Test device and test method for impact damage prefabrication of engine blade and blade disc

Abstract

The invention discloses an engine blade and blade disc impact damage prefabrication test device and test method, belongs to the technical field of engine blade and blade disc impact tests, and solves the problem that an existing impact damage prefabrication test device is not high in universality for blades and blade discs with complex geometric configurations. The engine blade and blade disc impact damage prefabrication test device comprises a rack, a launching device and a clamp assembly are arranged on the rack, and the clamp assembly is located at a projectile body outlet of the launching device; a blade or a blade disc is mounted on the clamp assembly; a measuring system is arranged on the outer side of the rack. According to the method, when a damage prefabrication test is carried out, the projectile body is launched through the launching device to impact the blade and the blade disc, so that the blade and the blade disc are damaged; the blade and the blade disc can be clamped and fixed through the clamp assembly, multi-degree-of-freedom installation posture adjustment of the blade and the blade disc is achieved, the clamping requirements of the blade and the blade disc under various impact conditions are met, universality is high, and the application range is wide.

Description

Technical Field

[0001] The invention relates to the technical field of engine blade and blade disk impact test, in particular to a test device and a test method for prefabricating engine blade and blade disk impact damage. Background Art

[0002] During the service of aircraft engines, foreign objects sucked into the engine collide with the engine blades, causing damage and failure of the blades. The impact of foreign objects will cause local damage such as notches, pits, and notches to the blades and blade disks of aircraft engines. The resulting stress concentration and cracks will further induce overall damage, seriously threatening the safe operation of aircraft engines. Therefore, the MIL-E-5007D, JSGS-87231A, GJB214-87, CCAR-33 and other aircraft engine airworthiness standards, design specifications and manuals have stipulated the foreign object impact resistance of engine blades and the fatigue resistance of blades after impact damage.

[0003] Precise and controllable impact damage prefabrication of single blades and whole blade disks is the basic link for studying the fatigue resistance of blades after impact damage and formulating maintenance criteria, and is also a key link for evaluating and verifying the impact resistance of engine blades. In the process of verifying the resistance of blades and blade disks to foreign object impact, the test scheme is generally designed in combination with the statistical spectrum of blade damage during the service of aircraft engines to study the impact response and damage law of blades and blade disks when foreign objects impact in different postures and positions. Due to the variety of models of blades and blade disks of aircraft engines, they have complex curved surface geometries under different aerodynamic shape requirements, and the positions and angles of foreign object impact damage of blades and blade 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 blade disks, the following two key technical problems must be solved: First, the impact degrees of freedom of blades and blade disks should be as many as possible when performing impact damage prefabrication; second, the test equipment and test methods should have good versatility for blades and blade disks of different forms.

[0004] A Chinese invention patent with authorization announcement number CN110823724B discloses an experimental device for observing impact damage of aircraft engine blades. In the patent, a rotating blade impact test with a single launch angle adjustment can be achieved through a screw, but this method is only applicable to a single degree of freedom impact of a rotating blade disk, and cannot achieve impacts with higher degrees of freedom. Since the experimental device for observing impact damage of aircraft engine blades lacks protection for non-target positions of the blade disk and control over the rotation of the blade disk, the actual impact damage position is difficult to control.

[0005] A rotating impact test device for a non-full-ring fan blade of an aircraft engine is disclosed in a Chinese invention patent with authorization publication number CN113495002B, and a rotating blade impact test device and a rotating blade impact test method are disclosed in a Chinese invention patent with authorization publication number CN114646445B. In the schemes of the two patents, a rotor test bench is used to drive the blade disk to rotate during the impact test of the rotating blade disk. However, the scheme only conducts tests on the blade disk, is not suitable for the impact test of a single blade, and cannot achieve multi-degree-of-freedom adjustment.

[0006] The Chinese invention patent with the authorization announcement number CN110470446B discloses a test device for the service reliability of composite blades under impact, vibration, and high-temperature excitation. The patent takes into account the influence of the test environment such as temperature and vibration of the blades, but the tail of the barrel of the light gas gun is set on a short fixed plate through a barrel fixing seat, which can only achieve two-degree-of-freedom rotation, and the setting of the complex environment limits the installation of the blade disk and the impact degree-of-freedom adjustment, and cannot be applied to the multi-degree-of-freedom impact damage prefabrication test of the blade disk.

