CN112730021B - Vibration thermal shock coupling service working condition loading system and method - Google Patents

Abstract

A service condition loading system coupled with vibration, heat and shock, comprising: a clamp (1), provided with a slot for fixing a turbine blade (100); a plurality of slots are provided, so that the turbine blade ( 100) is set at a preset angle with the fixture (1); a vibration loading device is fixedly connected with the fixture (1), and is used to drive the turbine blade (100) on the fixture (1) to vibrate; a spray gun , for injecting high-temperature gas to load thermal shock conditions on the turbine blades (100); the spray gun moving device (3) is used to move the spray gun so that the direction of the spray gun injecting high-temperature gas is consistent with the The airfoil of the turbine blade (100) is vertical. The service condition loading system of the invention can accurately simulate the failure mechanism of the turbine blade under different service environments.

Description

A service condition loading system and method coupled with vibration, heat and shock

technical field

The invention belongs to the field of aero-engines, and in particular relates to a vibration-thermal-shock coupled service condition loading system and method.

Background technique

Aeroengines are known as the "heart" of aircraft and play a decisive role in the development of the aerospace industry. The key parameter of an engine is its thrust-to-weight ratio. Taking the first-generation fighter F86 and the fourth-generation fighter F22 as examples, the thrust-to-weight ratio of the engine has grown from less than 2 to greater than 10. Obviously, increasing the thrust-to-weight ratio of an aeroengine is to improve engine performance. Inevitable measures and inevitable trends of efficiency and efficiency. As the thrust-to-weight ratio increases, the gas inlet temperature of the engine continues to increase. By the time of the fourth-generation fighter jets, the gas inlet temperature of the aero-engine has reached about 1700°C. The significant increase in gas inlet temperature undoubtedly puts forward higher requirements on the hot end parts of the engine, that is, the material of the turbine blade. In order to meet the use requirements of turbine blades, various countries have successively developed a series of super high-temperature alloy materials for turbine blades. At present, the service limit temperature of advanced nickel-based high-temperature single crystals is 1150°C. Obviously, the technology of using high-temperature metal alloy materials alone cannot meet the requirements. An urgent requirement for the rapid development of advanced aero-engines. As early as 1953, the NASA center in the United States proposed the concept of thermal barrier coating, which is to coat high temperature resistant and high heat insulation ceramic materials on the surface of the base alloy to reduce the working temperature of the alloy surface and improve the thermal efficiency of the engine. After this concept was put forward, it immediately attracted the attention of defense departments, universities and research institutions all over the world. In the aero-engine propulsion plans of the United States, Europe and my country, thermal barrier coating technology is listed as the key to high-performance aero-engines. One of the techniques. Moreover, it is believed that the use of thermal barrier coating technology is the most feasible method to greatly increase the operating temperature of aero-engines.

Thermal barrier coatings (TBCs for short) are a layer of ceramic coatings that are deposited on the surface of high temperature resistant metals or superalloys. The thermal barrier coating acts as a thermal insulator for the base material, which reduces the

The bottom temperature enables the devices made of it (such as engine turbine blades) to operate at high temperatures, and has the characteristics of high melting point, low thermal conductivity, corrosion resistance, and thermal shock resistance. During high-temperature service, thermal barrier coatings can protect high-temperature substrates, increase the temperature and thermal efficiency of heat engines, and thus are widely used in the fields of aviation, chemical industry, metallurgy and energy.

However, in the process of actual application, due to the influence of material parameter mismatch and thermal residual stress, high temperature sintering effect of ceramic materials, high temperature interface oxidation, etc., cracks are prone to appear inside the coating, and the thermal barrier coating of turbine blades is in service. It is inevitable that low-frequency or high-frequency vibrations will occur due to factors such as rotor imbalance, meshing instability, and aerodynamic loads. Under high-frequency vibrations, internal cracks in the coating will rapidly expand and peel off. Once the coating peels off, the base metal part will be exposed to high temperature environment, and the consequences are very serious.

Therefore, it is very important to study the failure mechanism of thermal barrier coating caused by blade vibration under high temperature environment. The service time after cracks will promote the development of thermal barrier coatings for aero-engines in my country.

Contents of the invention

(1) Purpose of the invention

The purpose of the present invention is to provide a service condition loading system and method capable of accurately simulating the failure mechanism of turbine blades in different service environments.

