Performance test system and method for high-temperature anti-oxidation coating of airspace engine

Abstract

The invention discloses a performance test system and method for a high-temperature anti-oxidation coating of an airspace engine, and relates to the technical field of coating performance test.The system comprises a sample detection platform, a detection system cooling system and a control system; the detection system comprises a high-precision colorimetric infrared laser thermodetector, a complex impedance spectroscopy measurement device and an acoustic emission detection device, the thermodetector is used for detecting the temperature of a to-be-detected sample and outputting a temperature signal, and the complex impedance spectroscopy measurement device is used for detecting the impedance change of a coating when the to-be-detected sample is oxidized and outputting an impedance change data signal; and the acoustic emission detection device detects the damage of the surface appearance of the to-be-detected sample after high-temperature oxidation and outputs a damage acoustic emission data signal. According to the system disclosed by the invention, the impedance change of the coating and a damage acoustic emission signal during sample oxidation are detected in real time through the complex impedance spectroscopy measurement system and the acoustic emission detection system, and an important experimental platform is provided for effectively evaluating the failure process and the failure mechanism of the coating in a high-temperature aerobic environment.

Description

Technical Field

[0001] This specification relates to the technical field of high-temperature anti-oxidation coating material testing for aerospace engines, and in particular to a performance testing system and method for high-temperature anti-oxidation coatings for aerospace engines. Background Art

[0002] Aerospace engines are the power plant and core component of rockets. With the development of the aerospace industry, the application temperature of high-temperature materials is constantly increasing, especially in the aerospace and defense sectors. As the service temperatures of key rocket engine components continue to rise, higher high-temperature resistance requirements are being placed on these materials. In particular, the operating temperature and oxidation resistance requirements for high-temperature anti-oxidation coatings have been significantly increased. For example, heat-resistant, high-strength structural materials used in rockets, missiles, and satellites, exposed to gaseous environments, must be coated with specialized coatings to prevent oxidation failure at high temperatures. For example, the operating temperature of engine combustion chambers, nozzles, nozzle extensions, and other key components has increased from 1200-1400°C to 1600-2200°C. Below 1400°C, traditional muffle furnaces have been used for heating. At temperatures reaching 1600°C, the high temperature makes them incapable of long-term monitoring. As the temperature rises further, the furnace's insulation material limits its ability to withstand the high temperatures. Furthermore, the muffle furnace cannot accurately monitor surface coating changes and coating failure in real time; observation can only be performed after the furnace is cooled and shut down. When the temperature reaches 1700-2200℃, the temperature control of existing high-temperature antioxidant equipment fluctuates greatly, has low accuracy, and cannot control the heating time. It can only perform static constant temperature tests, etc., which makes it difficult to truly simulate the actual service conditions of the rocket engine, which is not conducive to experiments and scientific research.

[0003] In the existing technology, there are methods to test the thermal shock resistance of thermal barrier coatings by cyclically using high-temperature flame flow devices, to test the oxidation resistance of coatings by heating with electrodes, and to test the thermal shock life and thermal insulation performance of coatings by using flame spray guns.

[0004] However, existing coating testing devices or methods only test the coating's thermal shock resistance, thermal insulation, and static constant-temperature oxidation resistance. They lack devices that simulate the transient heating and cooling experienced during actual aerospace engine operations. More importantly, these existing testing devices lack real-time monitoring and evaluation of the coating's oxidation resistance and the formation of oxidative damage, which weakens experimental results. They also lack real-time monitoring and early warning of coating failure processes. Aerospace engine manufacturing is difficult and costly, and engine qualification tests, especially high-altitude simulated tests, are expensive. Using engine tests to test material performance, especially post-production performance, is undoubtedly unfeasible.

[0005] Therefore, designing and developing experimental simulation devices for high-temperature static oxidation and high-temperature thermal shock cyclic oxidation of high-temperature anti-oxidation coatings, and combining real-time monitoring technology and related equipment to effectively and reliably simulate the actual working conditions of the coating and detect the high-temperature anti-oxidation ability of the coating, is the primary problem that must be solved in the development of high-temperature anti-oxidation coatings, and is also a key problem that must be solved in scientific research experiments and applications. Summary of the Invention

[0006] One or more embodiments of this specification provide a performance testing system and method for high-temperature anti-oxidation coatings in aerospace engines, which are used to solve the following technical problems: it is difficult for existing technologies to achieve high-temperature static constant-temperature oxidation and dynamic thermal shock cycle oxidation tests of high-temperature anti-oxidation coatings in aerospace engines under high-temperature application environments.