[0007] A Chinese utility model patent with authorization announcement number CN216208272U discloses an aircraft engine blade impact test simulation device; in this patent, three telescopic cylinders are used to drive the adjustment of the angle and height of the blade in a single plane, but its controllable degrees of freedom are still two, and multi-degree-of-freedom adjustment cannot be achieved, and the clamping part cannot be used for blade disk impact tests.

[0008] In summary, there are two main problems with the existing test devices and test methods: First, the foreign object impact test is mainly carried out on rotating blades or stationary blades, and the test devices and test methods used lack versatility and compatibility; second, only a few degrees of freedom of impact can be adjusted, and there is a lack of foreign object impact damage test devices that can adjust more than two degrees of freedom of impact, 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 prefabricated test device and test method that is compatible with single blades and integral blades has important engineering value for engine foreign object impact damage assessment and engine impact resistance performance verification. Summary of the invention

[0009] In view of 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 solves the problems of low versatility and low impact freedom of existing impact damage prefabricated test devices for blades and blisks with complex geometric configurations.

[0010] In the first aspect, in order to achieve the above-mentioned purpose, the technical solution adopted by the present invention is: A test device for prefabricating impact damage of engine blades and blade disks comprises a test bench, a launching device, a fixture assembly and a measuring system; a launching device is arranged at one end of the test bench, a fixture assembly is arranged at the other end of the test bench, and the fixture assembly is located at the projectile outlet of the launching device; blades or blade disks are mounted on the fixture assembly; and a measuring system is arranged on the outer side of the test bench.

[0011] In this scheme, when conducting a damage prefabrication test, the blade or blade disk is installed on the fixture assembly, and a projectile is launched through a launching device to impact the blade or blade disk to cause damage to it; the fixture assembly can be used for clamping and fixing blades or blade disks, and has strong versatility and a wide range of applications; it has a high degree of impact freedom and can be used for different impact postures; the measurement system can collect image information of the blade or blade disk during the impact test, which is convenient for subsequent test result analysis and impact damage prefabrication effect evaluation.

[0012] Furthermore, the launching device includes a high-pressure gas tank, which is fixedly connected to the end of the platform; a pressure gauge, an inflation valve and a launching switch are arranged on the high-pressure gas tank; an air gun barrel is connected to one end of the high-pressure gas tank; the axis of the air gun barrel is parallel to the length direction of the platform; a bullet support for loading the projectile is slidingly arranged inside the air gun barrel; the end of the air gun barrel away from the high-pressure gas tank is the air gun muzzle, and the air gun muzzle is provided with a bullet ejection device.

[0013] In this scheme, the high-pressure gas tank uses air pressure to launch the projectile along the air cannon barrel. When the projectile is launched to the muzzle of the air cannon, the cartridge case used to load the projectile is blocked by the ejection device; the projectile continues to move and impacts the blades or blade discs; the ejection device can prevent the cartridge case from being an unexpected impact object along with the projectile to impact the blades or blade discs.

[0014] Further, the fixture assembly includes a bottom plate, which is rectangular in shape; the bottom plate is horizontally arranged on the upper surface of the stand located on the side of the air cannon muzzle, and a plurality of bottom plate long strip holes are opened on the bottom plate, and each bottom plate long strip hole is perpendicular to the axial direction of the air cannon barrel; a bottom plate bolt is arranged in the bottom plate long strip hole, and the bottom plate bolt passes through the bottom plate long strip hole and is threadedly connected to the stand; A rotating plate is installed on the bottom plate, and the rotating plate is circular in shape; the rotating plate is horizontally arranged on the upper surface of the bottom plate; a plurality of rotating plate circular waist holes arranged in a circular array on the same circumference are opened on the rotating plate; rotating plate bolts are arranged in the rotating plate circular waist holes, and the rotating plate bolts penetrate the rotating plate circular waist holes and are threadedly connected to the bottom plate; A clamping block is connected to the upper surface of the rotating plate, and a rectangular clamping cavity is opened 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 wall of the clamping cavity perpendicular to the axis of the air cannon barrel; a plurality of clamping cavity threaded holes are arranged on the side wall of the clamping block away from the muzzle of the air cannon, and clamping bolts are threadedly connected to the inner threads of the clamping cavity threaded holes, and one end of the clamping bolts located in the clamping cavity abuts against the top block; a blade or a blade disc installation kit for fixing the blade disc is clamped between the top block and the inner wall of the clamping cavity.

