Comprehensive mechanical properties testing machine and test method for protective coatings on aeroengine blades based on factors of humidity, heat, salt spray, bird strike and rotation

Abstract

The present invention belongs to the field of coating mechanical property testing, and specifically relates to a comprehensive mechanical property testing machine and testing method for aircraft engine blade protective coatings based on damp heat, salt spray, bird strikes and rotation factors. The technical scheme is as follows: it includes a base, a projectile storage and launch device, a blade-disc rotating device, a vacuum-sealed structure and a damp heat salt spray environment simulation device. The projectile storage and launch device, the blade-disc rotating device, the vacuum-sealed structure and the damp heat salt spray environment simulation device are arranged on the base. The projectile storage and launch device is used to project projectiles to the blades to simulate the state of bird strikes on the blades; the blade-disc rotating device is used to simulate the high-speed rotation state of the blades; the vacuum-sealed structure is used to provide a vacuum state; the damp heat salt spray environment simulation device is used to simulate the damp heat and salt spray environment to corrode and oxidize the blades. The present invention can complete the comprehensive mechanical property testing of aircraft engine blade protective coatings.

Description

Technical Field

[0001] The present invention belongs to the field of coating mechanical property testing, and specifically relates to a comprehensive mechanical property testing machine and a testing method for aircraft engine blade protective coatings based on factors of humidity, heat, salt spray, bird strike and rotation. Background Art

[0002] Aircraft engine blades are one of the most important parts of an engine. They work in extremely harsh environments such as high speed, high temperature, high pressure, and corrosive airflow scouring, and occasionally encounter sudden accidents such as bird strikes. At present, problems such as high-cycle fatigue damage and bird strike impact damage of blades caused by harsh environments in my country's newly developed military high-thrust engines still occur from time to time. Advanced protective coating technology is a key technology with great application prospects, which generally includes thermal barrier coatings, corrosion-resistant coatings, anti-scouring coatings, damping coatings, etc. A large number of studies have shown that metal or composite blades coated with advanced protective coatings can greatly improve the performance and service life of blades because the coatings themselves have excellent mechanical properties and high-temperature protection capabilities, and can generate good adhesion with the substrate material. Therefore, studying and quantitatively evaluating the mechanical properties of protective coatings, especially simulating various service conditions on blade components and scientifically testing their performance, is of great engineering value for my country to prepare coating materials with better performance.

[0003] Although a lot of research has been done on the impact, vibration and dynamic performance of materials and structures under high temperature, there are no reports on the market about comprehensive mechanical testing equipment or devices for protective coatings on aeroengine blades that take into account the influence of multiple factors such as rotation, bird strikes, humidity, heat, and salt spray. For example, patents CN202010345956.0, CN201910334159.X, CN201621290937.8, and CN103604587A respectively provide several design concepts for high-speed rotor test benches, but they are only for high-speed rotating rotor parts, and do not consider the design related to rotating blades, nor can they meet the needs of bird strike tests and humidity, heat, and salt spray environment simulations, and cannot achieve the purpose of comprehensive mechanical performance evaluation of blade structures coated with protective coatings.

[0004] Patents CN200810242905.4, CN201410041022.2, CN201410359334.8, and CN201410418991.5 provide design methods for impact devices, but in principle, they all adopt a free fall method to adjust the impact speed and impact energy by controlling the height of the released object, and the structure is not compact. If you want to obtain a large impact kinetic energy, you can only increase the falling height. It is difficult to make improvements on this basis, for example, it is difficult to combine with a high-speed rotation function.

[0005] Patent CN110345811 discloses an air cannon bird strike test device, which is equipped with a high-pressure gas chamber and an air storage chamber. It can use high-pressure gas to accelerate the projectile or bird simulation object and achieve a high-speed impact effect on the object, but the device is large in size, expensive, and the compressed gas used is also dangerous. Patent CN112747931A introduces a device that uses centrifugal acceleration to launch a projectile, which is more suitable for simulating the impact excitation working condition of the blade component, but there are still certain problems. For example, the launch trigger device of the device is too simple. The slide is pushed out by the switch lever and falls directly into the rotating cavity. The rotor is likely to collide with it when rotating at high speed, causing damage to the equipment and certain dangers. In addition, the openings of the diversion ducts of its storage box and outer shell are large, resulting in a large position deviation of the ejected projectile, which needs to be improved. The centrifugal launcher described in patent CN208653751U requires multiple sensors to work together, with a complex structure and high cost. Moreover, the device shoots at the blades when they are not rotating, which does not conform to the actual working state of the blades. In addition, the device can only launch one projectile or projectile at a time, which is very inefficient. Patent CN110689971A provides a projectile launcher in a rotating state, in which the projectile accelerates from the center of the rotor, is thrown out by the blades, and then moves in a circular motion in the rotating chamber before being launched. Therefore, the device can only be used to launch rigid projectiles, and cannot launch soft projectiles simulating birdshot, and cannot accurately control the direction of projectile launch. In addition, patent CN109540447A discloses a foreign object impact test platform for aircraft engine fan blades. The rotor of the test platform does not operate in a vacuum environment, which will result in its rotation speed not being high enough and the motor power being lost. Moreover, its launcher uses a spring-like energy storage to launch the projectile, and its projectile launch speed is not fast enough, and it is also impossible to effectively launch multiple projectiles. Patent CN114018522A discloses a device for studying the dynamic performance of rotating blades in simulating bird impacts. It uses an air cannon to launch projectiles, so the overall size and weight of the equipment are large, and the blades are installed in a non-full-ring asymmetric manner. It is impossible to guarantee that each shot is an effective shot during the test, and multiple repeated tests are required. Patent CN113495002A discloses a rotating impact test device for non-full-ring blades of aircraft engines. The device limits the shooting position of the projectile through the opening of the baffle plate to reduce the number of test blades. However, because the blades and the baffle plate rotate at high speed, it is impossible to guarantee that the projectile will hit the blade every time it is fired. If it does not hit, the test needs to be repeated until the blade is hit, which undoubtedly increases the test cost. At the same time, the device cannot control the impact on a specified blade, and cannot implement impact tests on multiple blades.

[0006] In addition, there are patents CN201420808043, CN200320122091, CN201120441056, and CN202022126718 that provide different heating devices, but they are not compact enough in structure, have low space utilization, and are mostly used in specialized fields, and have poor integration performance with other functions. Patents CN210015029U and CN104502258A provide two salt spray generating devices, both of which rely on compressed air to blow the salt solution into mist, which cannot meet the requirements for the vacuum test environment. Patents CN209911200U and CN102087301A provide two devices that generate salt spray by pressure, but their structures are not compact enough and have low space utilization. If they are not improved, it is difficult to integrate with other required functions, especially with the bird strike test in a rotating state, which is a difficult design task to complete.