(2) Technical solution

In order to solve the above problems, the first aspect of the present invention provides a service condition loading system coupled with vibration, heat and shock, including: a clamp, which is provided with a slot for fixing the turbine blade; the slot is provided with a plurality of, so that the turbine blade and the fixture are set at a preset angle; the vibration loading device is fixedly connected with the fixture, and is used to drive the vibration of the turbine blade on the fixture; the thermal shock loading device is used to inject high temperature The gas is used to apply thermal shock conditions to the turbine blades; the moving device is used to move the thermal shock loading device so that the direction of the thermal shock loading device injecting high-temperature gas is towards the leading edge of the turbine blade.

Optionally, the above-mentioned service condition loading system coupled with vibration, heat and shock further includes: a control device, connected in communication with the vibration loading device, the thermal shock loading device and the mobile device, for controlling the vibration loading device vibration parameters of the thermal shock loading device, and the moving position of the moving device; the thermal shock parameters include flame temperature, flame excitation frequency and heating time.

Optionally, the flame excitation frequency of the thermal shock loading device, the vibration frequency of the vibration loading device and the heating time of the thermal shock loading device satisfy the following relationship:

为火焰额定频率；ΔP为幅值；ω为振动频率；t为升温时间。In the formula, P is the flame excitation frequency;

is the flame rated frequency; ΔP is the amplitude; ω is the vibration frequency; t is the heating time.

Optionally, the vibration frequency and temperature of the turbine blades satisfy the following relationship to simulate thermal shock vibration conditions during takeoff, cruise, and landing of the aeroengine:

f ₁ =k ₁ T ₁ (t)

f ₂ =k ₂ T ₂

f ₃ =k ₃ T ₃ (t)

In the formula, f ₁ , f ₂ , and f ₃ are the vibration frequencies of the turbine blades during take-off, cruise, and landing, respectively; T ₁ , T ₂ , and T ₃ are the surface temperatures of the turbine blades during take-off, cruise, and landing, respectively; k ₁ , k ₂ , k ₃ are constants; t is time.

Optionally, the thermal shock loading device is a spray gun.

Optionally, the moving device includes: a first track; a second track, slidingly connected with the first track, so that the second track slides on the first track; a third track, connected with the The second track is slidably connected, so that the third track slides on the second track; the slider is slidably connected with the third track, so that the slider slides on the third track; The slider is fixedly connected with the thermal shock loading device.

Optionally, the vibration loading device includes: a vibration generating module, used to generate vibration; a support shaft, one end is connected with the vibration generating module, and the other end is connected with the clamp, and is used to connect the vibration generated by the vibration generating module. Vibrations are transmitted to the gripper.

Optionally, the support shaft is set as a hollow shaft, one end communicates with the air compressor, and the other end communicates with the clamp; a communication channel is provided in the clamp; the communication channel communicates with the clamp and the support The joint of the shaft extends to the slot.

Optionally, the above-mentioned vibration-thermal-shock coupled service loading system further includes: a liquid cooling component, configured to liquid-cool the thermal shock loading device.

Optionally, the above-mentioned service condition loading system coupled with vibration, heat and shock also includes: a display module, which is used to display the vibration parameters of the vibration loading device, the flame excitation frequency and heating time of the spray gun, and the The moving position of the spray gun moving device.

The second aspect of the present invention provides a vibration-thermal-shock coupled service condition loading method, using the vibration-thermal-shock coupled service condition loading device as provided in the first aspect of the present invention for loading, including: The turbine blade is fixed on the slot of the fixture; the moving device is activated to move the thermal shock loading device so that the direction of the thermal shock loading device injecting high-temperature gas is towards the leading edge of the turbine blade; the vibration loading device and the thermal shock loading device are activated Loading device.

(3) Beneficial effects

The technical solution of the present invention has the following beneficial technical effects:

The present invention can accurately simulate the vibration thermal shock coupling service environment of the aeroengine turbine blade or the thermal barrier coating of the turbine blade by setting the fixture, the vibration loading device, the thermal shock loading device and the moving device, and can independently control the changing law, thereby simulating The vibration-thermal-shock coupling service environment of aero-engine turbine blade thermal barrier coatings in different stages of take-off, cruise, and landing provides an important experimental platform and reference for correctly understanding the high-temperature vibration damage mechanism of turbine blade thermal barrier coatings and optimizing its design in accordance with.

