the path of the projectile launched by the launching device.

[0029] In this solution, the irradiation point of the laser emitted by the laser locator on the blade or disk is the impact position of the projectile. It is convenient to adjust the attitude of the blade or disk according to the irradiation point of the laser, realizing precise control of the impact position of the blade or disk.

[0030] Furthermore, the measurement system includes a high-speed camera, a light source and a computer; the high-speed camera and the computer are electrically connected; the shooting direction of the high-speed camera and the irradiation direction of the light source both face the fixture assembly.

[0031] In this solution, the high-speed camera is used to shoot and monitor the impact speed of the projectile and the process of the projectile impacting the blades and disks, supporting subsequent test analysis; the light source is set to increase the brightness of the test site and ensure that the images captured by the high-speed camera are clear.

[0032] Furthermore, the test device for prefabricating impact damage of engine blades and disks further includes a power assist device, and the power assist device is used to drive the disk to rotate around the disk mounting shaft.

[0033] In a second aspect, based on the test device for prefabricating impact damage of engine blades and disks provided in the first aspect, the present invention provides a test method for prefabricating impact damage of engine blades and disks;

[0034] Performing a prefabrication test on the impact damage of the blade includes the following steps:

[0035] Step S1. Determine the parameters for the blade impact test: Determine the impact parameters and projectile parameters for the blade impact test to be conducted based on the impact damage prefabrication test outline of the aero-engine blade.

[0036] Step S2. Prepare for the blade impact test:

[0037] Install the base plate and use the base plate bolts to fixedly connect the base plate to the bench. Install the rotating plate and use the rotating plate bolts to fixedly connect the rotating plate to the base plate.

[0038] Make impact marks on the blade to be tested, and use the top block and clamping bolts to fix the end of the marked blade to be tested in the clamping cavity.

[0039] Install the positioning component. Move the base plate on the bench along the long slots of the base plate, rotate the rotating plate on the base plate along the arc waist slots of the rotating plate, and adjust the clamping depth of the blade end in the vertical direction so that the laser line emitted by the laser locator in the positioning component is aligned with the impact mark on the blade to be tested. Remove the positioning component and install the protection component. Calibrate the pixel space size of the measurement system's field of view.

[0040] Step S3. Conduct the blade impact test: Determine the air pressure value of the high-pressure gas tank in the launching device according to the impact parameters and projectile parameters. Turn on the launch switch to launch the projectile to impact the marked position on the blade to be tested.

[0041] Step S4. Data acquisition: Use the measurement system to acquire the image data during the blade impact test.

[0042] Step S5. Evaluate the impact damage effect of the blade: Compare the image data before and after the blade impact test and analyze the impact damage failure law of the blade.

[0043] Conduct the impact damage prefabrication test on the blisk, including the following steps:

[0044] Step T1. Determine the blisk impact test parameters: Determine the impact parameters and projectile parameters for the blisk impact test to be conducted according to the impact damage prefabrication test outline of the aero-engine blisk.

[0045] Step T2. Prepare for the blisk impact test:

[0046] Install the base plate and use the base plate bolts to fixedly connect the base plate to the bench. Install the rotating plate and use the rotating plate bolts to fixedly connect the rotating plate to the base plate.

[0047] Assemble the blisk installation kit, thread-connect the blisk installation shaft, connecting shaft, and connecting flange, and use the vertical plate bolts to fixedly connect the connecting flange to the vertical plate.

[0048] Make impact marks on the bladed disk to be tested, and install the bladed disk baffle and the bladed disk with impact marks on the bladed disk mounting shaft; use a fastening nut to limit the bladed disk and the bladed disk baffle; use a top block and a clamping bolt to fix the bladed disk mounting kit with the bladed disk installed in the clamping cavity of the clamping block;

[0049] Install the positioning component. Move the bottom plate on the bench along the long slots of the bottom plate, rotate the rotating plate on the bottom plate along the arc waist slots of the rotating plate, adjust the vertical position of the connecting flange, rotate the bladed disk and the bladed disk baffle so that the position to be impacted marked on the bladed disk aligns with the hollow notch on the bladed disk baffle, and make the laser line emitted by the laser locator in the positioning component align with the impact mark on the bladed disk to be tested; Remove the positioning component and install the protection component; Calibrate the pixel space size of the measurement system field of view;

[0050] Step T3, conduct the bladed disk impact test: Determine the air pressure value of the high-pressure gas tank in the launching device according to the impact parameters and the projectile parameters; Turn on the launch switch to launch the projectile to impact the marked position on the bladed disk to be tested;

[0051] Step T4, data acquisition: Use the measurement system to acquire the image data during the bladed disk impact test;

[0052] Step T5, evaluate the impact damage effect of the bladed disk: Compare the image data before and after the bladed disk impact test, and analyze the impact damage failure law of the bladed disk.