[0007] In summary, although the above patents provide certain technologies or devices for high-speed rotation, impact excitation, high temperature, and salt spray, it is difficult to complete the comprehensive mechanical test and evaluation task of aero-engine blade coatings that takes into account factors such as moisture, heat, salt spray, bird strikes, and rotation by relying on a single technology of the above patents. Without improvement, integration, and innovative design, it is impossible to obtain the equipment or device required for the engineering project to conduct comprehensive mechanical testing of aero-engine blade protective coatings. Summary of the invention

[0008] The present invention provides a comprehensive mechanical properties testing machine and a testing method for aero-engine blade protective coating based on factors such as humidity, heat, salt spray, bird strikes and rotation. The testing machine and a testing method can simultaneously consider factors such as humidity, heat, salt spray, bird strikes and rotation to complete the comprehensive mechanical properties testing of aero-engine blade protective coating.

[0009] The technical solution of the present invention is as follows:

[0010] The invention discloses a comprehensive mechanical performance testing machine for protective coatings of aero-engine blades based on factors of humidity, heat, salt spray, bird strikes and rotation, comprising a base, a projectile storage and launching device, a blade-disc rotating device, a vacuum-sealed structure and a humidity, heat and salt spray environment simulation device, wherein the projectile storage and launching device, the blade-disc rotating device, the vacuum-sealed structure and the humidity, heat and salt spray environment simulation device are arranged on the base, the projectile storage and launching device is used for projecting projectiles to blades to simulate a bird strike state; the blade-disc rotating device is used for simulating a high-speed rotation state of blades; the vacuum-sealed structure is used for providing a vacuum state; and the humidity, heat and salt spray environment simulation device is used for simulating a humidity, heat and salt spray environment to cause corrosion and oxidation to blades.

[0011] Furthermore, in the comprehensive mechanical properties testing machine for aircraft engine blade protective coatings based on moisture, heat, salt spray, bird strikes and rotation factors, the projectile storage and launching device comprises a support seat 1, a main shaft 1, a rotatable quartered bullet storage device, a projectile guide shell and an electromagnetic trigger switch device, the support seat 1 is fixedly mounted on the base, the main shaft 1 is mounted on the support seat 1 through a bearing, the rotatable quartered bullet storage device is mounted on the main shaft 1, the projectile guide shell and the rotatable quartered bullet storage device are coaxial and coplanar, the two bottom feet of the projectile guide shell are fixedly mounted on the base, the electromagnetic trigger switch device is arranged at the top of the projectile guide shell, and the projectile guide shell is provided with a horizontally arranged hollow shooting tube.

[0012] Furthermore, in the comprehensive mechanical properties testing machine for aircraft engine blade protective coating based on humidity, heat, salt spray, bird strike and rotation factors, the rotatable quartered bullet storage device includes a quartered bullet storage rotor, a rotating cover plate, a rotating cover plate limit rod, a rotating cover plate limit rod spring, a cover opening trigger rod, a cover opening trigger rod spring, a trigger rod limit rod and a trigger rod limit rod spring, the quartered bullet storage rotor includes a wheel rim and four projectile storage blades, the wheel rim is fixedly mounted on the main shaft, and the four projectile storage blades are evenly arranged on the wheel rim along the circumferential direction. The upper end of the leeward side of the projectile storage blade is provided with a bullet groove, and the bullet groove is used to place the projectile; a rotating cover plate mounting groove is provided below the bullet groove, and the side of the projectile storage blade is provided with mounting platform 1, mounting platform 2 and mounting platform 3 distributed from bottom to top in sequence; the lower part of the rotating cover plate is a fan-shaped bracket with a weight reduction groove, and the upper part is a cover plate, the side of the cover plate is provided with a positioning platform, the positioning platform is provided with a positioning square hole, and the fan-shaped bracket is provided with a cover plate limiting hole; the lower end of the rotating cover plate is rotatably connected to the leeward side of the projectile storage blade On the wind side, the fan-shaped bracket can be placed in the rotating cover installation groove, and the cover is used to cover the spring groove; the rotating cover limit rod is installed on the mounting platform one by horizontal sliding, and the rotating cover limit rod spring is sleeved on the rotating cover limit rod and is located between the rotating cover limit rod and the mounting platform one, and the rotating cover limit rod is used to insert into the cover limit hole for positioning when the rotating cover is in the open state; the upper end of the opening trigger rod is a square head, the lower part is provided with a trigger inclined platform, and the middle part is provided with a trigger rod limit hole, and the opening trigger rod is installed by vertical sliding. On the second and third mounting platforms, the cover-opening trigger rod spring is sleeved on the cover-opening trigger rod and is located between the cover-opening trigger rod and the second mounting platform, and the square head of the cover-opening trigger rod is inserted into the positioning square hole of the rotating cover plate so that the rotating cover plate covers the spring slot and is in a closed state; the trigger rod limit rod is installed on the second mounting platform in a transverse sliding manner, and the trigger rod limit rod spring is sleeved on the trigger rod limit rod and is located between the trigger rod limit rod and the second mounting platform, and the trigger rod limit rod is inserted into the trigger rod limit hole for positioning when the cover-opening trigger rod is triggered to move downward.

[0013] Furthermore, in the comprehensive mechanical properties testing machine for aircraft engine blade protective coatings based on humidity, heat, salt spray, bird strikes and rotation factors, the electromagnetic trigger switch device includes a bracket, two electromagnets, a latch rod, a latch rod spring, an intervention rod, an intervention rod spring, an intervention rod limit rod and an intervention rod limit rod spring, and the bracket is arranged on the projectile guide shell; the two electromagnets are connected in series, one electromagnet is fixedly mounted on the upper part of the bracket, and the other electromagnet is provided with a support plate; the latch rod is laterally slidably mounted on the upper part of the bracket, the tail end of the latch rod is fixedly mounted on the support plate, the latch rod spring is sleeved on the latch rod and is located between the support plate and the bracket; the upper end of the intervention rod is provided with a latch hole, a middle An intervention rod limiting hole is provided, and the intervention rod is vertically slidably installed on the side of the bracket, and the intervention rod spring is sleeved on the intervention rod and is located between the intervention rod and the bracket; the front end of the latch rod is inserted into the latch hole of the intervention rod, so that the intervention rod is in a closed position; a mounting block is provided on the side of the bracket, and the intervention rod limiting rod is transversely slidably installed on the mounting block, and the intervention rod limiting rod spring is sleeved on the intervention rod limiting rod and is located between the intervention rod limiting rod and the mounting block; the front end of the latch rod withdraws from the latch hole, and during the falling process of the intervention rod, the end of the intervention rod limiting rod is inserted into the intervention rod limiting hole for positioning, and the intervention rod is in an open position, which is used to apply force to the trigger ramp of the cover opening trigger rod.

