Simulation experiment system for working condition of thermal barrier coating of aero-engine

Abstract

The invention relates to the technical field of aero-engines, in particular to an aero-engine thermal barrier coating working condition simulation experiment system which comprises a high-temperature thermal cycle module, a high-speed airflow scouring module, a high-pressure loading module, an atmosphere control module and a data monitoring and collecting module. The high-temperature thermal cycle module is used for realizing rapid heating and cooling so as to simulate a thermal environment; the high-speed airflow scouring module is used for generating high-speed airflow to simulate gas scouring; the coating performance can be accurately evaluated through the multi-working-condition high-precision simulation capability, research and development personnel can be assisted to optimize components and structures, coating defects and weak points can be rapidly and accurately found through strict working condition simulation in the aspect of quality detection, the product quality is guaranteed, the defective rate is reduced, and the method has good application prospects from cost benefit consideration. The test frequency and the part replacement cost caused by the coating problem in engine research and development are reduced, the research and development period is shortened, the performance and reliability of the aero-engine are greatly improved, the development of the aerospace industry is powerfully promoted, and a solid foundation is laid for advanced engine research and development.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and particularly to a simulation experiment system for the working conditions of aeroengine thermal barrier coatings. Background Technique

[0002] In the field of aeroengines, improving thermal efficiency and reliability is the core pursuit. High-temperature components of engines face extremely harsh working conditions, and thermal barrier coatings have emerged and become a key technology. Traditional engine materials are limited in performance at high temperatures. Thermal barrier coatings can effectively insulate heat, reduce the temperature of components, reduce the amount of cooling air, and improve combustion efficiency and thrust-to-weight ratio. However, the working conditions of aeroengines are complex. For example, the temperature in the combustion chamber exceeds 1500 °C, and there is high-speed gas (about 500 m / s) erosion and a pressure of several MPa at the turbine. Moreover, the thermal cycle is frequent, and the oxygen content and humidity in the atmosphere vary, resulting in the easy failure of thermal barrier coatings, which seriously threatens the safety and life of engines. Previously, most experimental systems focused on simulating single or simple combined working conditions and were difficult to accurately reflect the actual service environment and could not meet the R & D requirements of thermal barrier coatings. Therefore, a simulation experiment system for the working conditions of aeroengine thermal barrier coatings is proposed. Summary of the Invention

[0003] In view of this, the present invention provides a simulation experiment system for the working conditions of aeroengine thermal barrier coatings to solve or alleviate the technical problems existing in the prior art and at least provide a beneficial option.

[0004] The technical solution of the present invention is realized as follows: A simulation experiment system for the working conditions of aeroengine thermal barrier coatings includes a high-temperature thermal cycle module, a high-speed gas flow erosion module, a high-pressure loading module, an atmosphere control module, and a data monitoring and acquisition module;

[0005] The high-temperature thermal cycle module realizes rapid heating and cooling to simulate the thermal environment;

[0006] The high-speed gas flow erosion module generates high-speed gas flow to simulate gas erosion;

[0007] The high-pressure loading module applies pressure to simulate mechanical stress;

[0008] The atmosphere control module regulates the atmosphere to simulate the gas environment in the engine;

[0009] The data monitoring and acquisition module monitors parameters in real time to provide data support for research.