[0015] In this scheme, during the process of clamping a single blade, the posture of the blade in the horizontal plane can be changed by adjusting the position of the base plate on the stand and adjusting the rotational orientation of the rotating plate relative to the base plate. The blade can be adjusted in the vertical direction by adjusting the depth of the blade end inserted into the clamping cavity, ultimately achieving multi-degree-of-freedom installation posture adjustment during impact damage prefabrication of a single blade.

[0016] Further, the fixture assembly also includes a blisk mounting kit; The blade disk installation kit includes a vertical plate, which is clamped between the top block and the inner wall of the clamping cavity; a plurality of vertical plate long holes are opened in the vertical direction on the vertical plate, and vertical plate bolts are arranged in the vertical plate long holes; a connecting flange is arranged on the side of the vertical plate close to the muzzle of the air cannon, and the vertical plate bolts penetrate the vertical plate long holes and are threadedly connected to the connecting flange; The connecting flange is connected to a blade disk installation shaft via a connecting shaft. The blade disk installation shaft, the connecting shaft and the connecting flange are coaxial in the horizontal direction. The diameter of the blade disk installation shaft is smaller than the diameter of the connecting shaft, and the blade disk is installed on the blade disk installation shaft.

[0017] In this solution, during the process of clamping the blade disc, the blade disc installation kit can adjust the posture of the blade disc in the horizontal plane by adjusting the position of the base plate on the test bench and adjusting the rotation orientation of the rotating plate relative to the base plate; the blade disc height can be adjusted in the vertical direction by adjusting the vertical height of the connecting flange on the vertical plate, which facilitates flexible and efficient multi-degree-of-freedom foreign object impact testing of the blade disc.

[0018] Furthermore, a baffle plate is provided on the side of the baffle plate close to the muzzle of the air cannon, and the baffle plate is mounted on the baffle plate mounting shaft; a fastening nut is threadedly connected to the side of the baffle plate mounting shaft close to the muzzle of the air cannon; a hollow notch is opened on the baffle plate, and the size of the hollow notch matches the size of the sub-blades on the baffle plate.

[0019] In this solution, a hollow gap is opened on the blade disk baffle, and the position of the hollow gap on the blade disk baffle is adjusted, so that the sub-blades at specific positions on the blade disk can be impacted during static blade disk impact, thereby avoiding damage to other parts of the blade disk.

[0020] Furthermore, the prefabricated test device for impact damage of engine blades and blade disks also includes a protective component; the protective component includes a protective shell and a buffer, and the protective shell covers the fixture component; a channel for the projectile launched by the launch device to pass through is opened 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; The buffer is arranged in the protective shell, and the buffer is located at a side of the clamp assembly away from the launching device; the bottom of the buffer is detachably connected to the upper surface of the stand.

[0021] In this solution, the buffer is used to absorb the remaining kinetic energy after the impact of the projectile, and the protective shell can isolate the space where the fixture assembly is located from the outside world to prevent the projectile from rebounding or generating fragments during the impact, which may pose a threat to the safety of personnel and equipment.

[0022] Furthermore, the prefabricated test device for impact damage of engine blades and blisks also includes a positioning assembly; the positioning assembly includes a fixing seat and a laser locator, the fixing seat is detachably connected to the upper surface of the test bench, and is located on the side of the fixture assembly away from the launching device; the laser locator is installed on the fixing seat, and the laser emission path of the laser locator coincides with the path of the projectile launched by the launching device.