[0014] Furthermore, the comprehensive mechanical properties testing machine for aircraft engine blade protective coating based on humidity, heat, salt spray, bird strikes and rotation factors, the blade-disk rotating device includes a second main shaft, a second support seat, a disk, a test blade, a speed measuring pressure cover and a speed sensor, the second support seat is fixedly arranged on the base, the base is provided with a support plate, the two ends of the second main shaft are respectively mounted on the second support seat and the support plate through bearings, the disk is fixedly mounted on the second main shaft, the test blade is evenly tenoned on the disk along the circumferential direction, the second main shaft is provided with a speed measuring pressure cover, 8 magnetic steel sheets are evenly arranged on the speed measuring pressure cover along the circumferential direction, the speed sensor is mounted on the support plate, and the probe of the speed sensor is opposite to the speed measuring pressure cover; the blade-disk rotating device is arranged vertically to the projectile storage and launching device, and the hollow shooting tube is opposite to the test blade.

[0015] Furthermore, in the comprehensive mechanical properties testing machine for aircraft engine blade protective coatings based on humidity, heat, salt spray, bird strikes and rotation factors, a speed increaser is fixedly provided on the base, one end of the second main shaft is connected to a high-power variable frequency motor through a flexible coupling, the other end of the second main shaft is connected to the input end of the speed increaser, and the output end of the speed increaser is connected to the first main shaft.

[0016] Furthermore, in the comprehensive mechanical properties testing machine for aircraft engine blade protective coatings based on moisture, heat, salt spray, bird strikes and rotation factors, the vacuum-tight structure includes a movable outer safety protection shell, a vacuum pumping device and a foam silicone sealing ring, slide rails are provided on both sides of the base, rollers are provided on both sides of the bottom of the movable outer safety protection shell, and the rollers are installed in coordination with the slide rails; the movable outer safety protection shell is connected to the vacuum pumping device, and a foam silicone sealing ring is provided between the movable outer safety protection shell and the base and the support plate to ensure the vacuum degree.

[0017] Furthermore, the comprehensive mechanical properties tester for aircraft engine blade protective coating based on humidity, heat, salt spray, bird strike and rotation factors, the humidity, heat and salt spray environment simulation device includes an annular enclosure, a heating tube, a salt spray gas generating box, a salt spray gas pipeline, a waste liquid box and a temperature and humidity sensor, the annular enclosure is fixedly mounted on the base by two legs, the annular enclosure is coaxially arranged with the wheel disc and completely surrounds the test blade; an inner casing is arranged inside the annular enclosure, and the inner casing encloses the test blade; an upper front cover plate and a lower front cover plate are arranged in front of the annular enclosure, a blade installation window and a shooting opening and closing port are arranged on the upper front cover plate, and the shooting opening and closing port corresponds to the position of the hollow shooting tube; the heating tube is installed on the inner wall of the annular enclosure; the salt spray gas generating box is connected to the annular enclosure through a salt spray gas pipeline, and a valve is arranged on the salt spray gas pipeline; a waste liquid hole is opened at the bottom of the annular enclosure, and the waste liquid box is installed below the annular enclosure; a temperature and humidity sensor is arranged on the annular enclosure.

[0018] The comprehensive mechanical properties test method of the protective coating of an aero-engine blade based on humidity, heat, salt spray, bird strike and rotation factors, using the comprehensive mechanical properties test machine of the protective coating of an aero-engine blade based on humidity, heat, salt spray, bird strike and rotation factors, includes the following steps:

[0019] 1) Open the blade installation window, install the test blade coated with the protective coating on the wheel, start the high-power variable frequency motor to slowly rotate the wheel, install the test blades in sequence until the installation is completed, and close the blade installation window;

[0020] 2) The bullet body is loaded into the bullet slot, the rotating cover plate covers the bullet slot, and the square head of the cover opening trigger rod is inserted into the positioning square hole of the rotating cover plate;

[0021] 3) inserting the front end of the latch rod into the latch hole of the intervention rod to energize the electromagnet;

[0022] 4) Close the shooting opening and closing port, move the movable outer safety protection shell to close with the support plate, and set a foamed silicone sealing ring to ensure the vacuum degree;

[0023] 5) Start the high-power variable frequency motor to make the blade-disk rotating device rotate at a low speed, start the salt spray gas generating box and the heating tube, and conduct a wet heat and salt spray environment corrosion test on the test blade protective coating;

[0024] 6) Stop the high-power variable frequency motor, turn off the salt spray gas generating box and the heating tube, remove the movable outer safety protection shell, open the blade installation window, remove the test blade, use a microscope, thickness gauge and other instruments to detect the oxidation and corrosion of the coating of the test blade 93, and record the experimental data;

[0025] 7) Install the test blade back on the wheel disc, close the blade installation window, move the movable outer safety protection shell to close with the support plate, start the vacuum device to vacuum, start the high-power variable frequency motor, increase the speed of the blade-wheel rotating device to a specified value, and maintain it for a period of time; stop the high-power variable frequency motor, remove the movable outer safety protection shell, open the blade installation window, remove the test blade, use a microscope, a thickness gauge, an X-ray scanner and other instruments to check the detachment and peeling of the coating of the test blade 93, and record the experimental data;

[0026] 8) Install the test blade back onto the wheel disc, close the blade installation window, move the movable outer safety protection shell to close with the support plate, start the vacuum device to vacuum, start the high-power variable frequency motor, and when the predetermined speed is reached, open the shooting opening and closing mouth; cut off the power of the electromagnet, the front end of the latch rod withdraws from the latch hole, the intervention rod moves downward under the action of the intervention rod spring and its own weight, the lower end of the intervention rod collides with the trigger ramp of the high-speed rotating cover trigger rod, the square head of the cover trigger rod escapes from the positioning square hole of the rotating cover plate, so that the rotating cover plate is opened, the projectile body detaches from the projectile groove and then flies out horizontally through the hollow shooting tube to impact the test blade;

[0027] 9) Turn off the vacuum device and stop the high-power variable-frequency motor. After the entire testing machine stops completely, remove the test blade and use instruments such as a microscope, a thickness gauge, and an X-ray scanner to detect the condition of the coating of the test blade 93 after the impact, and record experimental data such as the coating crack depth and coating peeling condition.