[0053] The beneficial effects of the present invention are:

[0054] In the test device for prefabricating impact damage of engine blades and bladed disks provided by the present invention, a fixture assembly is used to fix the blades or the bladed disk, and the versatility is relatively strong; When conducting the prefabrication test of blade impact damage, use the fixture assembly to fix the blade. The bottom plate can move along the long slots of the bottom plate in the horizontal direction perpendicular to the axis of the air cannon barrel, and the rotating plate can rotate in the circumferential direction along multiple arc waist slots of the rotating plate, and the vertical height of the blade can be adjusted. Finally, the installation attitude adjustment of the blade in multiple degrees of freedom is realized to meet the test clamping requirements of the blade under various impact conditions; When conducting the prefabrication test of bladed disk impact damage, use the fixture assembly to fix the bladed disk. The connecting flange can move along the direction of multiple long slots of the vertical plate to adjust the height of the bladed disk in the vertical direction. The bladed disk and the bladed disk baffle can rotate around the bladed disk mounting shaft. Finally, the installation attitude adjustment of the bladed disk in multiple degrees of freedom and the impact on the specified position on the bladed disk are realized to meet the test clamping requirements of the bladed disk under various impact conditions; There is a hollow notch on the bladed disk baffle. When conducting an impact test on a specified part of the bladed disk, it can avoid causing unplanned damage to other parts of the bladed disk, improve the effectiveness of the impact test under specific working conditions, and save the test cost.

[0055] For the prefabrication tests of blade impact damage and blisk impact damage, components such as the bottom plate, bottom plate bolts, rotating plate, rotating plate bolts, clamping cavity, top block, and clamping bolts in the fixture assembly are common. Therefore, the entire fixture assembly has high adaptability and can simultaneously meet the requirements of prefabrication tests for blade and blisk impact damage, enabling rapid switching between blade tests and blisk tests. Under the framework of the same test outline, prefabrication tests for blade and blisk impact damage can be carried out simultaneously, improving the versatility and flexibility of the tests.

[0056] The positioning component is used to determine the impact position of the projectile on the blade or blisk, guiding the adjustment of the fixture assembly in each degree of freedom to achieve precise control of the impact position on the blade or blisk. In the protection component, the protective shell is used to isolate the space where the fixture assembly, blade, and blisk are located from the outside world, and the buffer is used to absorb the remaining kinetic energy of the projectile, preventing threats to the safety of personnel and equipment caused by projectile rebound, projectile fragments, etc. during the impact process. The measurement system is used to measure the impact velocity of the projectile and record the process of the projectile impacting the blade and blisk, facilitating subsequent analysis of test results and evaluation of the effect of prefabricated impact damage. Brief Description of the Drawings

[0057] Figure 1 Structural schematic diagram of the test device for prefabricating impact damage of engine blades and blisks according to the present invention;

[0058] Figure 2 Side view of the test device for prefabricating impact damage of engine blades and blisks according to the present invention;

[0059] Figure 3 Structural schematic diagram of the fixture assembly clamping the blade according to the present invention;

[0060] Figure 4 Structural schematic diagram of the fixture assembly clamping the blisk according to the present invention;

[0061] Figure 5 Top view of the fixture assembly clamping the blisk according to the present invention;

[0062] Figure 6 Structural schematic diagram of the blisk baffle according to the present invention.

[0063] Reference Signs:

[0064] 1. Bench; 2. Launch device; 201. High-pressure gas tank; 202. Pressure gauge; 203. Inflation valve; 204. Launch switch; 205. Air cannon barrel; 206. Air cannon muzzle; 207. Bullet ejection device; 3. Fixture assembly; 301. Base plate; 302. Long slot on the base plate; 303. Base plate bolt; 304. Rotating plate; 305. Arc waist hole on the rotating plate; 306. Rotating plate bolt; 307. Clamping block; 309. Clamping bolt; 310. Top block; 311. Vertical plate; 312. Long slot on the vertical plate; 313. Vertical plate bolt; 314. Blade disk mounting shaft; 315. Connecting shaft; 316. Connecting flange; 318. Locknut; 319. Blade disk baffle; 320. Hollow notch; 4. Positioning assembly; 401. Fixed seat; 402. Laser locator; 501. Protective shell; 502. Buffer; 6. Measuring system; 601. High-speed camera; 602. Light source; 603. Computer; 7. Blade; 8. Blade disk. Detailed implementation mode

[0065] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. The following describes the specific implementation mode of the present invention to facilitate those skilled in the art of the present technology to understand the present invention. However, it should be clear that the present invention is not limited to the scope of the specific implementation mode. For those of ordinary skill in the art of the present technology, as long as various changes are within the spirit and scope of the present invention defined and determined by the appended claims, these changes are obvious, and all inventions and creations using the concept of the present invention are within the scope of protection.