[0010] Further preferably, the high-temperature thermal cycle module includes a heating sub-module and a temperature control sub-module. The heating sub-module adopts a composite heating technology combining induction heating and resistance heating to create a fast and stable heating and cooling environment in a high-vacuum chamber. The induction coil is customized according to the geometry of the specimen and surrounds the specimen. An induced current is generated inside the specimen through an alternating magnetic field to achieve rapid heating. At the same time, resistance heating wires are reasonably arranged in the chamber for precise temperature compensation and fine-tuning on the basis of induction heating to ensure uniform heating of the specimen. The temperature control sub-module uses an advanced PID temperature controller and a high-precision temperature sensor to achieve precise temperature control. When simulating the working conditions of the thermal barrier coating in an aero-engine combustion chamber, the system can quickly raise the specimen from room temperature to 1200 °C within 10 - 30 seconds, and the cooling rate can reach 50 - 100 °C / second. After multiple thermal cycle tests, the microstructure of the coating is analyzed and it is found that even after more than 1000 thermal cycles, the crystal structure of the coating still remains relatively intact, and the bonding strength between the coating and the substrate only decreases by about 5%, effectively avoiding the cracking and spalling phenomena of the coating caused by thermal stress, providing key experimental conditions for in-depth study of the thermal fatigue performance of the coating.

[0011] Further preferably, the high-speed gas flow scouring module includes a gas flow generation sub-module and a scouring experiment and coating erosion analysis sub-module. The gas flow generation sub-module uses a design combining a high-pressure gas drive system and a Laval nozzle to generate a high-speed gas flow with a speed of up to 0.5 - 2.0 Ma. The high-pressure gas first accumulates energy in the drive chamber and then is accelerated through the special structure of the Laval nozzle, so that the gas flow reaches the required high-speed state at the nozzle outlet. In order to ensure the uniformity of the gas flow, a numerical simulation optimization technology is adopted in the nozzle design process to finely design the internal flow channel of the nozzle, so that the deviation of the gas flow velocity uniformity at the outlet is controlled within ±5%. In the scouring experiment and coating erosion analysis sub-module, the distance between the nozzle outlet and the specimen is accurately set at 50 - 100 mm to ensure that the high-speed gas flow can scour and simulate the coating at an appropriate angle and intensity.

[0012] Further preferably, the high-pressure loading module includes a loading system sub-module and a thermal-mechanical coupling experiment sub-module. The loading system sub-module is based on a hydraulic servo system and a customized fixture design, and can apply a pressure of 50-200 MPa to the specimen. The hydraulic servo system drives the loading piston to apply a stable pressure to the specimen by precisely controlling the pressure and flow rate of the hydraulic oil. The customized fixture is designed according to specimens of different shapes and sizes to ensure that the pressure can be evenly distributed on the surface of the specimen and avoid causing additional damage to the specimen during the loading process. The thermal-mechanical coupling experiment sub-module, when a pressure of 100 MPa is applied to the coating and high-temperature heating is carried out simultaneously, it is found by measuring the hardness of the coating through nano-indentation technology that the hardness of the coating has increased by about 10%-15% compared with when no pressure is applied.

[0013] Further preferably, the atmosphere control module includes a gas regulation sub-module and an oxidation experiment and coating antioxidant performance evaluation sub-module. The gas regulation sub-module can precisely regulate the atmosphere environment in the chamber with the help of a high-precision gas flow controller and an advanced vacuum system. The gas flow controller can precisely control the flow rates of gases such as oxygen, nitrogen, water vapor, and simulated aviation fuel combustion products, and achieve precise regulation of the oxygen content (5%-20%), humidity (0-10%RH), and gas composition in the chamber. For the oxidation experiment and coating antioxidant performance evaluation, the oxidation experiment and coating antioxidant performance evaluation sub-module sets the oxygen content in the chamber to 10%, maintains the temperature at 1000°C, and after 100 hours of oxidation treatment, it is found by measuring the oxidation weight gain of the coating through thermogravimetric analysis that the oxidation weight gain rate of the coating is about 0.1-0.3 mg / cm 2 ·h.