[0007] One or more embodiments of this specification adopt the following technical solutions:

[0008] One or more embodiments of this specification provide a performance testing system for a high-temperature anti-oxidation coating of an aerospace engine, the system comprising:

[0009] The sample testing platform includes a platform body and sample clamping platform A and sample clamping platform B. The platform body includes a support base and positioning devices A and positioning devices B. Positioning devices A and positioning devices B are arranged on the support base and can move horizontally on the support base. Sample clamping platform A and sample clamping platform B are respectively fixed to positioning devices A and positioning devices B and can move on the support base with positioning devices A and positioning devices B.

[0010] The sample clamping platform A includes a bracket, a clamping device, and upper and lower sample electrodes correspondingly arranged above and below. The bracket has a connecting portion connected to the clamping device and a supporting member for supporting the lower sample electrode. The clamping device can move up and down in the vertical direction within the connecting portion. The upper sample electrode and the lower sample electrode are arranged between the clamping device and the supporting member. Removable modules are provided at the relative positions of the upper sample electrode and the lower sample electrode. The opposing surfaces of the removable modules are provided with grooves. The shapes of the grooves of the pair of removable modules match to clamp one end of the sample to be tested. Cooling water pipes are provided inside the upper sample electrode and the lower sample electrode.

[0011] The sample clamping platform B is symmetrically arranged with the sample clamping platform A to clamp the two ends of the sample to be tested;

[0012] The detection system includes at least a high-precision colorimetric infrared laser thermometer, a complex impedance spectrum measuring device, and an acoustic emission detection device, which are arranged in the platform body. The high-precision colorimetric infrared laser thermometer is used to detect the temperature of the sample to be detected and output a temperature signal accordingly. The complex impedance spectrum measuring device includes at least an electrode, which can be connected to the sample to be detected to detect the impedance change of the coating when the sample to be detected is oxidized and output an impedance change data signal accordingly. The acoustic emission detection device includes at least a guide rod, which can be connected to the sample to be detected to detect damage to the surface morphology of the sample to be detected after high-temperature oxidation and output a damage acoustic emission data signal accordingly.

[0013] A cooling system comprising at least an exhaust fan and a water cooler, wherein the exhaust fan is disposed on the top of the platform body, and the water cooler is disposed inside the platform body. The water cooler is connected to a cooling water pipe so that cooling water circulates between the cooling water pipe and the water cooler;

[0014] A control system, wherein the control system is capable of receiving a temperature signal and adjusting the current in the upper sample electrode and the lower sample electrode and / or the operating state of the cooling system based on the temperature signal. The control system is also capable of receiving an impedance change data signal and obtaining information on changes in the internal structure of the coating of the sample to be tested during a high-temperature oxidation process based on the impedance change data signal. The control system is also capable of receiving a damage acoustic data signal and monitoring the generation and / or healing of high-temperature oxidation cracks in the coating of the sample to be tested based on the damage acoustic emission data signal.

[0015] When in working state, the clamping device is moved so that the sample clamping platform A and the sample clamping platform B respectively clamp the two ends of the sample to be tested. One of the positioning device A and the positioning device B is fixed on the support base, and the other is movably set on the support base. When the sample to be tested is deformed by heat, the movable positioning device can move to offset the deformation of the sample to be tested.

[0016] Furthermore, the control system also includes a power controller, which is electrically connected to the external power supply and the upper sample electrode and the lower sample electrode respectively, and is used to adjust the current in the upper sample electrode and the lower sample electrode.

[0017] Furthermore, the support seat includes a support seat body, and a slide rail, a slider and a limit block arranged in the support seat body. The slider and the limit block are respectively arranged on the slide rail, the limit block is connected to the fixed positioning device, and the slider is connected to the movably arranged positioning device. The slider can move along the slide rail to realize the displacement of the positioning device.

[0018] Furthermore, an insulating member is provided between the upper sample electrode and the clamping device, and another insulating member is provided between the lower sample electrode and the supporting member.

[0019] Preferably, the insulating member is an insulating gasket.