[0066] Embodiment 1

[0067] As Figure 1 and Figure 2 shown, this embodiment provides a test device for prefabricating impact damage of engine blades and blade disks. This test device for prefabricating impact damage of engine blades and blade disks is applicable to the prefabrication test of impact damage of blades and blade disks with complex geometric configurations, has strong versatility, and can realize multi-degree-of-freedom adjustment of the impact postures of blades and blade disks. Specifically, it includes:

[0068] Bench 1, launch device 2, fixture assembly 3, positioning assembly 4, protection assembly, and measuring system 6;

[0069] Among them, a launching device 2 is provided at one end of the test bench 1, and a clamp assembly 3 is provided at the other end of the test bench 1, and the clamp assembly 3 is located at the projectile outlet of the launching device 2; a blade 7 or a blade disk 8 is installed on the clamp assembly 3; when performing a damage prefabrication test, the projectile is launched by the launching device 2 to impact the blade 7 or the blade disk 8 to cause damage to it; a positioning assembly 4 is provided on the side of the clamp assembly 3 away from the launching device 2; a protective assembly is provided on the upper surface of the test bench 1 close to the clamp assembly 3 at one end; a measuring system 6 is provided on the outside of the test bench 1, and the measuring system 6 can collect image information of the blade 7 or the blade disk 8 during the impact test, so as to facilitate the subsequent test result analysis and impact damage prefabrication effect evaluation.

[0070] The launching device 2 includes a high-pressure gas tank 201, an air gun barrel 205, a pressure gauge 202, an air charging valve 203, a launching switch 204 and a bullet ejecting device 207;

[0071] The high-pressure gas tank 201 is fixedly connected to the end of the gantry 1; the high-pressure gas tank 201 is provided with a pressure gauge 202, a charging valve 203 and a firing switch 204; one end of the high-pressure gas tank 201 is connected to an air gun barrel 205; the axis of the air gun barrel 205 is parallel to the length direction of the gantry 1; the air gun barrel 205 is provided with a cartridge for loading the projectile in a sliding manner; the end of the air gun barrel 205 away from the high-pressure gas tank 201 is an air gun muzzle 206, and the air gun muzzle 206 is provided with a bullet-removing device 207. The high-pressure gas tank 201 launches the projectile along the air gun barrel 205 through the action of gas pressure, and when the projectile is launched to the position of the air gun muzzle 206, the cartridge for loading the projectile is blocked by the bullet-removing device 207; the projectile continues to move and impacts the blade 7 or the blade disk 8; the bullet-removing device 207 can prevent the cartridge from being an unexpected impact object and following the projectile to impact the blade 7 or the blade disk 8 together.

[0072] As a preferred embodiment of the present invention, the ejection device 207 is of mechanical or electromagnetic type. The mechanical ejection device separates the cartridge case from the projectile body by the collision between the ejection device and the cartridge case; the electromagnetic ejection device applies an electromagnetic field to cause the cartridge case to be subjected to reverse force and separated from the projectile body.

[0073] The clamp assembly 3 includes a bottom plate 301, bottom plate bolts 303, a rotating plate 304, a rotating plate bolts 306, a clamping block 307, a top block 310, a clamping bolt 309 and a blade disk installation kit;

[0074] like Figure 3As shown in the figure, the bottom plate 301 is rectangular; the bottom plate 301 is horizontally arranged on the upper surface of the bench 1 on one side of the muzzle 206 of the air cannon. A number of long strip holes 302 are provided on the bottom plate 301, and each long strip hole 302 of the bottom plate is perpendicular to the axial direction of the air cannon barrel 205; a bottom plate bolt 303 is arranged in the long strip hole 302 of the bottom plate, and the bottom plate bolt 303 penetrates through the long strip hole 302 of the bottom plate and is threadedly connected to the bench 1; a rotating plate 304 is installed on the bottom plate 301, and the rotating plate 304 is circular; the rotating plate 304 is horizontally arranged on the upper surface of the bottom plate 301 and is coaxial with the bottom plate 301 in the vertical direction; a number of rotating plate arc waist holes 305 are arranged on the rotating plate 304 in an annular array on the same circumference; a rotating plate bolt 306 is arranged in the rotating plate arc waist hole 305, and the rotating plate bolt 306 penetrates through the rotating plate arc waist hole 305 and is threadedly connected to the bottom plate 301.