[0014] Further preferably, the data monitoring and acquisition module includes a monitoring sub-module and a data acquisition and analysis sub-module. The monitoring sub-module integrates advanced monitoring devices such as an infrared thermal imager, high-temperature strain gauges, high-precision pressure sensors, and laser displacement sensors. The infrared thermal imager can non-contactedly monitor the temperature field distribution on the coating surface in real time, with a temperature resolution of up to 0.1 °C, providing intuitive data for studying the temperature changes of the coating during thermal cycling and thermal shock. The high-temperature strain gauges are directly pasted on the coating surface or the specimen substrate to measure the strain of the coating during stress and temperature changes, with a measurement accuracy of up to ±10 με. The pressure sensors are installed in the loading system and the chamber to monitor the magnitude and changes of the pressure in real time, with an accuracy of up to ±2 MPa. The laser displacement sensor accurately monitors the surface displacement of the coating during the experiment by emitting a laser beam and measuring the displacement change of the reflected light, with an accuracy of up to ±0.01 mm. The data acquisition and analysis sub-module transmits the data collected by all monitoring devices to the computer through a high-speed data acquisition card and performs real-time analysis and processing by specially developed data processing software. The data processing software adopts advanced signal processing algorithms and data analysis models, capable of performing fusion analysis on multi-source data, providing strong technical support for the maintenance of aero-engines and the life prediction of thermal barrier coatings.

[0015] Further preferably, when studying the heat insulation performance of the thermal barrier coating, the calculation formula for the heat flux is as follows:

[0016]

[0017] Where q is the heat flux (W / m 2 ), k is the thermal conductivity (W / (m·K)), is the temperature gradient (K / m). In the experimental system, by measuring the temperature difference on both sides of the coating and knowing the coating thickness, the heat flux can be calculated to evaluate the heat insulation effect of the coating. For example, in the high-temperature thermal cycling module, when the temperature on one side of the coating is T 1 = 1200 °C (1473 K), and the temperature on the other side is T 2 = 800 °C (1073 K), the coating thickness x = 0.5 mm = 0.0005 m. If the known thermal conductivity of the coating k = 1.5 W / (m·K), then the heat flux is:

[0018]

[0019] Further preferably, in the high-altitude airflow erosion module, the following formula is used to estimate the impact force of the airflow on the coating:

[0020]

[0021] In the case of horizontal erosion, h remains unchanged, and it can be simplified to:

[0022]

[0023] Among them, p is the static pressure (Pa), ρ is the gas density (kg / m 3 ), and v is the gas flow velocity (m / s). For example, when the gas flow velocity v 1 = 500 m / s and the gas density ρ = 1.2 kg / m 3 , assuming the static pressure p 1 = 10 5 Pa, when the gas flow velocity at a certain point on the coating surface drops to v 2 = 300 m / s, the pressure change at this point is:

[0024]

[0025] The pressure difference Δp = p 2 - p 1 = 96000 Pa. The impact force can be calculated based on the pressure difference and the coating area.

[0026] Due to the adoption of the above technical solutions in the embodiments of the present invention, it has the following advantages:

[0027] The multi-condition high-precision simulation ability of the present invention can accurately evaluate the coating performance, helping R & D personnel optimize the composition and structure. In terms of quality inspection, strictly simulating the working conditions can quickly and accurately detect coating defects and weak points, ensuring product quality and reducing the defective rate. Considering the cost-benefit, it reduces the number of tests and component replacement costs caused by coating problems in engine R & D, shortens the R & D cycle, greatly improves the performance and reliability of aero-engines, strongly promotes the development of the aerospace industry, and lays a solid foundation for the development of advanced engines.

[0028] The above summary is only for the purpose of the specification and is not intended to be limiting in any way. In addition to the illustrative aspects, embodiments, and features described above, further aspects, embodiments, and features of the present invention will become apparent by reference to the drawings and the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0030] Figure 1 It is the system flow chart of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0031] In the following text, only some exemplary embodiments are briefly described. As those skilled in the art can recognize, the described embodiments can be modified in various different ways without departing from the spirit or scope of the present invention. Therefore, the accompanying drawings and the description are considered to be exemplary in nature rather than restrictive.