[0023] In this solution, the irradiation point of the laser emitted by the laser locator on the blade or blade disk is the impact position of the projectile. The posture of the blade or blade disk is conveniently adjusted according to the irradiation point of the laser, thereby achieving precise control of the impact position of the blade or blade disk.

[0024] Furthermore, the measuring 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 are both toward the fixture assembly.

[0025] In this scheme, high-speed cameras are used to capture and monitor the impact velocity of the projectile and the process of impacting blades and disks to support subsequent test analysis. Light sources are set to increase the brightness of the test site to ensure that the images captured by the high-speed camera are clear.

[0026] Furthermore, the engine blade and blisk impact damage prefabrication test device also includes a power assist device, which is used to drive the blisk to rotate around the blisk installation axis.

[0027] In a second aspect, the present invention provides a test method for prefabrication of impact damage of engine blades and blade disks based on a test device for prefabrication of impact damage of engine blades and blade disks provided in the first aspect; The impact damage prefabrication test of the blade includes the following steps: Step S1, determining blade impact test parameters: determining the impact parameters and projectile parameters of the blade impact test to be tested according to the impact damage prefabrication test outline of the aero-engine blade; Step S2: Preparation for blade impact test: Install the bottom plate and use bottom plate bolts to fix the bottom plate on the stand, install the rotating plate and use rotating plate bolts to fix the rotating plate on the bottom plate; Make an impact mark on the blade to be tested, and fix the marked end of the blade to be tested in the clamping cavity using a top block and a clamping bolt; Install the positioning assembly, move the bottom plate on the stand along the long hole of the bottom plate, rotate the rotating plate on the bottom plate along the arc waist hole 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 assembly is aligned with the impact mark on the blade to be tested; remove the positioning assembly and install the protection assembly; calibrate the pixel space size of the field of view of the measurement system; Step S3, performing a blade impact test: determining the air pressure value of the high-pressure gas tank in the launch device according to the impact parameters and the projectile parameters; turning on the launch switch, and launching the projectile to impact the marked position on the blade to be tested; Step S4, data acquisition: using a measurement system to collect image data during the blade impact test; Step S5, evaluating the impact damage effect of the blade: comparing the image data before and after the blade impact test, and analyzing the impact damage failure law of the blade; The impact damage prefabrication test of the blade disk includes the following steps: Step T1, determining blade disk impact test parameters: determining the impact parameters and projectile parameters of the blade disk impact test to be tested according to the impact damage prefabrication test outline of the aircraft engine blade disk; Step T2, blade disk impact test preparation: Install the bottom plate and use bottom plate bolts to fix the bottom plate on the stand, install the rotating plate and use rotating plate bolts to fix the rotating plate on the bottom plate; Assemble the blade disk installation kit, thread the blade disk installation shaft, the connecting shaft, and the connecting flange, and use the vertical plate bolts to fix the connecting flange to the vertical plate; Make an impact mark on the blisk to be tested, install the blisk baffle and the blisk with the impact mark on the blisk installation shaft; use the fastening nut to limit the blisk and the blisk baffle; use the top block and the clamping bolt to fix the blisk installation kit with the blisk installed in the clamping cavity of the clamping block; Install the positioning assembly, move the bottom plate on the test bench along the long hole of the bottom plate, rotate the rotating plate on the bottom plate along the arc waist hole of the rotating plate, adjust the vertical position of the connecting flange, rotate the blade disk and the blade disk baffle, align the position to be impacted marked on the blade disk with the hollow notch on the blade disk baffle, and align the laser line emitted by the laser locator in the positioning assembly with the impact mark on the blade disk to be tested; remove the positioning assembly and install the protection assembly; calibrate the pixel space size of the field of view of the measurement system; Step T3, perform a blade disk impact test: determine the air pressure value of the high-pressure gas tank in the launch device according to the impact parameters and the projectile parameters; turn on the launch switch, and launch the projectile to impact the marked position on the blade disk to be tested; Step T4, data acquisition: using a measurement system to collect image data during the blade disk impact test; Step T5, evaluating the impact damage effect of the blade disk: comparing the image data before and after the blade disk impact test, and analyzing the impact damage failure law of the blade disk.