[0020] Furthermore, the upper sample electrode, the lower sample electrode and the detachable module are connected by bolts, and at least one type of pad is provided in the groove of the detachable module. The pad is detachably connected in the groove. Different types of pads have different shapes to adapt to samples to be tested with different cross-sectional shapes, so that the sample to be tested is fixed between the upper sample electrode and the lower sample electrode.

[0021] Furthermore, the control system includes at least a controllable programmer and a touch-screen industrial computer. The controllable programmer is signal-connected to the touch-screen industrial computer. The controllable programmer is signal-connected to a high-precision colorimetric infrared laser thermometer, an exhaust fan, and a water cooler respectively. The touch-screen industrial computer is signal-connected to a complex impedance spectrum measuring device and an acoustic emission detection device respectively.

[0022] Furthermore, the performance test system for high-temperature anti-oxidation coatings of aerospace engines also includes an experimental console, which includes a closed chassis with an observation element provided on the closed chassis, through which the state of the sample to be tested can be observed.

[0023] Furthermore, the experimental console also includes a control module and a display module. The control module is provided with at least an alarm element, an emergency stop element, a power switch and a data acquisition submodule. The data acquisition submodule is used to collect experimental parameters, and the display module is used to at least display the collected experimental parameters.

[0024] One or more embodiments of this specification provide a performance testing method for a high-temperature anti-oxidation coating for an aerospace engine. The testing method uses a performance testing system for a high-temperature anti-oxidation coating for an aerospace engine as described in any one of the above. The testing method includes the following steps:

[0025] Move the clamping device so that the sample clamping platform A and the sample clamping platform B respectively clamp the two ends of the sample to be tested;

[0026] One of the positioning device A and the positioning device B is fixed on the support base, and the other is movably arranged on the support base;

[0027] The upper sample electrode and the lower sample electrode are used to heat the sample to be tested by current, and the sample to be tested is heated to the target temperature according to the preset heating time;

[0028] Keep the sample to be tested warm according to the preset constant temperature oxidation time, and maintain the temperature within 1°C above or below the target temperature;

[0029] The experimental parameters of the high-precision colorimetric infrared laser thermometer, complex impedance spectroscopy measurement device, and acoustic emission detection device were obtained and recorded respectively.

[0030] Furthermore, the performance test method for high-temperature anti-oxidation coatings for aerospace engines also includes:

[0031] Use electric current to heat the sample to be tested;

[0032] The experiment is carried out according to the pre-set heating time, holding time and cooling time in the thermal shock cycle process. The sample to be tested is heated to the target temperature and maintained at the target temperature for 15 seconds before cooling down to complete a thermal shock cycle.

[0033] Repeat the previous step according to the preset number of cycles;

[0034] The experimental parameters of the high-precision colorimetric infrared laser thermometer, complex impedance spectroscopy measurement device, and acoustic emission detection device were obtained and recorded respectively.

[0035] At least one of the above technical solutions adopted in the embodiments of this specification can achieve the following beneficial effects:

[0036] 1. The present invention provides a performance testing system for high-temperature, anti-oxidation coatings on aerospace engines. This system uses a complex impedance spectroscopy measurement system and an acoustic emission detection system to detect changes in coating impedance and damage acoustic emission signals during sample oxidation in real time. A computer monitors changes in the internal structure of the high-temperature oxidation coating and monitors the generation and healing of high-temperature oxidation cracks in the coating in real time, providing an important experimental platform for effectively evaluating the failure process and mechanism of the coating in a high-temperature, aerobic environment. The performance testing system for high-temperature, anti-oxidation coatings on aerospace engines provided by the present invention can effectively reduce the number of test runs required for coating materials used in high-temperature components such as aerospace engines, thereby reducing engine development and production costs.

[0037] 2. The performance testing system for high-temperature anti-oxidation coatings for aerospace engines provided by the present invention can detect a wide temperature range, from room temperature to 2200°C, with high data credibility, solving the problem of difficult high-temperature static performance testing of high-temperature anti-oxidation coatings at 1600-2200°C.

[0038] 3. The performance testing system for high-temperature anti-oxidation coatings of aerospace engines provided by the present invention can simulate the frequent hot and cold shock environment of high-temperature engine components. Through the setting of the controllable programmer, it can achieve long-term and multiple temperature rises and falls, and accurately simulate actual dynamic working conditions by controlling the time of temperature rise and fall.