[0032] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0033] As Figure 1 shown, the embodiments of the present invention provide a simulation experimental system for the working conditions of thermal barrier coatings of aero-engines, including a high-temperature thermal cycle module, a high-speed air flow scouring module, a high-pressure loading module, an atmosphere control module, and a data monitoring and acquisition module;

[0034] The high-temperature thermal cycle module realizes rapid heating and cooling to simulate the thermal environment;

[0035] The high-speed air flow scouring module generates high-speed air flow to simulate the gas scouring;

[0036] The high-pressure loading module applies pressure to simulate mechanical stress;

[0037] The atmosphere control module regulates the atmosphere to simulate the gas environment inside the engine;

[0038] The data monitoring and acquisition module monitors the parameters in real time to provide data support for research.

[0039] In one embodiment, the high-temperature thermal cycle module includes a heating sub-module and a temperature control sub-module. The heating sub-module adopts a composite heating technology combining induction heating and resistance heating to create a rapid and stable heating and cooling environment in a high-vacuum chamber. The induction coil is customized according to the geometric shape of the specimen and is wound around the specimen. An induced current is generated inside the specimen through an alternating magnetic field to achieve rapid heating. At the same time, resistance heating wires are reasonably arranged in the chamber for precise temperature compensation and fine-tuning on the basis of induction heating to ensure uniform heating of the specimen. The temperature control sub-module uses an advanced PID temperature controller and a high-precision temperature sensor to achieve precise control of the temperature. When simulating the working conditions of the thermal barrier coating in the combustion chamber of an aero-engine, the system can rapidly raise the temperature of the specimen from room temperature to 1200 °C within 10 - 30 seconds, and the cooling rate can reach 50 - 100 °C / second. After multiple thermal cycle tests, the microstructure of the coating is analyzed and it is found that even after more than 1000 thermal cycles, the crystal structure of the coating still remains relatively intact, and the bonding strength between the coating and the substrate only decreases by about 5%, effectively avoiding the cracking and spalling phenomena of the coating caused by thermal stress, providing key experimental conditions for in-depth research on the thermal fatigue performance of the coating.

[0040] In one embodiment, the high-speed air flow scouring module includes an air flow generation sub-module and a scouring experiment and coating erosion analysis sub-module. The air flow generation sub-module combines a high-pressure gas drive system with a Laval nozzle design to generate a high-speed air flow with a speed of up to 0.5 - 2.0 Ma. The high-pressure gas first accumulates energy in the drive chamber and then is accelerated through the special structure of the Laval nozzle, enabling the air flow to reach the required high-speed state at the nozzle outlet. To ensure the uniformity of the air flow, numerical simulation optimization technology is adopted in the nozzle design process to finely design the internal flow channel of the nozzle, so that the velocity uniformity deviation of the air flow at the outlet is controlled within ±5%. For the scouring experiment and coating erosion analysis sub-module, the distance between the nozzle outlet and the specimen is precisely set at 50 - 100 mm to ensure that the high-speed air flow can scour the coating at an appropriate angle and intensity for simulation.

[0041] In one embodiment, the high-pressure loading module includes a loading system sub-module and a thermal-mechanical coupling experiment sub-module. The loading system sub-module is based on a hydraulic servo system and a customized fixture design, and can apply a pressure of 50 - 200 MPa to the specimen. The hydraulic servo system drives the loading piston to apply a stable pressure to the specimen by precisely controlling the pressure and flow rate of the hydraulic oil. The customized fixture is designed according to specimens of different shapes and sizes to ensure that the pressure can be evenly distributed on the specimen surface while avoiding causing additional damage to the specimen during the loading process. For the thermal-mechanical coupling experiment sub-module, when a pressure of 100 MPa is applied to the coating and high-temperature heating is carried out simultaneously, it is found by measuring the hardness of the coating through nanoindentation technology that the hardness of the coating has increased by about 10% - 15% compared with when no pressure is applied.