[0028] The beneficial effects of the present invention are: The engine blade and blade disk impact damage prefabrication test device provided by the present invention adopts a fixture assembly to fix the blade or blade disk, which has strong versatility; when the blade impact damage prefabrication test is carried out, the blade is fixed by the fixture assembly, the bottom plate can move along the long strip hole of the bottom plate in the horizontal direction perpendicular to the axis of the air gun barrel, the rotating plate can rotate in the circumferential direction along the multiple rotating plate arc waist holes, and the vertical height of the blade can be adjusted, and finally the installation posture adjustment of the blade in multiple degrees of freedom is realized, meeting the test clamping requirements of the blade under various impact conditions; when the blade disk impact damage prefabrication test is carried out During the test, the brim is fixed with a fixture assembly, and the connecting flange can move along the direction of the multiple vertical plate long holes to adjust the height of the brim in the vertical direction. The brim and the brim baffle can rotate around the brim installation axis, ultimately achieving the brim installation posture adjustment in multiple degrees of freedom and the impact at the specified position on the brim, meeting the test clamping requirements of the brim under various impact conditions; a hollow notch is provided on the brim baffle, and when the impact test is performed on the specified part of the brim, unplanned damage to other parts of the brim can be avoided, thereby improving the effectiveness of the impact test under specific working conditions and saving test costs.

[0029] For the blade impact damage prefabrication test and the brim impact damage prefabrication test, the base plate, base plate bolts, rotating plate, rotating plate bolts, clamping cavity, top block, clamping bolts and other components in the fixture assembly are universal. Therefore, the entire fixture assembly is highly adaptable and can meet the needs of blade and brim impact damage prefabrication tests at the same time, and can achieve rapid switching between blade tests and brim impact damage prefabrication tests; under the framework of the same test outline, blade and brim impact damage prefabrication tests can be carried out simultaneously, thereby improving the versatility and flexibility of the test.

[0030] The positioning component is used to determine the impact position of the projectile on the blade or blisk, guide the adjustment of the fixture component in each degree of freedom, and achieve precise control of the impact position of the blade or blisk. In the protection component, the protective shell is used to isolate the space where the fixture component and the blades and blisks are located from the outside world, and the buffer is used to absorb the residual kinetic energy of the projectile, which can prevent the projectile from rebounding and projectile fragments during the impact process, posing a threat to the safety of personnel and equipment. The measurement system is used to measure the impact velocity of the projectile and record the process of the projectile impacting the blades and blisks, which is convenient for subsequent test result analysis and impact damage prefabrication effect evaluation. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 A schematic diagram of the structure of the test device prefabricated for the impact damage of engine blades and blisks of the present invention; Figure 2 A side view of a test device prefabricated for engine blade and blisk impact damage according to the present invention; Figure 3 It is a schematic diagram of the structure of the clamp assembly clamping the blade in the present invention; Figure 4 It is a schematic diagram of the structure of the clamp assembly clamping the leaf disk in the present invention; Figure 5 A top view of the clamp assembly of the present invention clamping a leaf disk; Figure 6 It is a schematic diagram of the structure of the blade disk baffle in the present invention.

[0032] Reference numerals: 1. Stand; 2. Launching device; 201. High-pressure gas tank; 202. Air pressure gauge; 203. Inflating valve; 204. Launching switch; 205. Air cannon barrel; 206. Air cannon muzzle; 207. De-bulleting device; 3. Clamp assembly; 301. Bottom plate; 302. Long strip hole of bottom plate; 303. Bottom plate bolt; 304. Rotating plate; 305. Arc waist hole of rotating plate; 306. Rotating plate bolt; 307. Clamping block; 309. Clamping bolt; 310. Top block; 311. Vertical plate; 312. Long strip hole of vertical plate; 313. Vertical plate bolt; 314. Blade disk mounting shaft; 315. Connecting shaft; 316. Connecting flange; 318. Fastening nut; 319. Blade disk baffle; 320. Hollow gap; 4. Positioning assembly; 401. Fixing seat; 402. Laser positioner; 501. Protective shell; 502. Buffer; 6. Measuring system; 601. High-speed camera; 602. Light source; 603. Computer; 7. Blade; 8. Blade disk. DETAILED DESCRIPTION

[0033] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments. The specific implementation of the present invention is described below to facilitate the understanding of the present invention by those skilled in the art, but it should be clear that the present invention is not limited to the scope of the specific implementation. For those of ordinary skill in the art, as long as various changes are within the spirit and scope of the present invention defined and determined by the attached claims, these changes are obvious, and all inventions and creations using the concept of the present invention are protected.