[0039] 4. The performance testing system for high-temperature anti-oxidation coatings of aerospace engines provided by the present invention performs pre-experimental adjustments based on the characteristics of different workpieces, accurately generates and records temperature rise curves and data, and increases the accuracy and authenticity of experimental data.

[0040] 5. The performance testing method for high-temperature anti-oxidation coatings of aerospace engines provided by the present invention can simulate the high-temperature aerobic service environment of the anti-oxidation coatings of high-temperature components such as the nozzle extension of aerospace engines. By precisely controlling parameters such as the heating time and the cooling time, the heating curve is automatically run, and the operating status of each component is displayed in real time, thereby improving the intelligence and safety of the equipment. It also analyzes the evolution of the coating impedance and surface morphology in a high-temperature environment, and can effectively evaluate the failure process and failure mechanism of the high-temperature anti-oxidation coating in a high-temperature aerobic environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] In order to more clearly illustrate the embodiments of this specification or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments recorded in this specification. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0042] In the attached figure:

[0043] Figure 1 A schematic diagram of a structural diagram of a performance testing system for aerospace engine high-temperature anti-oxidation coating provided in an embodiment of this specification;

[0044] Figure 2 A schematic structural diagram of a sample detection platform in a performance test system for aerospace engine high-temperature anti-oxidation coatings provided in an embodiment of this specification;

[0045] Figure 3 This is a structural schematic diagram of an experimental console in a performance test system for high-temperature anti-oxidation coatings of aerospace engines provided in an embodiment of this specification.

[0046] in:

[0047] 11- platform body; 12- sample clamping platform A; 13- sample clamping platform B;

[0048] 111-support seat; 112-positioning device A; 113-positioning device B; 114-slide rail; 115-slider; 116-limiting block;

[0049] 121- bracket; 122- clamping device; 123- upper sample electrode; 124- lower sample electrode; 125- supporting member; 126- removable module; 127- cooling water pipe; 128- insulating member;

[0050] 21-High-precision colorimetric infrared laser thermometer; 22-Complex impedance spectroscopy measurement device; 23-Acoustic emission detection device;

[0051] 31-exhaust fan; 32-water cooler;

[0052] 41-enclosed chassis; 42-observation element;

[0053] 51-controllable programmer; 52-touch-screen industrial computer;

[0054] 900-sample to be tested. DETAILED DESCRIPTION

[0055] To help those skilled in the art better understand the technical solutions in this specification, the following will provide a clear and complete description of the technical solutions in the embodiments of this specification, in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of this specification, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this specification without creative work should fall within the scope of protection of this specification.

[0056] Considering the problems existing in existing experimental equipment, the present invention provides a system and method for testing the performance of high-temperature anti-oxidation coatings for aerospace engines. To more clearly illustrate the overall concept of the present invention, the following detailed description is given in conjunction with the accompanying drawings by way of example.

[0057] The specific plans adopted are:

[0058] On the one hand, this embodiment provides a performance testing system for high-temperature anti-oxidation coatings of aerospace engines. Figure 1-Figure 3As shown, the performance test system for high-temperature anti-oxidation coating of aerospace engines includes a sample detection platform, a detection system, a cooling system and a control system, wherein the sample detection platform includes a platform body 11 and a sample clamping platform A12 and a sample clamping platform B13, the platform body includes a support base 111 and a positioning device A112 and a positioning device B113, the positioning device A112 and the positioning device B113 are arranged on the support base 111, and can move on the support base 111 in the horizontal direction, the sample clamping platform A12 and the sample clamping platform B13 are respectively fixed on the positioning device A112 and the positioning device B113, and can move with the positioning device A112 and the positioning device B113. The positioning device B113 moves on the support seat 111; the sample clamping platform A12 includes a bracket 121, a clamping device 122, an upper sample electrode 123 and a lower sample electrode 124 arranged correspondingly above and below, the bracket 121 has a connecting portion connected to the clamping device and a supporting member 125 for supporting the lower sample electrode, the clamping device 122 can move up and down in the vertical direction within the connecting portion, the upper sample electrode 123 and the lower sample electrode 124 are arranged between the clamping device 122 and the supporting member 125, and a detachable module 126 is provided at the relative position of the upper sample electrode 123 and the lower sample electrode 124, and a detachable module 126 is provided on the opposite surface of the detachable module 126. The grooves of a pair of detachable modules are matched in shape to clamp one end of the sample to be tested 900. A cooling water pipe 127 is provided inside the upper sample electrode 123 and the lower sample electrode 124. The sample clamping platform B13 and the sample clamping platform A12 are symmetrically arranged to clamp the two ends of the sample to be tested 900. The detection system includes at least a high-precision colorimetric infrared laser thermometer 21, a complex impedance spectrum measuring device 22, and an acoustic emission detection device 23 arranged in the platform body. The high-precision colorimetric infrared laser thermometer 21 is used to detect the temperature of the sample to be tested and output a temperature signal accordingly. The complex impedance spectrum measuring device 22 includes at least an electrode, an electrode It can be connected to the sample to be tested to detect the impedance change of the coating when the sample to be tested is oxidized, and output an impedance change data signal accordingly. The acoustic emission detection device 23 includes at least a guide rod, which can be connected to the sample to be tested to detect damage to the surface morphology of the sample to be tested after high-temperature oxidation, and output a damage acoustic emission data signal accordingly. The cooling system includes at least an exhaust fan 31 and a water cooler 32. The exhaust fan 31 is arranged on the top of the platform body 11, and the water cooler 32 is arranged inside the platform body 11. The water cooler 32 is connected to the cooling water pipe 127 to circulate cooling water between the cooling water pipe 127 and the water cooler 32.The control system can receive temperature signals and, based on the temperature signals, adjust the current in the upper sample electrode 123 and the lower sample electrode 124 and / or the operating state of the cooling system. The control system can also receive impedance change data signals and, based on the impedance change data signals, obtain information on changes in the internal structure of the coating of the sample to be tested during the high-temperature oxidation process. The control system can also receive damage acoustic data signals and, based on the damage acoustic emission data signals, monitor the generation and / or healing of high-temperature oxidation cracks in the coating of the sample to be tested.

[0059] When in working state, the clamping device 122 is moved so that the sample clamping platform A12 and the sample clamping platform B13 respectively clamp the two ends of the sample to be tested 900. One of the positioning device A112 and the positioning device B113 is fixed on the support base 111, and the other is movably set on the support base 111. When the sample to be tested 900 is deformed by heat, the movably set positioning device can move to offset the deformation of the sample to be tested 900.

[0060] In a preferred embodiment, the control system further includes a power controller, which is electrically connected to an external power source and the upper sample electrode 123 and the lower sample electrode 124 respectively, and is used to adjust the current in the upper sample electrode 123 and the lower sample electrode 124.

[0061] In a preferred embodiment, the support seat 111 includes a support seat body, and a slide rail 114, a slider 115 and a limit block 116 arranged in the support seat body. The slider 115 and the limit block 116 are respectively arranged on the slide rail 114, the limit block 116 is connected to the fixed positioning device, and the slider 115 is connected to the movably arranged positioning device. The slider 115 can move along the slide rail to realize the displacement of the positioning device.

[0062] In a preferred embodiment, an insulating member is provided between the upper sample electrode 123 and the clamping device 122, and another insulating member is provided between the lower sample electrode 124 and the supporting member 125. The insulating member 128 is an insulating gasket.

[0063] In a preferred embodiment, the upper sample electrode 123, the lower sample electrode 124 and the detachable module 126 are connected by bolts. The groove of the detachable module 126 also includes at least one type of pad, which is detachably connected in the groove. Different types of pads have different shapes to adapt to the different cross-sectional shapes of the samples 900 to be tested, so that the sample 900 to be tested is fixed between the upper sample electrode 123 and the lower sample electrode 124.

[0064] In a preferred embodiment, the control system includes at least a controllable programmer 51 and a touch-screen industrial computer 52. The controllable programmer 51 is signal-connected to the touch-screen industrial computer 52. The controllable programmer 51 is signal-connected to the high-precision colorimetric infrared laser thermometer 21, the exhaust fan 31 and the water cooler 32 respectively. The touch-screen industrial computer 52 is signal-connected to the complex impedance spectroscopy measuring device 22 and the acoustic emission detection device 23 respectively.

[0065] In a preferred embodiment, the performance testing system for aerospace engine high-temperature anti-oxidation coatings further includes an experimental console comprising a closed chassis 41 on which an observation element 42 is provided, through which the state of the test specimen can be observed. The observation element 42 is an observation window.