[0075] A clamping block 307 is connected to the upper surface of the rotating plate 304. A rectangular clamping cavity is provided in the middle of the clamping block 307; a top block 310 is slidably arranged in the clamping cavity. The length of the top block 310 perpendicular to the axial direction of the air cannon barrel 205 is the same as the length of the inner side wall of the clamping cavity perpendicular to the axial direction of the air cannon barrel 205; a number of clamping cavity threaded holes are provided on the side wall of the clamping block 307 away from the muzzle 206 of the air cannon. A clamping bolt 309 is threadedly connected in the clamping cavity threaded hole, and one end of the clamping bolt 309 located in the clamping cavity abuts against the top block 310; a blade 7 or a blade disc installation kit for fixing the blade disc 8 is clamped between the top block 310 and the inner wall of the clamping cavity.

[0076] When performing the impact damage prefabrication test on a single blade 7, the blade 7 is clamped between the top block 310 and the inner wall of the clamping cavity; by adjusting the position of the bottom plate 301 on the bench 1 and adjusting the rotation orientation of the rotating plate 304 relative to the bottom plate 301, the attitude of the blade 7 in the horizontal plane can be changed, and by adjusting the depth of the blade 7 inserted into the clamping cavity, the adjustment of the blade 7 in the vertical direction can be realized, and finally the multi-degree-of-freedom installation attitude adjustment of a single blade 7 can be realized.

[0077] The blade disc installation kit includes a vertical plate 311, a vertical plate bolt 313, a connecting flange 316, a blade disc installation shaft 314, a connecting shaft 315, a fastening nut 318 and a blade disc baffle 319;

[0078] As Figure 4 and Figure 5As shown in the figure, a flat plate is vertically connected to the bottom of the vertical plate 311. The flat plate is accommodated inside the clamping cavity, and the vertical plate 311 is clamped between the top block 310 and the inner wall of the clamping cavity. A plurality of vertical plate long holes 312 are vertically formed in the vertical plate 311, and vertical plate bolts 313 are arranged in the vertical plate long holes 312; a connecting flange 316 is arranged on one side of the vertical plate 311 close to the muzzle 206 of the air cannon. The vertical plate bolts 313 penetrate through the vertical plate long holes 312 and are threadedly connected to the connecting flange 316; a disk mounting shaft 314 is connected to the connecting flange 316 through a connecting shaft 315. The disk mounting shaft 314, the connecting shaft 315, and the connecting flange 316 are coaxial in the horizontal direction and are threadedly connected; the diameter of the disk mounting shaft 314 is smaller than the diameter of the connecting shaft 315, and the disk 8 is mounted on the disk mounting shaft 314. A disk baffle 319 is arranged on one side of the disk 8 close to the muzzle 206 of the air cannon, and the disk baffle 319 is mounted on the disk mounting shaft 314; a fastening nut 318 is threadedly connected to one side of the disk mounting shaft 314 close to the muzzle 206 of the air cannon.

[0079] When conducting the impact damage prefabrication test on the entire disk 8, the disk 8 is mounted on the disk mounting shaft 314; by adjusting the position of the bottom plate 301 on the test bench 1 and the rotation orientation of the rotating plate 304 relative to the bottom plate 301, the attitude adjustment of the disk 8 in the horizontal plane can be realized; by adjusting the vertical height of the connecting flange 316 on the vertical plate 311, the height adjustment of the disk 8 in the vertical direction can be realized, which is convenient for conducting a flexible and efficient multi-degree-of-freedom foreign object impact test on the disk 8.

[0080] As Figure 6 shown, a hollow notch 320 is formed in the disk baffle 319, and the size of the hollow notch 320 matches the size of the sub-blades on the disk 8; by adjusting the position of the hollow notch 320 on the disk baffle 319, an impact test on specific sub-blades on the disk 8 can be conducted during the static disk 8 impact, avoiding damage to other parts of the disk 8.