[0034] Example 1 like Figure 1 and Figure 2 As shown, this embodiment provides a test device for prefabricating impact damage of engine blades and blade disks. The test device for prefabricating impact damage of engine blades and blade disks can be applied to impact damage prefabrication tests of blades and blade disks with complex geometric configurations, has strong versatility, and can achieve multi-degree-of-freedom adjustment of the impact posture of blades and blade disks; it specifically includes: Bench 1, launching device 2, fixture assembly 3, positioning assembly 4, protection assembly and measuring system 6; 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.

[0035] 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; 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.

[0036] 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.

[0037] 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; like Figure 3 As shown, the bottom plate 301 is rectangular; the bottom plate 301 is horizontally arranged on the upper surface of the stand 1 on the side of the air cannon muzzle 206, and a plurality of bottom plate long holes 302 are opened on the bottom plate 301, each of which is perpendicular to the axial direction of the air cannon barrel 205; a bottom plate bolt 303 is arranged in the bottom plate long hole 302, and the bottom plate bolt 303 passes through the bottom plate long hole 302 and is threadedly connected to the stand 1; the bottom plate 301 is provided with a plurality of bottom plate long holes 302, each of which is perpendicular to the axial direction of the air cannon barrel 205; a bottom plate bolt 303 is arranged in the bottom plate long hole 302, and the bottom plate bolt 303 passes through the bottom plate long hole 302 and is threadedly connected to the stand 1; A rotating plate 304 is installed, and the rotating plate 304 is circular in shape; the rotating plate 304 is horizontally arranged on the upper surface of the base plate 301, and is coaxial with the base plate 301 in the vertical direction; a plurality of rotating plate arc waist holes 305 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 arc waist hole 305, and the rotating plate bolt 306 passes through the rotating plate arc waist hole 305 and is threadedly connected to the base plate 301.

[0038] A clamping block 307 is connected to the upper surface of the rotating plate 304, and a rectangular clamping cavity is opened 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 axial direction of the air cannon barrel 205 is the same as the length of the inner wall of the clamping cavity perpendicular to the axial direction 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 of 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 disk installation kit for fixing the blade disk 8 is clamped between the top block 310 and the inner wall of the clamping cavity.

[0039] When conducting an 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; the posture of the blade 7 in the horizontal plane can be changed by adjusting the position of the base plate 301 on the stand 1 and adjusting the rotation orientation of the rotating plate 304 relative to the base plate 301, and the blade 7 can be adjusted in the vertical direction by adjusting the depth of the blade 7 inserted into the clamping cavity, ultimately achieving multi-degree-of-freedom installation posture adjustment of the single blade 7.

[0040] The blade disk installation kit includes a vertical plate 311, a vertical plate bolt 313, a connecting flange 316, a blade disk installation shaft 314, a connecting shaft 315, a fastening nut 318 and a blade disk baffle 319; like Figure 4 and Figure 5 As shown, a flat plate is vertically connected to the bottom of the vertical plate 311, and the flat plate is accommodated in the clamping cavity. The vertical plate 311 is clamped between the top block 310 and the inner wall of the clamping cavity. A plurality of vertical plate strip holes 312 are provided on the vertical plate 311 in the vertical direction, and vertical plate bolts 313 are arranged in the vertical plate strip holes 312; a connecting flange 316 is provided on the side of the vertical plate 311 close to the air cannon muzzle 206, and the vertical plate bolts 313 penetrate the vertical plate strip holes 312 and are threadedly connected to the connecting flange 316; the connecting flange 316 is connected to the blade disk mounting shaft 314 through the connecting shaft 315, and the blade 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 blade disk mounting shaft 314 is smaller than the diameter of the connecting shaft 315, and the blade disk 8 is installed on the blade disk mounting shaft 314. A blade disk baffle 319 is provided on one side of the blade disk 8 close to the air cannon muzzle 206 , and the blade disk baffle 319 is mounted on the blade disk mounting shaft 314 ; a fastening nut 318 is threadedly connected on one side of the blade disk mounting shaft 314 close to the air cannon muzzle 206 .