[0028] Further, in the test method, in step 8), the speed increaser adopts a bevel-cylindrical gear speed increaser, and its speed increase ratio is i, where i is an integer; the speed of the blade-disk rotating device is ω, and since the blade-disk rotating device and the rotatable quartered bullet storage device are connected by the speed increaser, the speed of the rotatable quartered bullet storage device is iω; the firing speed of the projectile is ν, ν=iωR, R is the rotation radius of the projectile; the distance between the release position of the projectile and the hit position of the test blade is d; the phase of the blade-disk rotating device during rotation satisfies the formula α=ωt, where t is the rotation time; under the above conditions, When the projectile is ejected from the rotatable quartered bullet storage device and before the projectile hits the test blade, since the blade-disk rotating device is still rotating, in order to ensure that the projectile can accurately hit the test blade after being ejected, the phase of the rotatable quartered bullet storage device during rotation satisfies the formula β=iωt-ωd / ν, wherein (ωd / ν)=(d / iR) is the phase of the blade-disk rotating device during the period before the projectile misses the test blade after being ejected. It can be seen from the formula that the phase difference is determined by the distance d, the rotation radius R of the projectile and the transmission ratio i of the speed increaser, and is a fixed value that will not change with the rotation speed ω. Therefore, the phase difference can be adjusted during installation. The invention is realized by connecting the blade-disk rotating device and the speed increasing box of the rotatable quartered bullet storage device; the phase of the blade-disk rotating device at a certain moment is detected by the speed sensor, and the computer controls the rotatable quartered bullet storage device to launch the projectile through the information obtained from the speed sensor; since the speed increasing ratio of the speed increasing box is i, when the rotatable quartered bullet storage device rotates one circle, that is, the phase angle changes by Δβ=2π, the rotation phase angle of the blade-disk rotating device changes by Δα=2π / i, so the electromagnet is triggered when the phase of the blade-disk rotating device is α=2nπ, and at this time, the intervention rod is sequentially connected with the rotatable quartered bullet storage device which is rotating at a high speed. The trigger ramps of the cover-opening trigger rods on the four blades of the rotating quartered bullet storage device collide with each other, so that the bullets stored on the four blades are ejected in sequence, and the 1st to 4th test blades can be shot; similarly, when the phase of the blade-disk rotating device is α=2π / i+2nπ, the electromagnet is triggered to shoot the 5th to 8th test blades; when the phase of the blade-disk rotating device is α=2×2π / i+2nπ, the electromagnet is triggered to shoot the 9th to 12th blades, and so on, when the phase of the blade-disk rotating device is α=2π(i-1) / i+2nπ, the electromagnet is triggered to shoot the (4i-3)th to 4ith blades.

[0029] The beneficial effects of the present invention are as follows: the comprehensive mechanical properties testing machine and testing method of aero-engine blade protective coating based on moisture, heat, salt spray, bird strikes and rotation factors provided by the present invention can simultaneously consider moisture, heat, salt spray, bird strikes, rotation and other factors, and complete the comprehensive mechanical properties testing of aero-engine blade protective coating on one machine. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 Schematic diagram of the comprehensive mechanical properties test machine for aircraft engine blade protective coatings based on factors such as humidity, heat, salt spray, bird strikes and rotation;

[0031] Figure 2 This is a cross-sectional view of the middle part of the comprehensive mechanical properties test machine for aircraft engine blade protective coatings based on factors such as humidity, heat, salt spray, bird strikes, and rotation;

[0032] Figure 3 This is a schematic diagram of the missile storage and launching device;

[0033] Figure 4 It is a schematic diagram of a rotatable quartered bullet storage device;

[0034] Figure 5 It is a schematic diagram of the structure of the top of the projectile storage blade;

[0035] Figure 6 This is a schematic diagram of the cover opening trigger lever;

[0036] Figure 7 It is a schematic diagram of an electromagnetic trigger switch device;

[0037] Figure 8 It is a schematic diagram of a blade-disk rotating device;

[0038] Fig. 9 Schematic diagram of the annular enclosure, wherein: (a) shows the blade installation window is not opened, (b) shows the blade installation window is opened;

[0039] Fig.10 It is a cross-sectional view of the internal structure of the annular enclosure cavity;

[0040] Fig.11 Schematic diagram of the process of the intervention rod colliding with the trigger ramp of the cover opening trigger rod that is rotating at high speed to open the rotating cover and release the projectile; wherein: (a) shows that the intervention rod does not collide with the trigger ramp, (b) shows that the intervention rod collides with the trigger ramp, (c) shows that the intervention rod pushes the cover opening trigger rod down to relax the rotating cover, (d) shows that the projectile is separated from the projectile slot after the rotating cover is opened, and (e) shows that the projectile is ejected forward due to inertia. DETAILED DESCRIPTION

[0041] like Figure 1-11As shown, a comprehensive mechanical properties testing machine for aircraft engine blade protective coating based on humidity, salt spray, bird strikes and rotation factors includes a base 2, a projectile storage and launch device 7, a blade-disc rotating device 9, a vacuum-sealed structure and a humidity, salt spray environment simulation device 3. The projectile storage and launch device 7, the blade-disc rotating device 9, the vacuum-sealed structure and the humidity, salt spray environment simulation device 3 are arranged on the base 2. The projectile storage and launch device 7 is used to project projectiles to the blades to simulate the bird strike state; the blade-disc rotating device 9 is used to simulate the high-speed rotation state of the blades; the vacuum-sealed structure is used to provide a vacuum state; the humidity, salt spray environment simulation device 3 is used to simulate the humidity, salt spray environment to corrode and oxidize the blades.

[0042] The projectile storage and launching device 7 includes a support seat 72, a main shaft 1, a rotatable four-part bullet storage device 71, a projectile guide shell 74 and an electromagnetic trigger switch device 73. The support seat 72 is fixedly installed on the base 2, the main shaft 1 is installed on the support seat 72 through a bearing, the rotatable four-part bullet storage device 71 is installed on the main shaft 1, the projectile guide shell 74 is coaxial and coplanar with the rotatable four-part bullet storage device 71, the two bottom feet of the projectile guide shell 74 are fixedly installed on the base 2, the electromagnetic trigger switch device 73 is arranged at the top of the projectile guide shell 74, and the projectile guide shell 74 is provided with a horizontally arranged hollow shooting tube 75.