Description of drawings

Fig. 1 is a structural schematic diagram of a service condition loading system coupled with vibration, heat and shock according to the first embodiment of the present invention;

Fig. 2 is a structural schematic diagram of a form in which the sample is set on the fixture according to the first embodiment of the present invention;

Fig. 3 is a structural schematic diagram of another form in which the sample is set on the fixture according to the first embodiment of the present invention;

4 is a schematic structural diagram of a mobile device according to a first embodiment of the present invention;

Fig. 5 is a schematic diagram of air cooling according to the first embodiment of the present invention.

Reference signs:

1: fixture; 2: thermal shock loading device; 21: kerosene tank; 22: oxygen tank; 23: nitrogen tank; 3: moving device; 31: first track; 32: second track; 33: third track; 34: slider; 35: servo motor; 41: vibration generating module; 42: support shaft; 51: air compressor; 52: chiller; 6: control device.

100: turbine blade;

200: Experimental test bench.

Detailed ways

In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings. It should be understood that these descriptions are exemplary only, and are not intended to limit the scope of the present invention. Also, in the following description, descriptions of well-known structures and techniques are omitted to avoid unnecessarily obscuring the concept of the present invention.

first embodiment

Fig. 1 is a structural schematic diagram of a vibration-thermal-shock coupling service condition loading system according to a first embodiment of the present invention.

As shown in FIG. 1 , this embodiment provides a service condition loading system coupled with vibration, heat and shock, including: a clamp 1 provided with a slot for fixing a turbine blade 100; multiple slots are provided so that The turbine blade 100 is set at a preset angle with the fixture 1; the vibration loading device is fixedly connected with the fixture 1, and is used to drive the vibration of the turbine blade 100 on the fixture 1; 100 loads a thermal shock working condition; the moving device 3 is used to move the thermal shock loading device 2 so that the direction in which the thermal shock loading device 2 injects high-temperature gas is toward the leading edge of the turbine blade 100 . By setting the fixture 1, the vibration loading device, the thermal shock loading device 2 and the moving device 3, it is possible to accurately simulate the vibration-thermal-shock coupling service environment of the aeroengine turbine blade 100 or the thermal barrier coating of the turbine blade 100 and to achieve independent control of the change rule , thereby simulating the vibration-thermal-shock coupling service environment of the aeroengine turbine blade 100 thermal barrier coating in different stages of take-off, cruising, and landing, which provides important information for correctly understanding the high-temperature vibration damage mechanism of the turbine blade 100 thermal barrier coating and optimizing its design. The experimental platform and reference basis.

Wherein, when carrying out the test, the above-mentioned device is placed on the test bench for testing.

Fig. 2 is a structural schematic diagram of a form in which the sample is arranged on the fixture 1 according to the first embodiment of the present invention; Fig. 3 is a structural schematic diagram of another form in which the sample is arranged on the fixture 1 according to the first embodiment of the present invention .

In some embodiments, there are multiple types of slots on the fixture 1, which can be flat, cylindrical, or sample slots in the shape of the tenon of the actual turbine blade 100, and can be loaded with turbine blades 100 of various shapes and sizes. Barrier coating sample or blade; by adjusting the sample clamping method, the angle between the sample and the support shaft 42 connected to the vibration generating module 41 can be realized, the angle is variable from 0° to 180°, and generally adjusted to be horizontal See Figure 3 or see Figure 2 vertically.

In some embodiments, the service condition loading system coupled with vibration, heat and shock further includes: a control device 6, connected in communication with the vibration loading device, the thermal shock loading device 2 and the mobile device 3, for controlling the vibration parameters, thermal The thermal shock parameters of the impact loading device 2 and the moving position of the moving device 3; the thermal shock parameters include flame temperature, flame excitation frequency and heating time. Among them, the flame excitation frequency of the thermal shock loading device 2, the vibration frequency of the vibration loading device and the heating time of the thermal shock loading device 2 satisfy the following relationship:

为火焰额定频率；ΔP为幅值；ω为振动频率；t为升温时间。此外，涡轮叶片100的振动频率与温度满足以下关系，以模拟航空发动机起飞、巡航、降落时的热冲击振动工况：In the formula, P is the flame excitation frequency;

is the flame rated frequency; ΔP is the amplitude; ω is the vibration frequency; t is the heating time. In addition, the vibration frequency and temperature of the turbine blade 100 satisfy the following relationship to simulate the thermal shock vibration conditions of the aero-engine during take-off, cruise, and landing:

f ₁ =k ₁ T ₁ (t)

f ₂ =k ₂ T ₂

f ₃ =k ₃ T ₃ (t)

In the formula, f ₁ , f ₂ , and f ₃ are the vibration frequencies of the turbine blade 100 during take-off, cruise, and landing, respectively; T ₁ , T ₂ , and T ₃ are the surface temperatures of the turbine blade 100 during take-off, cruise, and landing, respectively; k ₁ , k ₂ , k ₃ are constants; t is time. k ₁ , k ₂ , and k ₃ are constants, which are set in the system according to the test conditions. For example, the test target is to heat up to 1200°C in 20S, keep warm for 20S, cool down for 40S, and the final vibration frequency is 3000Hz. At this time, k ₁ is 150, k ₂ is 2.5, and k ₃ is 75. Generally speaking, turbine blades heat up when the aircraft takes off, keep warm during cruise, and cool down during landing.

Among them, flame excitation frequency: refers to the number of times the flame excites the blades per unit time. It is similar to the flame pulse frequency. When the frequency is low, there will be flickering phenomenon. The higher the frequency, the more stable and continuous the flame.

The control device 6 comprises a control panel (see FIG. 1 ).

Among them, on the one hand, the control module can control all the mechanical transmission, experimental parameter collection, adjustment and storage on the test platform, detect the test surface temperature of the sample through the infrared thermometer, and at the same time, according to the feedback temperature value, through the corresponding computer program Control, can realize the vibration frequency of the exciter changes with the change of the temperature value, and can achieve independent control of the change law, so as to simulate the vibration environment of the aero-engine turbine blade 100 thermal barrier coating in different stages of take-off, cruise, and landing; The display module displays all the experimental parameters on the experimental test platform, as well as the experimental process data and real-time video.

In some embodiments, the thermal shock loading device 2 is a spray gun. There are gas channels and water cooling channels inside the spray gun, and the gas channels are connected with liquid and gas storage devices. The liquid storage device can be a kerosene tank. For the accuracy of the test, No. 3 aviation kerosene can be used as the fuel, which is closer to the real service of the aero-engine environment, which heats up and cools down faster to reach the operating temperatures of high-temperature materials in aero-engines. Then the distance from the spray gun to the sample is controlled by the mechanical transmission device, and the heating area and heating temperature can be adjusted conveniently. The characteristics of the high-temperature gas spray gun loading system are: the heating temperature range is wide, and the heating from room temperature to 1700 °C can be realized; the operation It is simple, the test equipment is easy to implement, the test cost is low, and it can be used in coordination with other non-destructive testing equipment. The gas storage device can be an oxygen tank and a nitrogen tank, and the above-mentioned control device 6 can control the heat received by the pattern by controlling the flow rate of kerosene, the ratio of oxygen and nitrogen, the flow rate of oxygen and nitrogen, water cooling parameters, and the distance from the nozzle of the spray gun to the sample. shock. Wherein, the water-cooling channel is provided for water-cooling the spray gun, and the water-cooling channel is connected with the chiller. The water channel in the cooling water tank of the chiller is controlled by the electronic flow valve and enters the cooling channel through the inlet of the cooling channel to cool around the gas spray gun for a circle. After cooling the spray gun, it flows out from the outlet of the cooling channel to circulate between the spray gun and the cooling water tank flow.

FIG. 4 is a schematic structural diagram of the mobile device 3 according to the first embodiment of the present invention.

As shown in Figure 4, in some embodiments, the mobile device 3 includes: a first rail 31; a second rail 32, which is slidably connected with the first rail 31, so that the second rail 32 slides on the first rail 31; The track 33 is slidably connected with the second track 32, so that the third track 33 slides on the second track 32; the slider 34 is slidably connected with the third track 33, so that the slider 34 slides on the third track 33; The slider 34 is fixedly connected with the thermal shock loading device 2 . Optionally, the moving device 3 is also used to move the nozzle of the spray gun to a preset distance from the leading edge of the turbine blade 100, wherein the preset distance is set by the degree of thermal shock required for the test. Further optionally, the moving device 3 includes a servo motor 35, and the servo motor 35 directly controls the movement of the spray gun.