[0041] When conducting an impact damage prefabrication test on the entire blade disk 8, the blade disk 8 is installed on the blade disk installation shaft 314; by adjusting the position of the base plate 301 on the test bench 1 and adjusting the rotation orientation of the rotating plate 304 relative to the base plate 301, the posture of the blade disk 8 in the horizontal plane can be adjusted; by adjusting the vertical height of the connecting flange 316 on the vertical plate 311, the height of the blade disk 8 in the vertical direction can be adjusted, which is convenient for flexible and efficient multi-degree-of-freedom foreign object impact testing of the blade disk 8.

[0042] like Figure 6 As shown, a hollow notch 320 is opened on the blade disk baffle 319, and the size of the hollow notch 320 matches the size of the sub-blades on the blade disk 8; by adjusting the position of the hollow notch 320 on the blade disk baffle 319, an impact test is performed on the sub-blades at specific positions on the blade disk 8 when the static blade disk 8 is impacted, thereby avoiding damage to other parts of the blade disk 8.

[0043] The protection assembly includes a protection shell 501 and a buffer 502; The protective shell 501 is a hollow cubic structure, which covers the clamp assembly 3; a channel for the projectile launched by the launch device 2 to pass through is provided on the side of the protective shell 501 close to the air cannon muzzle 206; the material of the protective shell 501 is a transparent material; the buffer 502 is located on the side of the clamp assembly 3 away from the launch device 2, and is used to absorb the residual kinetic energy after the impact of the projectile; the bottom of the buffer 502 is detachably connected to the upper surface of the stand 1; the protective shell 501 can isolate the space where the clamp assembly 3 is located from the outside world, to prevent the projectile from rebounding or generating fragments during the impact, etc., which poses a threat to the safety of personnel and equipment.

[0044] The positioning assembly 4 includes a fixing seat 401 and a laser positioning device 402; The fixing seat 401 is detachably connected to the upper surface of the platform 1 and is located on the side of the fixture assembly 3 away from the launch device 2; a 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 launch device 2. The irradiation point of the laser emitted by the laser locator 402 on the blade 7 or the blade disk 8 is the impact position of the projectile, and the posture of the blade 7 or the blade disk 8 is conveniently adjusted according to the irradiation point of the laser, so as to realize the precise control of the impact position of the blade 7 or the blade disk 8.

[0045] The measuring system 6 includes 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. The high-speed camera 601 is used to shoot and monitor the impact speed of the projectile and the process of impacting the blade 7 and the blade disk 8 to support subsequent test analysis; the light source 602 is set to improve the brightness of the test site to ensure that the image captured by the high-speed camera 601 is clear.

[0046] In this embodiment, when performing the impact damage prefabrication test when the blade disk 8 is in a rotating state, a power auxiliary device may be provided on one side of the blade disk 8 to drive the blade disk 8 to rotate around the blade disk installation shaft 314 .

[0047] Specifically, the auxiliary power unit can be a high-pressure blowing device, which blows high-pressure and high-speed airflow toward the blade disk 8 to push the blade disk 8 to rotate around the blade disk mounting shaft 314, which can meet the needs of performing foreign object impact tests on the rotating blade disk 8.

[0048] Example 2 This embodiment provides a test method for engine blade impact damage prefabrication based on a test device for engine blade and blade disk impact damage prefabrication provided in Embodiment 1; the method comprises the following steps: Step S1, determining the impact test parameters of blade 7: According to the impact damage prefabrication test outline of aircraft engine blade 7, the impact parameters and projectile parameters of blade 7 impact test are determined; the impact parameters include target position and target angle parameters; the projectile parameters include projectile mass, projectile velocity and projectile attitude parameters.