[0043] The rotatable quartered bullet storage device 71 comprises a quartered bullet storage rotor, a rotating cover plate 712, a rotating cover plate limiting rod 713, a rotating cover plate limiting rod spring 714, a cover opening trigger rod 715, a cover opening trigger rod spring 716, a trigger rod limiting rod 717 and a trigger rod limiting rod spring 718. The quartered bullet storage rotor comprises a wheel rim 719 and four projectile storage blades 711. The wheel rim 719 is fixedly mounted on the main shaft 1. The four projectile storage blades 711 are evenly arranged on the wheel rim 719 along the circumferential direction. The upper end of the leeward side of the projectile storage blade 711 is provided with a bullet groove 7111. The groove 7111 is used to place the projectile 76; a rotating cover plate mounting groove is provided below the projectile groove 7111, and mounting platforms 1, 2 and 3 are arranged on the side of the projectile storage blade 711 from bottom to top; the lower part of the rotating cover plate 712 is a fan-shaped bracket with a weight-reducing groove, and the upper part is a cover plate, a positioning platform is provided on the side of the cover plate, a positioning square hole 7121 is provided on the positioning platform, and a cover plate limiting hole is provided on the fan-shaped bracket; the lower end of the rotating cover plate 712 is rotatably connected to the leeward side of the projectile storage blade 711, and the fan-shaped bracket can be placed in the rotating cover plate mounting groove The cover plate is used to cover the spring groove 7111; the rotating cover plate limiting rod 713 is horizontally slidably installed on the mounting platform one, and the rotating cover plate limiting rod spring 714 is sleeved on the rotating cover plate limiting rod 713 and is located between the rotating cover plate limiting rod 713 and the mounting platform one. The rotating cover plate limiting rod 713 is used to insert into the cover plate limiting hole for positioning when the rotating cover plate 712 is in the open state; the upper end of the opening cover trigger rod 715 is a square head 7151, the lower part is provided with a trigger inclined platform 7152, and the middle part is provided with a trigger rod limiting hole 7153. The opening cover trigger rod 715 is vertically slidably installed on the mounting platform two and the mounting platform three On the top, the cover opening trigger rod spring 716 is sleeved on the cover opening trigger rod 715 and is located between the cover opening trigger rod 715 and the mounting platform two, and the square head 7151 is inserted into the positioning square hole 7121 so that the rotating cover plate 712 covers the spring slot 7111 and is in a closed state; the trigger rod limiting rod 717 is installed on the mounting platform two in a horizontal sliding manner, and the trigger rod limiting rod spring 718 is sleeved on the trigger rod limiting rod 717 and is located between the trigger rod limiting rod 717 and the mounting platform two. When the cover opening trigger rod 715 is triggered to move downward, the trigger rod limiting rod 717 is inserted into the trigger rod limiting hole 7153 for positioning.

[0044] The electromagnetic trigger switch device 73 includes a bracket 731, two electromagnets 734, a latch rod 732, a latch rod spring 733, an intervention rod 735, an intervention rod spring 736, an intervention rod limit rod 737 and an intervention rod limit rod spring 738. The bracket 731 is arranged on the projectile guide shell 74; the two electromagnets 734 are connected in series, one electromagnet 734 is fixedly mounted on the upper part of the bracket 731, and the other electromagnet 734 is provided with a support plate 739; the latch rod 732 is slidably mounted on the upper part of the bracket 731, the tail end of the latch rod 732 is fixedly mounted on the support plate 739, the latch rod spring 733 is sleeved on the latch rod 732 and is located between the support plate 739 and the bracket 731; the upper end of the intervention rod 735 is provided with a latch hole 7351, the middle part is provided with an intervention rod limit hole, The rod 735 is vertically slidably installed on the side of the bracket 731, and the intervention rod spring 736 is sleeved on the intervention rod 736 and is located between the intervention rod 735 and the bracket 731; the front end of the latch rod 732 is inserted into the latch hole 7351, so that the intervention rod 735 is in a closed position; a mounting block is provided on the side of the bracket 731, and the intervention rod limit rod 737 is horizontally slidably installed on the mounting block, and the intervention rod limit rod spring 738 is sleeved on the intervention rod limit rod 737 and is located between the intervention rod limit rod 737 and the mounting block; the front end of the latch rod 732 withdraws from the latch hole 7351, and during the falling process of the intervention rod 735, the end of the intervention rod limit rod 737 is inserted into the intervention rod limit hole for positioning, and the intervention rod 735 is in an open position, which is used to apply force to the trigger ramp 7152 of the cover opening trigger rod 715.

[0045] The triggering of the projectile storage and launching device to complete a launch requires the following actions: the electromagnet 734 is powered off, the front end of the latch rod 732 is withdrawn from the latch hole 73510, the intervention rod 735 moves downward under the action of the intervention rod spring 736 and its own weight, the lower end of the intervention rod 735 collides with the trigger ramp 7152 of the high-speed rotating cover trigger rod 715, the square head 7151 of the high-speed rotating cover trigger rod 715 escapes from the positioning square hole 7121 of the rotating cover 712, and then the intervention rod 735 collides with the rotating cover 712, so that the rotating cover 712 opens, so that the projectile 76 is timely separated from the bullet groove 7111 due to the centrifugal force generated during high-speed rotation, continues to move along the rotation tangent direction, and then flies out horizontally through the hollow shooting tube 75 to accurately hit the test blade 93.

[0046] The blade-disk rotating device 9 includes a main shaft 91, a support seat 4, a disk 92, a test blade 93, a speed measuring pressure cover 94 and a speed sensor. The support seat 4 is fixedly arranged on the base 2, and a support plate 8 is provided on the base 2. The two ends of the main shaft 91 are respectively mounted on the support seat 4 and the support plate 8 through bearings. The disk 92 is fixedly mounted on the main shaft 91. The test blade 93 is evenly tenoned on the disk 92 along the circumferential direction. The main shaft 91 is provided with a speed measuring pressure cover 94. Eight magnetic steel sheets 95 are evenly arranged on the speed measuring pressure cover 94 along the circumferential direction. The speed sensor is mounted on the support plate 8, and the probe of the speed sensor faces the speed measuring pressure cover 94. The blade-disk rotating device 9 is arranged vertically to the projectile storage and launching device 7, and the hollow shooting tube 75 faces the test blade 93.

[0047] A speed increaser 5 is fixedly provided on the base 2, one end of the second main shaft 91 is connected to the high-power variable frequency motor 1 through a flexible coupling 10, the other end of the second main shaft 91 is connected to the input end of the speed increaser 5, and the output end of the speed increaser 5 is connected to the first main shaft.

[0048] The vacuum-tight structure includes a movable outer safety protection shell 6, a vacuum pumping device and a foam silicone sealing ring. Slide rails are provided on both sides of the base 2, and rollers are provided on both sides of the bottom of the movable outer safety protection shell 6. The rollers are installed in coordination with the slide rails. The movable outer safety protection shell 6 is connected to the vacuum pumping device, and a foam silicone sealing ring is provided between the movable outer safety protection shell 6 and the base 2 and the support plate 8 to ensure the vacuum degree.