[0066] In a preferred embodiment, the experimental console also includes a control module and a display module. The control module is provided with at least an alarm element, an emergency stop element, a power switch and a data acquisition submodule. The data acquisition submodule is used to collect experimental parameters, and the display module is used to at least display the collected experimental parameters.

[0067] In this embodiment, the upper sample electrode 123 and the lower sample electrode 124 are slidably engaged on the sample detection platform, which can adjust the deformation of the sample to be detected 900 due to heat to avoid peeling and failure of the coating. The stress generated by the heat of the detection sample 900 drives the positioning device to move, thereby preventing the deformation of the detection sample 900 and causing the coating to peel and fail, making the sample life detection more accurate. Cooling water can circulate between the cooling water pipe 127 in the electrode and the water chiller 32 to adjust the temperature of the sample electrode. The sample to be detected 900 is fixed in the groove of the detachable module 126. The grooves of different detachable modules 126 can match the different shapes of the samples to be detected 900, reducing the influence of contact resistance on the experiment. The groove of the detachable module 126 is in contact with the conductive electrode, and the bottom is connected to the insulating pad and the slider 115 vertically engaged on the slide rail 114.

[0068] The upper sample electrode 123 and the lower sample electrode 124 are connected to the two ends of the power supply and the dedicated high-power transformer. A power controller is also connected between the power supply and the transformer. The input power supply is 220 volts AC and the output is a safe voltage of 5 volts. The low voltage and high current mode can ensure the safety of equipment and personnel while meeting the experimental needs. The power controller is connected to the controllable programmer 51. The controllable programmer 51 is connected to the high-precision colorimetric infrared laser thermometer 21 through a data line. Combined with a special algorithm, it can automatically perform self-adjustment according to the experimental parameters when the external voltage or environment fluctuates. In a relatively short time, Through self-adjustment and real-time tracking through algorithms, the system accurately achieves test temperatures from room temperature to 2200°C. A high-precision colorimetric infrared laser thermometer 21 is aligned with the center of the test specimen 900. A controllable programmer 51 is connected to a touch-screen industrial computer 52 via a data cable for control, enabling periodic oscillations in thermal shock experiments or continuous operation of antioxidant experiments. The complex impedance spectroscopy measurement device 22 and acoustic emission detection device 23 are connected to the touch-screen industrial computer 52, allowing the computer to capture changes in the internal structure of the high-temperature oxidation coating and monitor the generation and healing of high-temperature oxidation cracks in the coating in real time. The exhaust fan 31 on top of the sample testing platform is connected to the controllable programmer 51, and the water cooler 32 is also connected to the controllable programmer 51 to regulate the temperature of the chassis during operation and ensure experimental safety.

[0069] This embodiment provides a performance testing system for high-temperature, anti-oxidation coatings on aerospace engines. This system uses a complex impedance spectroscopy measurement system and an acoustic emission detection system to detect changes in coating impedance and damage acoustic emission signals during sample oxidation in real time. A computer monitors changes in the internal structure of the high-temperature oxidation coating and monitors the generation and healing of high-temperature oxidation cracks in the coating in real time, providing an important experimental platform for effectively evaluating the failure process and mechanism of the coating in a high-temperature, aerobic environment. This performance testing system for high-temperature, anti-oxidation coatings on aerospace engines can effectively reduce the number of qualification tests for coating materials used in high-temperature components such as aerospace engines, thereby reducing engine development and production costs.

[0070] The performance testing system for high-temperature anti-oxidation coatings for aerospace engines provided in this embodiment can detect a wide temperature range, from room temperature to 2200°C, with high data credibility, solving the problem of difficult high-temperature static performance testing of high-temperature anti-oxidation coatings at 1600-2200°C.

[0071] The performance testing system for high-temperature anti-oxidation coatings of aerospace engines provided in this embodiment can simulate the frequent hot and cold shock environment of high-temperature engine components. Through the setting of the controllable programmer, it can achieve long-term and multiple temperature increases and decreases, and accurately simulate actual dynamic working conditions by controlling the time of temperature increase and decrease.

[0072] The performance testing system for high-temperature anti-oxidation coatings of aerospace engines provided in this embodiment performs pre-experimental adjustments based on the characteristics of different workpieces, accurately generates and records temperature rise curves and data, and increases the accuracy and authenticity of experimental data.