[0042] In one embodiment, the atmosphere control module includes a gas regulation sub-module and an oxidation experiment and coating oxidation resistance evaluation sub-module. The gas regulation sub-module can precisely regulate the atmosphere environment in the chamber with the help of a high-precision gas flow controller and an advanced vacuum system. The gas flow controller can precisely control the flow rates of gases such as oxygen, nitrogen, water vapor, and simulated aviation fuel combustion products, realizing precise regulation of the oxygen content (5% - 20%), humidity (0 - 10% RH), and gas composition in the chamber. For the oxidation experiment and coating oxidation resistance evaluation sub-module, when the oxygen content in the chamber is set to 10% and the temperature is maintained at 1000 °C, after 100 hours of oxidation treatment, it is found by measuring the oxidation weight gain of the coating through thermogravimetric analysis that the oxidation weight gain rate of the coating is about 0.1 - 0.3 mg / cm 2 ·h.

[0043] In one embodiment, the data monitoring and acquisition module includes a monitoring sub-module and a data acquisition and analysis sub-module. The monitoring sub-module integrates advanced monitoring devices such as an infrared thermal imager, high-temperature strain gauges, high-precision pressure sensors, and laser displacement sensors. The infrared thermal imager can non-contactly monitor the temperature field distribution on the surface of the coating in real time, with a temperature resolution of up to 0.1 °C, providing intuitive data for studying the temperature changes of the coating during thermal cycling and thermal shock. The high-temperature strain gauges are directly pasted on the surface of the coating or the specimen substrate to measure the strain of the coating during the process of force and temperature changes, with a measurement accuracy of up to ±10 με. The pressure sensors are installed in the loading system and the chamber to monitor the magnitude and changes of the pressure in real time, with an accuracy of up to ±2 MPa. The laser displacement sensor accurately monitors the surface displacement of the coating during the experiment by emitting a laser beam and measuring the displacement change of the reflected light, with an accuracy of up to ±0.01 mm. The data acquisition and analysis sub-module transmits the data collected by all monitoring devices to the computer through a high-speed data acquisition card and performs real-time analysis and processing by a specially developed data processing software. The data processing software adopts advanced signal processing algorithms and data analysis models, which can perform fusion analysis on multi-source data, providing strong technical support for the maintenance of aero-engines and the life prediction of thermal barrier coatings.

[0044] In one embodiment, when studying the heat insulation performance of the thermal barrier coating, the calculation formula of the heat flux is as follows:

[0045]

[0046] Where q is the heat flux (W / m 2 ), k is the thermal conductivity (W / (m·K)), is the temperature gradient (K / m). In the experimental system, by measuring the temperature difference between both sides of the coating and knowing the coating thickness, the heat flux can be calculated to evaluate the heat insulation effect of the coating. For example, in the high-temperature thermal cycling module, when the temperature on one side of the coating is T 1 = 1200 °C (1473 K), and the temperature on the other side is T 2 = 800 °C (1073 K), the coating thickness x = 0.5 mm = 0.0005 m. If the known thermal conductivity of the coating k = 1.5 W / (m·K), then the heat flux is:

[0047]

[0048] In one embodiment, in the high-altitude airflow erosion module, the following formula is used to estimate the impact force of the airflow on the coating:

[0049]

[0050] In the case of horizontal erosion, when h remains unchanged, it can be simplified as:

[0051]

[0052] where p is the static pressure (Pa), ρ is the gas density (kg / m 3 ), and v is the gas flow velocity (m / s). For example, when the gas flow velocity v 1 = 500 m / s and the gas density ρ = 1.2 kg / m 3 , assuming the static pressure p 1 = 10 5 Pa, and the gas flow velocity at a certain point on the coating surface drops to v 2 = 300 m / s, then the pressure change at this point is:

[0053]

[0054] The pressure difference Δp = p 2 - p 1 = 96000 Pa. The impact force can be calculated based on the pressure difference and the coating area.

[0055] The following table shows the performance change data of the coating under different working conditions:

[0056]

[0057] As described above, it is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of various changes or substitutions, and these should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claimed rights.