[0049] The wet and hot salt fog environment simulation device 3 includes an annular enclosure 31, a heating tube 316, a salt fog gas generating box 33, a salt fog gas pipeline 34, a waste liquid box 32 and a temperature and humidity sensor 35. The annular enclosure 31 is fixedly mounted on the base 2 by two legs. The annular enclosure 31 is coaxially arranged with the wheel disc 92 and completely surrounds the test blade 93. An inner casing 315 is arranged inside the annular enclosure 31, and the inner casing 315 encloses the test blade 93. An upper front cover plate 311 and a lower front cover plate 312 are arranged in front of the annular enclosure 31. The cover plate 312 and the upper front cover plate 311 are provided with a blade installation window 313 and a shooting opening and closing port 314, and the shooting opening and closing port 314 corresponds to the position of the hollow shooting tube 75; the heating tube 316 is installed on the inner wall of the annular surrounding cavity 31; the salt spray gas generating box 33 is connected to the annular surrounding cavity 31 through the salt spray gas pipeline 34, and a valve is provided on the salt spray gas pipeline 34; a waste liquid hole is opened at the bottom of the annular surrounding cavity 31, and the waste liquid box 32 is installed below the annular cavity 31; and a temperature and humidity sensor 35 is provided on the annular surrounding cavity 31. The salt spray gas generating box 33 is arranged next to the support plate 8, and the high-power variable frequency motor 1 is installed above the salt spray gas generating box 33.

[0050] The comprehensive mechanical properties test method of the protective coating of an aero-engine blade based on humidity, heat, salt spray, bird strike and rotation factors, using the comprehensive mechanical properties test machine of the protective coating of an aero-engine blade based on humidity, heat, salt spray, bird strike and rotation factors, includes the following steps:

[0051] 1) Open the blade installation window 313, install the test blade 93 coated with the protective coating on the wheel 92, start the high-power variable frequency motor 1 to slowly rotate the wheel 92, install the test blades 93 in sequence until the installation is completed, and close the blade installation window 313;

[0052] 2) Install the bullet body 76 into the bullet slot 7111, cover the bullet slot 7111 with the rotating cover plate 712, and insert the square head 7151 of the cover opening trigger rod 715 into the positioning square hole 7121 of the rotating cover plate 712;

[0053] 3) Insert the front end of the latch rod 732 into the latch hole 7351 of the intervention rod 735 to energize the electromagnet 734;

[0054] 4) Close the shooting opening and closing port 314, move the movable outer safety protection shell 6 to close with the support plate 8, and set a foamed silicone sealing ring to ensure the vacuum degree;

[0055] 5) starting the high-power variable frequency motor 1, causing the blade-disk rotating device 9 to rotate at a low speed, starting the salt spray gas generating box 33 and the heating tube 316, and performing a wet heat and salt spray environment corrosion test on the protective coating of the test blade 93;

[0056] 6) Stop the high-power variable frequency motor 1, turn off the salt spray gas generating box 33 and the heating tube 316, remove the movable outer safety protection shell 6, open the blade installation window 313, remove the test blade 93, use a microscope, a thickness gauge and other instruments to detect the oxidation and corrosion of the coating of the test blade 93, and record the experimental data;

[0057] 7) Install the test blade 93 back on the wheel disc 92, close the blade installation window 313, move the movable outer safety protection shell 6 to close with the support plate 8, start the vacuum device to vacuum, start the high-power variable frequency motor 1, increase the speed of the blade-wheel disc rotating device 9 to a specified value, and maintain it for a period of time; stop the high-power variable frequency motor 1, remove the movable outer safety protection shell 6, open the blade installation window 313, remove the test blade 93, use a microscope, a thickness gauge, an X-ray scanner and other instruments to check the detachment and peeling of the coating of the test blade 93, and record the experimental data;

[0058] 8) Install the test blade 93 back onto the wheel 92, close the blade installation window 313, move the movable outer safety protection shell 6 to close with the support plate 8, start the vacuum device to vacuum, start the high-power variable frequency motor 1, and when the predetermined speed is reached, open the shooting opening and closing port 314; cut off the power of the electromagnet 734, the front end of the latch rod 732 withdraws from the latch hole 73510, and the intervention rod 735 moves downward under the action of the intervention rod spring 736 and its own weight, and the lower end of the intervention rod 735 collides with the trigger ramp 7152 of the lid opening trigger rod 715 that is rotating at a high speed , the square head 7151 of the cover-opening trigger rod 715 escapes from the positioning square hole 7121 of the rotating cover plate 712, and then the intervention rod 735 collides with the rotating cover plate 712, so that the rotating cover plate 712 is opened, and the projectile 76 is separated from the projectile groove 7111 and then flies out horizontally through the hollow shooting tube 75 to impact the test blade 93; the speed increaser 5 adopts a bevel-cylindrical gear speed increaser, and its speed increase ratio is i, i is an integer; the speed of the blade-wheel rotating device 9 is ω, and the speed of the rotatable quartered bullet storage device 7 is iω; the release position of the projectile 76 is consistent with the hit position of the test blade 93 The distance between the positions is d, the firing speed of the projectile 76 is ν=iωR, R is the rotation radius of the projectile; the phase of the blade-disk rotating device 9 during rotation satisfies the formula α=ωt, t is the rotation time; to ensure that the projectile 76 can accurately hit the predetermined test blade 93, the phase of the rotatable quartered bullet storage device 7 during rotation satisfies the formula β=iωt-d / iR; the phase of the blade-disk rotating device 9 at a certain moment is detected by the speed sensor, and the computer controls the rotatable quartered bullet storage device 7 to launch the projectile 76 through the information obtained from the speed sensor; when the blade-disk rotates When the phase of the device 9 is α=2nπ, the electromagnet 734 is triggered, and the test blades 93 No. 1 to 4 are shot; when the phase of the blade-disk rotating device 9 is α=2π / i+2nπ, the electromagnet 734 is triggered, and the test blades 93 No. 5 to 8 are shot; when the phase of the blade-disk rotating device 9 is α=2×2π / i+2nπ, the electromagnet 734 is triggered, and the blades 93 No. 9 to 12 are shot. By analogy, when the phase of the blade-disk rotating device 9 is α=2π(i-1) / i+2nπ, the electromagnet 734 is triggered, and the blades 93 No. (4i-3) to 4i are shot;

[0059] 9) Turn off the vacuum device and stop the high-power variable frequency motor 1. After the entire testing machine stops completely, remove the test blade 93, use a microscope, a thickness gauge, an X-ray scanner and other instruments to detect the condition of the coating of the test blade 93 after the impact, and record experimental data such as the coating crack depth and coating peeling condition.