In some embodiments, the vibration loading device includes: a vibration generating module 41 for generating vibration; a support shaft 42, one end is connected with the vibration generating module 41, and the other end is connected with the clamp 1 for transmitting the vibration generated by the vibration generating module 41 Give fixture 1. Wherein, the vibration generating module 41 can be a vibrator. Optionally, the vibration loading module is composed of a vibrator and a fixed shaft, and the vibration direction is vertical, but the vibration of the sample in different directions can be realized according to the different clamping methods of the sample; the vibration loading device is connected below the fixed shaft , the vibration frequency is 0-5000Hz, and the maximum thrust is 6000N; the vibration is generated by the exciter and transmitted to the sample through the support shaft 42 and the sample holder 1 during operation.

Fig. 5 is a schematic diagram of air cooling according to the first embodiment of the present invention.

As shown in Figure 5, in some embodiments, the support shaft 42 is set as a hollow shaft, one end communicates with the air compressor, and the other end communicates with the clamp 1; a communication channel is provided in the clamp 1; The connection extends to the card slot. Among them, the cold air enters from the bottom inlet of the internal cooling channel of the sample, passes through the inner channel of the sample, and is discharged from the outlet of the top cooling gas, cooling a pair of samples; the bottom inlet of the sample corresponds to the position of the cold air outlet of the slot , so that cold air can enter the interior of the sample.

In some embodiments, the above-mentioned vibration thermal shock coupling service condition loading system further includes: a liquid cooling component, which is used for liquid cooling the thermal shock loading device 2 .

Optionally, the above-mentioned service condition loading system coupled with vibration, heat and shock also includes: a display module, which is used to display the vibration parameters of the vibration loading device, the flame excitation frequency and heating time of the spray gun, and the temperature of the spray gun moving device 3 move Place.

The second aspect of the present invention provides a vibration-thermal-shock coupled service condition loading method, using the vibration-thermal-shock coupled service condition loading device provided in the first aspect of the present invention for loading, including: the turbine blade 100 is fixed on the slot of the fixture 1; start the moving device 3 to move the thermal shock loading device 2, so that the direction of the thermal shock loading device 2 spraying high-temperature gas is towards the leading edge of the turbine blade 100; open the vibration loading device and the thermal shock loading device 2.

second embodiment

In some embodiments, the vibration thermal shock coupled service condition loading method uses the vibration thermal shock coupled service condition loading device according to the first embodiment of the present invention for loading, including: fixing the turbine blade 100 to the fixture 1 on the card slot; start the mobile device 3 to move the thermal shock loading device 2, so that the direction of the thermal shock loading device 2 spraying high-temperature gas is towards the leading edge of the turbine blade 100; open the vibration loading device and the thermal shock loading device 2.

In a specific embodiment, the service condition loading method coupled with vibration, heat and shock includes the following steps:

The first step is to prepare the sample: use the electron beam physical vapor deposition spraying process (EB-PVD) to spray the thermal barrier coating heat insulation material on the surface of the hollow turbine blade 100 of the test model. The system composition is: the material of the ceramic layer is zirconia stabilized with 7% yttria, the thickness of the ceramic layer is about 300 μm, the material of the transition layer is NiCrAIY alloy, and the thickness is about 100 μm.

The second step is to simulate the service state of the turbine blade 100: fix the sample of the turbine blade 100 with thermal barrier coating on the fixture 1, fix the fixture 1 on the fixed shaft connected to the vibrator at the same time, adjust the sample angle of support.

The third step is to start the cooling machine and turn on the cooling water switch of the spray gun and the fixed shaft. Start the air compressor, turn on the cooling gas control switch of the internal channel of the turbine blade 100, so that the cooling gas enters the blade from the cooling channel of the turbine blade 100, and is discharged from the outlet of the cooling channel, so that a large temperature gradient is formed from the surface of the ceramic layer to the inner surface of the metal substrate.