Claims

1. An aircraft engine thermal barrier coating working condition simulation experimental system, characterized by: It includes high temperature thermal cycle module, high speed air flow flushing module, high pressure loading module, atmosphere control module and data monitoring and acquisition module; The high temperature thermal cycle module realizes rapid heating and cooling to simulate a thermal environment; The high-speed airflow flushing module generates a high-speed airflow to simulate the flushing of gas; The high-voltage loading module applies pressure to simulate mechanical stress; The atmosphere control module regulates the atmosphere to simulate the gas environment in the engine; The data monitoring and acquisition module monitors parameters in real time to provide data support for research.

2. The aerospace engine thermal barrier coating working condition simulation experimental system according to claim 1, characterized in that: The high-temperature thermal cycle module includes a heating submodule and a temperature control submodule. The heating submodule adopts a composite heating technology combining induction heating and resistance heating to create a fast and stable heating and cooling environment in the high vacuum chamber. The induction coil is customized according to the geometric shape of the specimen and surrounds the specimen. An induced current is generated inside the specimen through an alternating magnetic field to achieve rapid heating. At the same time, the resistance heating wire is reasonably arranged in the chamber to perform precise temperature compensation and fine-tuning based on induction heating to ensure uniform heating of the specimen. The temperature control submodule uses an advanced PID temperature controller and a high-precision temperature The temperature sensor can achieve precise control of the temperature. When simulating the working conditions of the thermal barrier coating in the combustion chamber of an aircraft engine, the system can quickly raise the temperature of the test piece from room temperature to 1200℃ within 10-30 seconds, and the cooling rate can reach 50-100℃ / second. After multiple thermal cycle tests, the microstructure of the coating was analyzed and it was found that even after more than 1000 thermal cycles, the crystal structure of the coating remained relatively intact, and the bonding strength between the coating and the substrate only decreased by about 5%, effectively avoiding the cracking and peeling of the coating due to thermal stress, providing key experimental conditions for in-depth research on the thermal fatigue performance of the coating.

3. The aerospace engine thermal barrier coating working condition simulation experimental system according to claim 1, characterized in that: The high-speed airflow scouring module includes an airflow generation submodule and a scouring experiment and coating erosion analysis submodule. The airflow generation submodule uses a design that combines a high-pressure gas drive system with a Laval nozzle to generate a high-speed airflow with a speed of up to 0.5-2.0Ma. The high-pressure gas first accumulates energy in the drive chamber and then accelerates through the special structure of the Laval nozzle, so that the airflow reaches the required high-speed state at the nozzle outlet. In order to ensure the uniformity of the airflow, numerical simulation optimization technology is used in the nozzle design process, and the internal flow channel of the nozzle is finely designed so that the speed uniformity deviation of the airflow at the outlet is controlled within ±5%. In the scouring experiment and coating erosion analysis submodule, the distance between the nozzle outlet and the test piece is precisely set at 50-100mm to ensure that the high-speed airflow can simulate the scouring of the coating at a suitable angle and intensity.

4. The aerospace engine thermal barrier coating working condition simulation experimental system according to claim 1, characterized in that: The high-pressure loading module includes a loading system submodule and a thermal coupling experiment submodule. The loading system submodule is based on a hydraulic servo system and a customized fixture design, and can apply a pressure of 50-200MPa to the specimen. The hydraulic servo system drives the loading piston to apply stable pressure to the specimen by precisely controlling the pressure and flow of the hydraulic oil. The customized fixture is designed according to specimens of different shapes and sizes to ensure that the pressure can be evenly distributed on the surface of the specimen while avoiding additional damage to the specimen during the loading process. In the thermal coupling experiment submodule, when a pressure of 100MPa is applied to the coating and high-temperature heating is performed at the same time, the hardness of the coating is measured by nanoindentation technology and it is found that the hardness of the coating is increased by about 10%-15% compared with when no pressure is loaded.