[0081] The protection component includes a protective shell 501 and a buffer 502;

[0082] The protective shell 501 is a hollow cubic structure that covers the fixture assembly 3; a passage for the projectile emitted by the launching device 2 to pass through is formed on one side of the protective shell 501 close to the muzzle 206 of the air cannon; the material of the protective shell 501 is a transparent material; the buffer 502 is located on the side of the fixture assembly 3 away from the launching device 2 and is used to absorb the remaining kinetic energy after the projectile impact; the bottom of the buffer 502 is detachably connected to the upper surface of the test bench 1; the protective shell 501 can isolate the space where the fixture assembly 3 is located from the outside world, preventing the projectile from rebounding or generating fragments during the impact from threatening the safety of personnel and equipment.

[0083] The positioning component 4 includes a fixed seat 401 and a laser locator 402;

[0084] The fixed seat 401 is detachably connected to the upper surface of the bench 1 and is located on the side of the fixture assembly 3 away from the launching device 2; a laser locator 402 is installed on the fixed seat 401, and the laser emission path of the laser locator 402 coincides with the path of the projectile launched by the launching device 2. The irradiation point of the laser emitted by the laser locator 402 on the blade 7 or the disk 8 is the impact position of the projectile. According to the irradiation point of the laser, it is convenient to adjust the attitude of the blade 7 or the disk 8, realizing precise control of the impact position of the blade 7 or the disk 8.

[0085] The measurement system 6 includes a high-speed camera 601, a light source 602 and a computer 603;

[0086] The high-speed camera 601 and the computer 603 are electrically connected; the shooting direction of the high-speed camera 601 and the irradiation direction of the light source 602 both face the fixture assembly 3. The high-speed camera 601 is used to shoot and monitor the impact speed of the projectile and the process of the projectile impacting the blade 7 and the disk 8, supporting subsequent test analysis; the light source 602 is set to increase the brightness of the test site and ensure the clarity of the images captured by the high-speed camera 601.

[0087] In this embodiment, when performing the impact damage prefabrication test in the rotating state of the disk 8, a power assist device can be set on one side of the disk 8 to drive the disk 8 to rotate around the disk mounting shaft 314.

[0088] Specifically, the auxiliary power device can be a high-pressure air blowing device. The high-pressure air blowing device blows high-pressure and high-speed air flow towards the disk 8 to drive the disk 8 to rotate around the disk mounting shaft 314, which can meet the requirements of the foreign object impact test on the rotating disk 8.

[0089] Embodiment 2

[0090] Based on the test device for impact damage prefabrication of engine blades and disks provided in Embodiment 1, this embodiment provides a test method for impact damage prefabrication of engine blades; it includes the following steps:

[0091] Step S1, determining the impact test parameters of the blade 7:

[0092] According to the impact damage prefabrication test outline of the aero-engine blade 7, determine the impact parameters and projectile parameters of the blade 7 impact test; the impact parameters include the target position and the target angle parameter; the projectile parameters include the projectile mass, the projectile speed, and the projectile attitude parameter.

[0093] Step S2, preparing for the blade 7 impact test:

[0094] Install the mounting base plate 301 and use the base plate bolts 303 to fixedly connect the base plate 301 to the bench 1. Install the rotating plate 304 and use the rotating plate bolts 306 to fixedly connect the rotating plate 304 to the base plate 301;

[0095] Make impact marks on the blade 7 to be tested, and use the top block 310 and the clamping bolt 309 to fix the end of the marked blade 7 to be tested in the clamping cavity;

[0096] Install the positioning component 4. Move the base plate 301 on the bench 1 along the long slot 302 of the base plate, rotate the rotating plate 304 on the base plate 301 along the arc waist hole 305 of the rotating plate, and adjust the clamping depth of the end of the blade 7 in the vertical direction so that the laser line emitted by the laser locator 402 in the positioning component 4 is aligned with the impact mark on the blade 7 to be tested. Remove the positioning component 4 and install the protection component. Calibrate the pixel space size of the field of view of the measurement system 6.

[0097] Step S3: Conduct the impact test on the blade 7:

[0098] Determine the air pressure value of the high-pressure gas tank 201 in the launching device 2 according to the impact parameters and the projectile parameters; determine the projectile model, place the projectile in the projectile carrier, and slidably arrange the projectile carrier in the air cannon barrel 205; turn on the launch switch 204 to launch the projectile to impact the blade 7 to be tested.

[0099] Step S4: Data acquisition:

[0100] Use the measurement system 6 to collect the image data during the impact test of the blade 7;

[0101] Step S5: Evaluate the impact damage effect of the blade 7;

[0102] Compare the image data of the blade 7 before and after the impact test; use a microscope and a depth gauge to observe the damage morphology and measure the test damage parameters such as the damage position, depth, and width, and analyze and summarize the impact damage failure law of the blade 7 according to the changes in the test damage parameters, impact parameters, and projectile parameters.