The fourth step is to start the vibration loading device, turn on the power button of the vibrator, and when the LINE, COOLING, and OPER on the display panel all turn green, turn the knob to the five o'clock direction. Open the operation panel of the experimental platform, enter the vibration parameter setting interface, and set the control parameters, limit parameters, target spectrum, experiment schedule, vibration mode and miscellaneous items required for the experiment.

The fifth step is to start the kerosene rapid heating device, open the operation panel of the experimental platform, and enter the temperature parameter setting interface, such as heating time, holding time, cooling time, program segment, etc. Adjust the gas flow, and the gas temperature is stable at 1200°C 15 seconds after ignition. By controlling the mechanical transmission switch, the spray gun moves to the vibration station to rapidly heat the surface of the turbine blade 100 at a heating rate of 100°C/s, so that the surface temperature of the sample is stabilized at the required temperature, such as about 1200°C; at the same time, according to the infrared measurement The temperature value fed back by the thermometer, the system will adjust the vibration value of the exciter according to the previously set rules, such as the vibration value will increase correspondingly as the temperature rises.

In the experiment, the experimental parameters such as vibration frequency, vibration mode random vibration, sinusoidal vibration, etc., loading mode dwell, frequency sweep, etc. can be changed, and the failure mechanism and degree of failure of the thermal barrier coating under high temperature vibration and thermal shock can be analyzed. The relationship between these experimental parameters Correlation to find the key parameters affecting the failure of vibration-thermal-shock coupling.

The high-temperature gas spray gun loading system of the test device of the present invention uses No. 3 aviation kerosene as fuel, which is closer to the real service environment of the aero-engine, and has faster heating and cooling rates, which can reach the working temperature of high-temperature materials in the aero-engine. Then the distance from the spray gun to the sample is controlled by the mechanical transmission device, and the heating area and heating temperature can be adjusted conveniently. The characteristics of the high-temperature gas spray gun loading system are: the heating temperature range is wide, and the heating from room temperature to 1700 °C can be realized; the operation It is simple, the test equipment is easy to implement, the test cost is low, and it can be used in coordination with other non-destructive testing equipment.

The sample clamping device of the test device of the present invention comprises a fixed shaft, a sample clamp 1 and a turbine blade 100 directly fixed on the sample clamp 1 or a slot of the flat clamp 1 . When simulating the experiment of the thermal barrier coating of the aeroengine turbine blade 100, the sample holder 1 is engraved with a flat plate, a cylindrical sample groove, and a tenon shape of the actual turbine blade 100, which can be loaded with various shapes and sizes of thermal barriers. Coated sample or blade; by adjusting the sample clamping method, the angle between the thermal barrier coating sample and the fixed axis connected to the vibrator can be realized, and the angle can be horizontal or vertical.

The test device of the present invention has two different types of cooling devices, one is to cool the cooling system of the fixedly connected shaft by means of cooling water; the other is to cool the turbine blade 100 sample with a cooling channel, through Cooling by means of cooling air. For example, taking a hollow turbine blade 100 sample with a thermal barrier coating as an example, the cooling air enters the interior of the turbine blade 100 through the cooling passage for cooling to ensure that the internal temperature of the blade is maintained at the set temperature, thereby realizing the transition from the coating surface to the interior of the blade. form a temperature gradient. The cooling air flow is controlled and measured by an electronic flow valve.

The test control system of the test device of the present invention includes a test control module and a display module; the control module can control all the mechanical transmissions on the test platform, the collection, adjustment and storage of experimental parameters, and adjust the test temperature of the sample through the infrared thermometer At the same time, according to the feedback temperature value, through the corresponding computer program control, the vibration frequency of the exciter can be changed with the change of the temperature value, and the change law can be controlled independently, thereby simulating the thermal barrier coating of the aeroengine turbine blade 100 The vibration environment in different stages of take-off, cruising, and landing; the display module displays all the experimental parameters and the experimental process on the test platform.

It should be understood that the above specific embodiments of the present invention are only used to illustrate or explain the principles of the present invention, and not to limit the present invention. Therefore, any modification, equivalent replacement, improvement, etc. made without departing from the spirit and scope of the present invention shall fall within the protection scope of the present invention. Furthermore, it is intended that the appended claims of the present invention embrace all changes and modifications that come within the scope and metesques of the appended claims, or equivalents of such scope and metes and bounds.