Claims

1. A comprehensive mechanical properties testing machine for aircraft engine blade protective coatings based on humidity, heat, salt spray, bird strike and rotation factors, characterized by: It comprises a base, a projectile storage and launching device, a blade-wheel disc rotating device, a vacuum-sealed structure and a wet and hot salt spray environment simulation device, wherein the projectile storage and launching device, the blade-wheel disc rotating device, the vacuum-sealed structure and the wet and hot salt spray environment simulation device are arranged on the base, the projectile storage and launching device is used to project projectiles to blades to simulate a bird-hit blade state; the blade-wheel disc rotating device is used to simulate a high-speed rotation state of blades; the vacuum-sealed structure is used to provide a vacuum state; the wet and hot salt spray environment simulation device is used to simulate a wet and hot, salt spray environment to corrode and oxidize the blades; The projectile storage and launching device comprises a support seat 1, a main shaft 1, a rotatable quartered bullet storage device, a projectile guide shell and an electromagnetic trigger switch device, wherein the support seat 1 is fixedly mounted on the base, the main shaft 1 is mounted on the support seat 1 through a bearing, the rotatable quartered bullet storage device is mounted on the main shaft 1, the projectile guide shell and the rotatable quartered bullet storage device are coaxially and coplanarly arranged, the two bottom feet of the projectile guide shell are fixedly mounted on the base, the electromagnetic trigger switch device is arranged on the top of the projectile guide shell, and the projectile guide shell is provided with a horizontally arranged hollow shooting tube; The rotatable four-part ammunition storage device comprises a four-part ammunition storage rotor, a rotating cover plate, a rotating cover plate limiting rod, a rotating cover plate limiting rod spring, a cover opening trigger rod, a cover opening trigger rod spring, a trigger rod limiting rod and a trigger rod limiting rod spring. The four-part ammunition storage rotor comprises a wheel rim and four projectile storage blades. The wheel rim is fixedly mounted on the main shaft 1, and the four projectile storage blades are evenly arranged on the wheel rim along the circumferential direction; an ammunition groove is provided at the upper end of the leeward side of the projectile storage blade, and the ammunition groove is used to place the projectile; a rotating cover plate mounting groove is provided below the ammunition groove, and mounting platforms 1, 2 and 3 are arranged on the side of the projectile storage blade in sequence from bottom to top; the lower part of the rotating cover plate is a fan-shaped bracket with a weight reduction groove, and the upper part is a cover plate, a positioning platform is provided on the side of the cover plate, a positioning square hole is provided on the positioning platform, and a cover plate limiting hole is provided on the fan-shaped bracket; the lower end of the rotating cover plate is rotatably connected to the leeward side of the projectile storage blade, and the fan-shaped bracket can be placed in the rotating cover plate mounting groove. The cover plate is used to cover the spring groove; the rotating cover plate limit rod is installed on the mounting platform one by horizontal sliding; the rotating cover plate limit rod spring is sleeved on the rotating cover plate limit rod and is located between the rotating cover plate limit rod and the mounting platform one; the rotating cover plate limit rod is used to be inserted into the cover plate limit hole for positioning when the rotating cover plate is in the open state; the upper end of the cover opening trigger rod is a square head, the lower part is provided with a trigger inclined platform, and the middle part is provided with a trigger rod limit hole; the cover opening trigger rod is installed on the mounting platform two and the mounting platform three by vertical sliding. The spring of the cover-opening trigger rod is sleeved on the cover-opening trigger rod and is located between the cover-opening trigger rod and the second mounting platform. The square head of the cover-opening trigger rod is inserted into the positioning square hole of the rotating cover plate so that the rotating cover plate covers the elastic groove and is in a closed state. The trigger rod limit rod is installed on the second mounting platform in a transverse sliding manner. The spring of the trigger rod limit rod is sleeved on the trigger rod limit rod and is located between the trigger rod limit rod and the second mounting platform. When the cover-opening trigger rod is triggered to move downward, the trigger rod limit rod is inserted into the trigger rod limit hole for positioning. The electromagnetic trigger switch device includes a bracket, two electromagnets, a latch rod, a latch rod spring, an intervention rod, an intervention rod spring, an intervention rod limit rod and an intervention rod limit rod spring. The bracket is arranged on the projectile guide shell; the two electromagnets are connected in series, one electromagnet is fixedly mounted on the upper part of the bracket, and the other electromagnet is provided with a support plate; the latch rod is horizontally slidably mounted on the upper part of the bracket, the tail end of the latch rod is fixedly mounted on the support plate, the latch rod spring is sleeved on the latch rod and is located between the support plate and the bracket; the upper end of the intervention rod is provided with a latch hole, the middle part is provided with an intervention rod limit hole, and the intervention rod is vertically slidably mounted on the bracket The side of the intervention rod, the intervention rod spring is sleeved on the intervention rod and is located between the intervention rod and the bracket; the front end of the pin rod is inserted into the pin hole of the intervention rod, so that the intervention rod is in a closed position; the side of the bracket is provided with a mounting block, the intervention rod limit rod is laterally slidably installed on the mounting block, the intervention rod limit rod spring is sleeved on the intervention rod limit rod and is located between the intervention rod limit rod and the mounting block; after the electromagnet is powered off, the front end of the pin rod withdraws from the pin hole, and during the falling process of the intervention rod, the end of the intervention rod limit rod is inserted into the intervention rod limit hole for positioning, and the intervention rod is in an open position, which is used to apply force to the trigger ramp of the cover opening trigger rod.

2. The comprehensive mechanical properties testing machine for aircraft engine blade protective coating based on humidity, heat, salt spray, bird strike and rotation factors according to claim 1 is characterized in that: The blade-disk rotating device includes a second main shaft, a second support seat, a disk, a test blade, a speed measuring pressure cover and a speed sensor. The second support seat is fixedly arranged on the base, and a support plate is provided on the base. The two ends of the second main shaft are respectively mounted on the second support seat and the support plate through bearings. The disk is fixedly mounted on the second main shaft, and the test blade is evenly tenoned on the disk along the circumferential direction. A speed measuring pressure cover is provided on the second main shaft, and 8 magnetic steel sheets are evenly arranged on the speed measuring pressure cover along the circumferential direction. The speed sensor is mounted on the support plate, and the probe of the speed sensor faces the speed measuring pressure cover. The blade-disk rotating device is arranged vertically to the projectile storage and launching device, and the hollow shooting tube faces the test blade.

3. The comprehensive mechanical properties testing machine for aircraft engine blade protective coating based on humidity, heat, salt spray, bird strike and rotation factors according to claim 2 is characterized in that: A speed increaser is fixedly provided on the base, one end of the second main shaft is connected to a high-power variable frequency motor through a flexible coupling, the other end of the second main shaft is connected to the input end of the speed increaser, and the output end of the speed increaser is connected to the first main shaft.

4. The comprehensive mechanical properties testing machine for aircraft engine blade protective coating based on humidity, heat, salt spray, bird strike and rotation factors according to claim 3 is characterized in that: The vacuum-tight structure includes a movable outer safety protection shell, a vacuum pumping device and a foam silicone sealing ring. Slide rails are provided on both sides of the base, and rollers are provided on both sides of the bottom of the movable outer safety protection shell. The rollers are installed in coordination with the slide rails. The movable outer safety protection shell is connected to the vacuum pumping device, and a foam silicone sealing ring is provided between the movable outer safety protection shell and the base and the support plate to ensure the vacuum degree.