[0103] Embodiment 3

[0104] Based on the test device for prefabricating impact damage of engine blades and disks provided in Embodiment 1, this embodiment provides a test method for prefabricating impact damage of engine disks; including the following steps:

[0105] Step T1: Determine the impact test parameters of the disk 8:

[0106] Determine the impact parameters and projectile parameters of the impact test of the disk 8 according to the impact damage prefabrication test outline of the aeroengine disk 8; the impact parameters include the target position and the target angle parameters; the projectile parameters include the projectile mass, the projectile velocity, and the projectile attitude parameters.

[0107] Step T2, Preparation for the impact test of the blisk 8:

[0108] Install the bottom plate 301 and use the bottom plate bolts 303 to fixedly connect the bottom plate 301 to the bench 1. Install the rotating plate 304 and use the rotating plate bolts 306 to fixedly connect the rotating plate 304 to the bottom plate 301;

[0109] Assemble the blisk installation kit so that the blisk installation shaft 314, the connecting shaft 315, and the connecting flange 316 are threadedly connected, and use the vertical plate bolts 313 to fixedly connect the connecting flange 316 to the vertical plate 311;

[0110] Make impact marks on the blisk 8 to be tested, and install the blisk baffle 319 and the blisk 8 with the impact marks on the blisk installation shaft 314; use the fastening nut 318 to limit the blisk 8 and the blisk baffle 319; use the top block 310 and the clamping bolts 309 to fix the blisk installation kit with the blisk 8 installed in the clamping cavity of the clamping block 307;

[0111] Install the positioning assembly 4. Move the bottom plate 301 on the bench 1 along the long strip hole 302 of the bottom plate, rotate the rotating plate 304 on the bottom plate 301 along the arc waist hole 305 of the rotating plate, adjust the vertical position of the connecting flange 316, rotate the blisk 8 and the blisk baffle 319 so that the impact position marked on the blisk 8 is aligned with the hollow notch 320 on the blisk baffle 319, and make the laser line emitted by the laser locator 402 in the positioning assembly 4 align with the impact mark on the blisk 8 to be tested; Remove the positioning assembly 4 and install the protection assembly; Calibrate the pixel space size of the field of view of the measurement system 6.

[0112] Step T3, Conduct the impact test of the blisk 8:

[0113] Determine the air pressure value of the high-pressure gas tank 201 in the launching device 2 according to the impact parameters and the projectile parameters; Determine the projectile model, place the projectile in the projectile carrier, and slidably arrange the projectile carrier in the air cannon barrel 205; Turn on the launch switch 204 to launch the projectile to impact the blisk 8 to be tested.

[0114] Step T4, Data acquisition:

[0115] Use the measurement system 6 to acquire the image data during the impact test of the blisk 8.

[0116] Step T5, Evaluate the impact damage effect of the blisk 8;

[0117] Compare the image data before and after the impact test of the blisk 8; Use a microscope and a depth gauge to observe the damage morphology and measure the test damage parameters such as the damage position, depth, and width, and analyze and summarize the impact damage failure law of the blisk 8 according to the changes in the test damage parameters, impact parameters, and projectile parameters.