5. The aerospace engine thermal barrier coating working condition simulation experimental system according to claim 1, characterized in that: The atmosphere control module includes a gas control submodule and an oxidation experiment and coating antioxidant performance evaluation submodule. The gas control submodule can accurately control the atmosphere in the chamber with the help of a high-precision gas flow controller and an advanced vacuum system. The gas flow controller can accurately control the flow of gases such as oxygen, nitrogen, water vapor, and simulated aviation fuel combustion products, and realize accurate regulation of the oxygen content (5%-20%), humidity (0-10% RH) and fuel gas composition in the chamber. The oxidation experiment and coating antioxidant performance evaluation submodule sets the oxygen content in the chamber to 10% and the temperature to 1000°C. After 100 hours of oxidation treatment, the oxidation weight gain of the coating is measured by thermogravimetric analysis. It is found that the oxidation weight gain rate of the coating is about 0.1-0.3 mg / cm 2 ·h.

6. The aerospace engine thermal barrier coating working condition simulation experimental system according to claim 1, characterized in that: The data monitoring and acquisition module includes a monitoring submodule and a data acquisition and analysis submodule. The monitoring submodule integrates advanced monitoring equipment such as infrared thermal imagers, high-temperature strain gauges, high-precision pressure sensors and laser displacement sensors. The infrared thermal imager can monitor the temperature field distribution on the coating surface in real time and non-contactly, and its temperature resolution can reach 0.1°C, providing intuitive data for studying the temperature change of the coating during thermal cycling and thermal shock. The high-temperature strain gauge is directly attached to the coating surface or the specimen substrate to measure the strain of the coating during stress and temperature changes, and its measurement accuracy can reach ±10με. The pressure sensor is installed in the loading system and In the chamber, the size and changes of pressure are monitored in real time with an accuracy of ±2MPa. The laser displacement sensor accurately monitors the surface displacement of the coating during the experiment by emitting a laser beam and measuring the displacement changes of the reflected light with an accuracy of ±0.01mm. The data acquisition and analysis submodule transmits the data collected by all monitoring devices to the computer through a high-speed data acquisition card, and the data is analyzed and processed in real time by specially developed data processing software. The data processing software uses advanced signal processing algorithms and data analysis models, and can perform fusion analysis on multi-source data, providing strong technical support for the maintenance of aircraft engines and the life prediction of thermal barrier coatings.

7. The aerospace engine thermal barrier coating working condition simulation experimental system according to claim 1, characterized in that: When studying the thermal insulation performance of thermal barrier coatings, the heat flux is calculated as follows: Where q is the heat flux (W / m 2 ), k is the thermal conductivity (W / (m·K)), is the temperature gradient (K / m). In the experimental system, by measuring the temperature difference on both sides of the coating and the known coating thickness, the heat flux can be calculated to evaluate the thermal insulation effect of the coating. For example, in the high-temperature thermal cycle module, when the temperature on one side of the coating is T1 = 1200°C (1473K), the temperature on the other side is T2 = 800°C (1073K), and the coating thickness is x = 0.5mm = 0.0005m, if the thermal conductivity of the coating is known to be k = 1.5W / (m·K), the heat flux is:

8. The aerospace engine thermal barrier coating working condition simulation experimental system according to claim 1, characterized in that: In the high-altitude airflow wash module, the following formula is used to estimate the impact of airflow on the coating: In the case of horizontal scour, h remains unchanged and can be simplified to: Where p is the static pressure (Pa), ρ is the gas density (kg / m 3 ), v is the air velocity (m / s). For example, when the air velocity v1 = 500 m / s and the gas density ρ = 1.2 kg / m 3 , assuming static pressure p1 = 10 5 Pa, the air flow velocity at a certain point on the coating surface drops to v2 = 300m / s, then the pressure change at that point is: The pressure difference Δp=p2-p1=96000Pa. The impact force can be calculated based on the pressure difference and the coating area.

Images