[0049] Step S2, preparation for blade 7 impact test: Install the bottom plate 301 and use the bottom plate bolts 303 to fix the bottom plate 301 on the stand 1, install the rotating plate 304 and use the rotating plate bolts 306 to fix the rotating plate 304 on the bottom plate 301; Make an impact mark on the blade to be tested 7, and use the top block 310 and the clamping bolt 309 to fix the marked end of the blade to be tested 7 in the clamping cavity; Install the positioning component 4, move the base plate 301 on the stand 1 along the long hole 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.

[0050] Step S3, performing an impact test on the blade 7: Determine 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; determine the projectile model, place the projectile in the cartridge, and slide the cartridge into the air gun barrel 205; turn on the launch switch 204, and launch the projectile to impact the blade 7 to be tested.

[0051] Step S4: Data collection: Using the measuring system 6 to collect image data during the impact test of the blade 7; Step S5, evaluating the impact damage effect of the blade 7; The image data of blade 7 before and after the impact test were compared. A microscope and a depth gauge were used to observe the damage morphology and measure the test damage parameters such as damage position, depth and width. Based on the changes in the test damage parameters, impact parameters and projectile parameters, the impact damage failure law of blade 7 was analyzed and summarized.

[0052] Example 3 This embodiment provides a test method for engine blade and blade disk impact damage prefabrication based on a test device for engine blade and blade disk impact damage prefabrication provided in Embodiment 1; the method comprises the following steps: Step T1, determine the impact test parameters of the blade disk 8: According to the impact damage prefabrication test outline of the aircraft engine blade disk 8, the impact parameters and projectile parameters of the blade disk 8 impact test are determined; the impact parameters include target position and target angle parameters; the projectile parameters include projectile mass, projectile velocity, and projectile attitude parameters.

[0053] Step T2, preparation for the impact test of the blade disk 8: Install the bottom plate 301 and use the bottom plate bolts 303 to fix the bottom plate 301 on the stand 1, install the rotating plate 304 and use the rotating plate bolts 306 to fix the rotating plate 304 on the bottom plate 301; 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 the connecting flange 316 is fixedly connected to the vertical plate 311 using the vertical plate bolts 313; Make an impact mark on the blade disk 8 to be tested, 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 component 4, move the base plate 301 on the test bench 1 along the long hole 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, 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 component 4 with the impact mark on the blade disk 8 to be tested; remove the positioning component 4, install the protection component; calibrate the pixel space size of the field of view of the measurement system 6.

[0054] Step T3, performing an impact test on the blade disk 8: Determine 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; determine the projectile model, place the projectile in the cartridge, and slide the cartridge into the air gun barrel 205; turn on the launch switch 204, and launch the projectile to impact the blade disk 8 to be tested.

[0055] Step T4: Data collection: The measuring system 6 is used to collect image data during the impact test of the blade disk 8 .

[0056] Step T5, evaluating the impact damage effect of the blade disk 8; The image data of blade disk 8 before and after the impact test were compared. A microscope and a depth gauge were used to observe the damage morphology and measure the test damage parameters such as damage position, depth and width. Based on the changes in the test damage parameters, impact parameters and projectile parameters, the impact damage failure law of blade disk 8 was analyzed and summarized.

[0057] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in 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).

2. The test device for prefabricating impact damage of engine blades and blisks according to claim 1, characterized in that: 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).

3. The test device for prefabricating impact damage of engine blades and blisks according to claim 2, characterized in that: 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.

4. The test device for prefabricating impact damage of engine blades and blisks according to claim 3, 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).

5. The test device for prefabricating impact damage of engine blades and blisks according to claim 4, 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).

6. The test device for prefabrication of engine blade and blade disk impact damage according to claim 4, 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).

7. The test device for prefabricating impact damage of engine blades and blisks according to claim 4, 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).

8. The test device for prefabrication of engine blade and blade disk impact damage according to claim 4, 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).

9. The test device for prefabrication of engine blade and blade disk impact damage according to claim 4, 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).

10. A test method for the engine blade and blade disk impact damage prefabrication test device based on any one of claims 1 to 8, 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).

Images