[0118] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims

1. A test device for prefabrication of impact damage of engine blades and blisks, characterized in that: The apparatus comprises a platform (1), a launching device (2), a fixture assembly (3) and a measuring system (6); the launching device (2) is arranged at one end of the platform (1), the fixture assembly (3) is arranged at the other end of the platform (1), and the fixture assembly (3) is located at the projectile outlet of the launching device (2); a blade (7) or a blade disk (8) is installed on the fixture assembly (3); and the measuring system (6) is arranged on the outer side of the platform (1); The launching device (2) comprises a high-pressure gas tank (201), wherein the high-pressure gas tank (201) is fixedly connected to the end of the platform (1); the high-pressure gas tank (201) is provided with a pressure gauge (202), a charging valve (203) and a launching switch (204); one end of the high-pressure gas tank (201) is connected to an air gun barrel (205); the axis of the air gun barrel (205) is parallel to the length direction of the platform (1); a bullet holder for loading a projectile is slidably provided inside the air gun barrel (205); the end of the air gun barrel (205) away from the high-pressure gas tank (201) is an air gun muzzle (206), and the air gun muzzle (206) is provided with a bullet removal device (207); The clamp assembly (3) comprises a bottom plate (301), and the bottom plate (301) is rectangular in shape; the bottom plate (301) is horizontally arranged on the upper surface of the stand (1) on the side of the air cannon muzzle (206); a plurality of bottom plate long strip holes (302) are opened on the bottom plate (301), and each of the bottom plate long strip holes (302) is perpendicular to the axial direction of the air cannon barrel (205); a bottom plate bolt (303) is arranged in the bottom plate long strip hole (302), and the bottom plate bolt (303) passes through the bottom plate long strip hole (302) and is threadedly connected to the stand (1); A rotating plate (304) is mounted on the bottom plate (301), and the rotating plate (304) is circular in shape; the rotating plate (304) is horizontally arranged on the upper surface of the bottom plate (301); a plurality of rotating plate circular arc waist holes (305) arranged in a circular array on the same circumference are opened on the rotating plate (304); a rotating plate bolt (306) is arranged in the rotating plate circular arc waist hole (305), and the rotating plate bolt (306) passes through the rotating plate circular arc waist hole (305) and is threadedly connected to the bottom plate (301); The upper surface of the rotating plate (304) is connected to a clamping block (307), and a rectangular clamping cavity is provided in the middle of the clamping block (307); a top block (310) is slidably arranged in the clamping cavity, and the length of the top block (310) perpendicular to the axis of the air cannon barrel (205) is the same as the length of the inner wall of the clamping cavity perpendicular to the axis of the air cannon barrel (205); a plurality of clamping cavity threaded holes are arranged on the side wall of the clamping block (307) away from the air cannon muzzle (206), and a clamping bolt (309) is threadedly connected to the inner thread hole of the clamping cavity, and one end of the clamping bolt (309) located in the clamping cavity abuts against the top block (310); a blade (7) or a blade disk installation kit for fixing the blade disk (8) is clamped between the top block (310) and the inner wall of the clamping cavity.

2. The test device for prefabrication of engine blade and blade disk impact damage according to claim 1, characterized in that: The blade disk installation kit comprises a vertical plate (311), wherein the vertical plate (311) is clamped between the top block (310) and the inner wall of the clamping cavity; a plurality of vertical plate long holes (312) are provided on the vertical plate (311) along the vertical direction, and vertical plate bolts (313) are arranged in the vertical plate long holes (312); a connecting flange (316) is provided on one side of the vertical plate (311) close to the muzzle (206) of the air cannon, and the vertical plate bolts (313) pass through the vertical plate long holes (312) and are threadedly connected to the connecting flange (316); The connecting flange (316) is connected to a blade disk mounting shaft (314) via a connecting shaft (315); the blade disk mounting shaft (314), the connecting shaft (315) and the connecting flange (316) are coaxial in a horizontal direction; the diameter of the blade disk mounting shaft (314) is smaller than the diameter of the connecting shaft (315); and the blade disk (8) is mounted on the blade disk mounting shaft (314).

3. The test device for prefabricating impact damage of engine blades and blisks according to claim 2, characterized in that: A blade disc baffle (319) is provided on one side of the blade disc (8) close to the air cannon muzzle (206), and the blade disc baffle (319) is mounted on the blade disc mounting shaft (314); a fastening nut (318) is threadedly connected to one side of the blade disc mounting shaft (314) close to the air cannon muzzle (206); a hollow notch (320) is provided on the blade disc baffle (319), and the size of the hollow notch (320) matches the size of the sub-blades on the blade disc (8).

4. The test device for prefabricating impact damage of engine blades and blisks according to claim 2, characterized in that: It also includes a protection component; the protection component includes a protection shell (501) and a buffer (502); the protection shell (501) covers the clamp assembly (3); a channel for the projectile launched by the launch device (2) to pass through is opened on a side of the protection shell (501) close to the muzzle (206) of the air cannon; the material of the protection shell (501) is a transparent material; The buffer (502) is arranged in the protective shell (501), and the buffer (502) is located on a side of the clamp assembly (3) away from the launching device (2); the bottom of the buffer (502) is detachably connected to the upper surface of the stand (1).

5. The test device for prefabrication of engine blade and blade disk impact damage according to claim 2, characterized in that: It also includes a positioning component (4); the positioning component (4) includes a fixing seat (401) and a laser locator (402); the fixing seat (401) is detachably connected to the upper surface of the platform (1) and is located on a side of the clamping component (3) away from the launching device (2); the laser locator (402) is installed on the fixing seat (401), and the laser emission path of the laser locator (402) coincides with the path of the projectile emitted by the launching device (2).

6. The test device for prefabrication of engine blade and blade disk impact damage according to claim 2, characterized in that: The measuring system (6) comprises a high-speed camera (601), a light source (602) and a computer (603); the high-speed camera (601) and the computer (603) are electrically connected; the shooting direction of the high-speed camera (601) and the irradiation direction of the light source (602) are both toward the fixture assembly (3).