5. The comprehensive mechanical properties testing machine for aircraft engine blade protective coating based on humidity, heat, salt spray, bird strike and rotation factors according to claim 4 is characterized in that: The humid and hot salt spray environment simulation device comprises an annular enclosure, a heating tube, a salt spray gas generating box, a salt spray gas pipeline, a waste liquid box and a temperature and humidity sensor. The annular enclosure is fixedly mounted on the base through two legs. The annular enclosure is coaxially arranged with the wheel disc and completely surrounds the test blade. An inner casing is arranged inside the annular enclosure, and the inner casing encloses the test blade. An upper front cover plate and a lower front cover plate are arranged in front of the annular enclosure, and a blade installation window and a shooting opening and closing port are arranged on the upper front cover plate, and the shooting opening and closing port corresponds to the position of the hollow shooting tube. The heating tube is installed on the inner wall of the annular enclosure. The salt spray gas generating box is connected to the annular enclosure through a salt spray gas pipeline, and a valve is arranged on the salt spray gas pipeline. A waste liquid hole is opened at the bottom of the annular enclosure, and the waste liquid box is installed below the annular enclosure. A temperature and humidity sensor is arranged on the annular enclosure.

6. A comprehensive mechanical properties test method for aircraft engine blade protective coatings based on humidity, heat, salt spray, bird strike and rotation factors, characterized in that: The comprehensive mechanical properties testing machine for aircraft engine blade protective coating based on humidity, heat, salt spray, bird strike and rotation factors as claimed in claim 5 comprises the following steps: 1) Open the blade installation window, install the test blade coated with the protective coating on the wheel, start the high-power variable frequency motor to slowly rotate the wheel, install the test blades in sequence until the installation is completed, and close the blade installation window; 2) The bullet body is loaded into the bullet slot, the rotating cover plate covers the bullet slot, and the square head of the cover opening trigger rod is inserted into the positioning square hole of the rotating cover plate; 3) inserting the front end of the latch rod into the latch hole of the intervention rod to energize the electromagnet; 4) Close the shooting opening and closing port, move the movable outer safety protection shell to close with the support plate, and set a foamed silicone sealing ring to ensure the vacuum degree; 5) Start the high-power variable frequency motor to make the blade-disk rotating device rotate at a low speed, start the salt spray gas generating box and the heating tube, and conduct a wet heat and salt spray environment corrosion test on the test blade protective coating; 6) Stop the high-power variable frequency motor, turn off the salt spray gas generating box and the heating tube, remove the movable outer safety protection shell, open the blade installation window, remove the test blade, use a microscope, thickness gauge and other instruments to detect the oxidation and corrosion of the coating of the test blade 93, and record the experimental data; 7) Install the test blade back on the wheel disc, close the blade installation window, move the movable outer safety protection shell to close with the support plate, start the vacuum device to vacuum, start the high-power variable frequency motor, increase the speed of the blade-wheel disc rotating device to the specified value, and maintain it for a period of time; Stop the high-power variable frequency motor, remove the movable outer safety protection shell, open the blade installation window, remove the test blade, use a microscope, thickness gauge, X-ray scanner and other instruments to check the coating detachment and peeling of the test blade 93, and record the experimental data; 8) Install the test blade back onto the wheel disc, close the blade installation window, move the movable outer safety protection shell to close with the support plate, start the vacuum device to vacuum, start the high-power variable frequency motor, and when the predetermined speed is reached, open the shooting opening and closing mouth; cut off the power of the electromagnet, the front end of the latch rod withdraws from the latch hole, the intervention rod moves downward under the action of the intervention rod spring and its own weight, the lower end of the intervention rod collides with the trigger ramp of the high-speed rotating cover trigger rod, the square head of the cover trigger rod escapes from the positioning square hole of the rotating cover plate, so that the rotating cover plate is opened, the projectile body detaches from the projectile groove and then flies out horizontally through the hollow shooting tube to impact the test blade; 9) Turn off the vacuum device and stop the high-power variable-frequency motor. After the entire testing machine stops completely, remove the test blade and use instruments such as a microscope, a thickness gauge, and an X-ray scanner to detect the condition of the coating of the test blade 93 after the impact, and record experimental data such as the coating crack depth and coating peeling condition.

7. The test method according to claim 6, characterized in that: In the step 8), the speed increaser adopts a bevel-cylindrical gear speed increaser, and its speed increase ratio is i, where i is an integer; the speed of the blade-disk rotating device is ω, and since the blade-disk rotating device and the rotatable quartered bullet storage device are connected by the speed increaser, the speed of the rotatable quartered bullet storage device is iω; the firing speed of the projectile is ν, ν=iωR, where R is the rotation radius of the projectile; the distance between the release position of the projectile and the hit position of the test blade is d; The phase of the blade-disk rotating device during rotation satisfies the formula α=ωt, where t is the rotation time; under the above conditions, after the projectile is ejected from the rotatable quartered bullet storage device and before the projectile hits the test blade, since the blade-disk rotating device is still rotating, in order to ensure that the projectile can accurately hit the test blade after being ejected, the phase of the rotatable quartered bullet storage device during rotation satisfies the formula β=iωt-ωd / ν, wherein (ωd / ν)=(d / iR) is the phase of the blade-disk rotating device during the period before the projectile misses the test blade after being ejected. It can be seen from the formula that the phase difference is determined by the distance d, the rotation radius R of the projectile and the transmission ratio i of the speed increase box, and is a fixed value that will not change with the rotation speed ω. Therefore, the phase difference can be obtained when the blade-disk rotating device is installed and connected. The computer controls the rotatable quarter-divided bullet storage device to launch the projectile by means of the speed sensor and the speed increase box of the rotatable quarter-divided bullet storage device; the speed increase ratio of the speed increase box is i, when the rotatable quarter-divided bullet storage device rotates one circle, i.e., the phase angle changes by Δβ=2π, the rotation phase angle of the blade-disk rotating device changes by Δα=2π / i, so the electromagnet is triggered when the phase of the blade-disk rotating device is α=2nπ, and at this time, the intervention rod sequentially collides with the trigger ramp of the cover opening trigger rod on the four blades of the rotatable quarter-divided bullet storage device that is rotating at a high speed, so that the projectiles stored on the four blades are sequentially ejected, and the No. 1 to No. 4 test blades can be shot; Similarly, when the phase of the blade-disk rotating device is at α = 2π / i + 2nπ, the electromagnet is triggered to shoot the test blades No. 5 to No. 8; When the phase of the blade-disk rotating device is α=2×2π / i+2nπ, the electromagnet is triggered to shoot blades No. 9 to 12. Similarly, when the phase of the blade-disk rotating device is α=2π(i-1) / i+2nπ, the electromagnet is triggered to shoot blades No. (4i-3) to 4i.

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