Claims (7)

1. A vibration thermal shock coupling service working condition loading system is characterized by comprising:

the fixture (1) is provided with a clamping groove and used for fixing the turbine blade (100); the clamping grooves are arranged in a plurality of numbers so that the turbine blade (100) and the clamp (1) are arranged at a preset angle;

the vibration loading device is fixedly connected with the clamp (1) and is used for driving the turbine blade (100) on the clamp (1) to vibrate;

the thermal shock loading device (2) is used for injecting high-temperature gas so as to load thermal shock working conditions on the turbine blade (100);

moving means (3) for moving the thermal shock loading means (2) such that the thermal shock loading means (2) jets a direction of the high temperature gas towards the leading edge of the turbine blade (100);

the control device (6) is in communication connection with the vibration loading device, the thermal shock loading device (2) and the moving device (3) and is used for controlling the vibration parameters of the vibration loading device, the thermal shock parameters of the thermal shock loading device (2) and the moving position of the moving device (3);

the thermal shock parameters comprise flame temperature, flame excitation frequency and heating time;

the flame excitation frequency of the thermal shock loading device (2), the vibration frequency of the vibration loading device and the temperature rise time of the thermal shock loading device (2) satisfy the following relations:

wherein, P is the flame excitation frequency;

the rated frequency of the flame; Δ P is the amplitude; omega is the vibration frequency; t is the temperature rise time;

the vibration frequency and the temperature of the turbine blade (100) meet the following relation so as to simulate thermal shock vibration working conditions of the aircraft engine during takeoff, cruising and landing:

f ₁ ＝k ₁ T ₁ (t)

f ₂ ＝k ₂ T ₂

f ₃ ＝k ₃ T ₃ (t)

in the formula, f ₁ ，f ₂ ，f ₃ The vibration frequencies of the turbine blade (100) during take-off, cruise and landing respectively; t is a unit of ₁ ，T ₂ ，T ₃ The surface temperatures of the turbine blades (100) during take-off, cruise and landing respectively; k is a radical of formula ₁ ，k ₂ ，k ₃ Is a constant; t is time.

2. The in-service condition loading system for the coupling of the vibratory thermal shock according to claim 1,

the thermal shock loading device (2) is a spray gun.

3. The service condition loading system for the coupling of the vibratory thermal shock according to claim 1, wherein the moving device (3) comprises:

a first rail (31);

a second rail (32) slidably connected to the first rail (31) such that the second rail (32) slides on the first rail (31);

a third rail (33) slidably connected to the second rail (32) such that the third rail (33) slides on the second rail (32);

a slide (34) slidably connected to the third rail (33) such that the slide (34) slides on the third rail (33); the sliding block (34) is fixedly connected with the thermal shock loading device (2).

4. The system of claim 1, wherein the vibration loading device comprises:

a vibration generation module (41) for generating vibrations;

and the supporting shaft (42) is connected with the vibration generation module (41) at one end and connected with the clamp (1) at the other end, and is used for transmitting the vibration generated by the vibration generation module (41) to the clamp (1).

5. The service condition loading system of the vibration thermal shock coupling according to claim 4,

the supporting shaft (42) is a hollow shaft, one end of the supporting shaft is communicated with an air compressor, and the other end of the supporting shaft is communicated to the clamp (1);

a communication channel is arranged in the clamp (1);

the communication channel extends from the joint of the clamp (1) and the supporting shaft (42) to the clamping groove.

6. The service condition loading system for the coupling of the vibration and thermal shock according to claim 1, further comprising:

and the liquid cooling component is used for carrying out liquid cooling on the thermal shock loading device (2).

7. A loading method for the service condition of the vibration thermal shock coupling is characterized in that the loading is carried out by using the service condition loading device of the vibration thermal shock coupling as claimed in any one of claims 1 to 6, and comprises the following steps:

fixing the turbine blade (100) on a clamping groove of the clamp (1);

starting a moving device (3) to move a thermal shock loading device (2), so that the thermal shock loading device (2) jets high-temperature gas in a direction towards the front edge of the turbine blade (100);

and starting the vibration loading device and the thermal shock loading device (2).

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