7. The test device for prefabrication of engine blade and blade disk impact damage according to claim 2, characterized in that: It also includes a power assist device, which is used to drive the blade disk (8) to rotate around the blade disk installation shaft (314).

8. A test method based on the test device for prefabricating impact damage of engine blades and blisks according to any one of claims 1 to 6, characterized in that: Performing an impact damage prefabrication test on a blade (7) comprises the following steps: Step S1, determining blade (7) impact test parameters: determining impact parameters and projectile parameters of the impact test of the blade (7) to be tested according to the impact damage prefabrication test outline of the aircraft engine blade (7); Step S2, blade (7) impact test preparation: Installing a bottom plate (301) and fixing the bottom plate (301) to the stand (1) using bottom plate bolts (303), installing a rotating plate (304) and fixing the rotating plate (304) to the bottom plate (301) using rotating plate bolts (306); An impact mark is made on the blade to be tested (7), and the marked end of the blade to be tested (7) is fixed in the clamping cavity using a top block (310) and a clamping bolt (309); Installing the positioning assembly (4), moving the bottom plate (301) on the stand (1) along the bottom plate long strip hole (302), rotating the rotating plate (304) on the bottom plate (301) along the rotating plate arc waist hole (305), and adjusting the clamping depth of the end of the blade (7) in the vertical direction so that the laser line emitted by the laser locator (402) in the positioning assembly (4) is aligned with the impact mark on the blade (7) to be tested; removing the positioning assembly (4), installing the protection assembly; and calibrating the pixel space size of the field of view of the measurement system (6); Step S3, performing an impact test on the blade (7): determining the air pressure value of the high-pressure gas tank (201) in the launch device (2) according to the impact parameter and the projectile parameter; turning on the launch switch (204) to launch the projectile to impact the marked position on the blade (7) to be tested; Step S4, data acquisition: using the measurement system (6) to acquire image data of the blade (7) during the impact test; Step S5, evaluating the impact damage effect of the blade (7): comparing the image data of the blade (7) before and after the impact test, and analyzing the impact damage failure law of the blade (7); The impact damage prefabrication test of the blade disk (8) includes the following steps: Step T1, determining the impact test parameters of the blade disk (8): determining the impact parameters and projectile parameters of the impact test of the blade disk (8) to be tested according to the impact damage prefabrication test outline of the aircraft engine blade disk (8); Step T2, preparation for the impact test of the blade disk (8): Installing a bottom plate (301) and fixing the bottom plate (301) to the stand (1) using bottom plate bolts (303), installing a rotating plate (304) and fixing the rotating plate (304) to the bottom plate (301) using rotating plate bolts (306); Assemble the blade disk installation kit so that the blade disk installation shaft (314), the connecting shaft (315) and the connecting flange (316) are threadedly connected, and use the vertical plate bolts (313) to fix the connecting flange (316) to the vertical plate (311); Make an impact mark on the blade disk (8) to be tested, and install the blade disk baffle (319) and the blade disk (8) with the impact mark on the blade disk installation shaft (314); use the fastening nut (318) to limit the blade disk (8) and the blade disk baffle (319); use the top block (310) and the clamping bolt (309) to fix the blade disk installation kit with the blade disk (8) installed in the clamping cavity of the clamping block (307); Install the positioning assembly (4), move the bottom plate (301) on the test bench (1) along the bottom plate strip hole (302), rotate the rotating plate (304) on the bottom plate (301) along the rotating plate arc waist hole (305), adjust the vertical position of the connecting flange (316), rotate the blade disk (8) and the blade disk baffle (319), align the position to be impacted marked on the blade disk (8) with the hollow notch (320) on the blade disk baffle (319), and align the laser line emitted by the laser locator (402) in the positioning assembly (4) with the impact mark on the blade disk (8) to be tested; remove the positioning assembly (4), install the protection assembly; calibrate the pixel space size of the field of view of the measurement system (6); Step T3, performing an impact test on the blade disk (8): determining the air pressure value of the high-pressure gas tank (201) in the launch device (2) according to the impact parameters and the projectile parameters; turning on the launch switch (204), launching the projectile to impact the marked position on the blade disk (8) to be tested; Step T4, data acquisition: using the measurement system (6) to acquire image data of the blade disk (8) during the impact test; Step T5, evaluating the impact damage effect of the blade disk (8): comparing the image data of the blade disk (8) before and after the impact test, and analyzing the impact damage failure law of the blade disk (8).

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