[0073] Another aspect of this embodiment provides a performance testing method for a high-temperature anti-oxidation coating for an aerospace engine. The testing method uses the performance testing system for a high-temperature anti-oxidation coating for an aerospace engine as described in any one of the above items. The testing method includes the following steps:

[0074] Move the clamping device so that the sample clamping platform A and the sample clamping platform B respectively clamp the two ends of the sample to be tested;

[0075] One of the positioning device A and the positioning device B is fixed on the support base, and the other is movably arranged on the support base;

[0076] The upper sample electrode and the lower sample electrode are used to heat the sample to be tested by current, and the sample to be tested is heated to the target temperature according to the preset heating time;

[0077] Keep the sample to be tested warm according to the preset constant temperature oxidation time, and maintain the temperature within 1°C above or below the target temperature;

[0078] The experimental parameters of the high-precision colorimetric infrared laser thermometer, complex impedance spectroscopy measurement device, and acoustic emission detection device were obtained and recorded respectively.

[0079] In a preferred embodiment, the performance testing method for aerospace engine high-temperature anti-oxidation coating further includes:

[0080] Use electric current to heat the sample to be tested;

[0081] The experiment is carried out according to the pre-set heating time, holding time and cooling time in the thermal shock cycle process. The sample to be tested is heated to the target temperature and maintained at the target temperature for 15 seconds before cooling down to complete a thermal shock cycle.

[0082] Repeat the previous step according to the preset number of cycles;

[0083] The experimental parameters of the high-precision colorimetric infrared laser thermometer, complex impedance spectroscopy measurement device, and acoustic emission detection device were obtained and recorded respectively.

[0084] To facilitate understanding of the present invention, the performance testing method for aerospace engine high-temperature anti-oxidation coating provided in this embodiment is further described:

[0085] The steps of using the performance testing system for aerospace engine high-temperature anti-oxidation coating provided by the present invention to conduct simulation experiments and real-time tests on samples of high-temperature anti-oxidation coating are as follows:

[0086] 1. Clamping of the sample to be tested: Clamp the sample to be tested to the groove of the detachable module with the right shape so that it contacts the conductive electrode. Connect the impedance test electrode and the acoustic emission test waveguide rod to the surface of the sample to be tested with the high-temperature anti-oxidation coating and the metal substrate at both ends respectively. Aim the colorimetric thermometer at the center of the sample to be tested, close the observation window and turn on the experimental power switch.

[0087] 2. Constant-Temperature Oxidation Experiment: Open the experimental control system through the experimental console and adjust the experiment type to a constant-temperature oxidation experiment. Set the experimental parameters according to the experimental conditions and the warning current and temperature according to the sample material to be tested. Simultaneously, open the detection system and adjust the instrument parameters. The equipment will not start heating until the cooling system is turned on. The current is automatically adjusted according to the set temperature. During the experiment, the changes in coating impedance and damage to the sample to be tested are monitored in real time during oxidation. After the experiment is completed, generate data and graphs, close the system, and clean up the equipment.

[0088] 3. Thermal Shock Cycle Test: Open the experimental control system through the experimental console and adjust the experiment type to thermal shock cycle test. Set the experimental parameters according to the experimental conditions and the warning current and temperature according to the material of the sample to be tested. At the same time, open the detection system and adjust the instrument parameters. The equipment can only start heating after the cooling system is turned on. The current is automatically adjusted according to the set temperature to cycle the temperature of the sample to be tested. During the experiment, the changes in coating impedance and damage of the sample to be tested are monitored in real time during oxidation. After the experiment is completed, data and graphs are generated, the system is closed, and the equipment is cleaned up.

[0089] The performance testing method for aerospace engine high-temperature anti-oxidation coatings provided in this embodiment can simulate the high-temperature aerobic service environment of high-temperature components such as aerospace engine nozzle extensions. By simulating different types of working environments (static constant-temperature oxidation, thermal shock cycle experiments), the process of simulating the high-temperature oxidation of the coating during service is realized. The changes in the sample during oxidation are detected in real time through the detection system, thereby analyzing the interface morphology and damage evolution during the oxidation process, and effectively evaluating the failure process and failure mechanism of the high-temperature anti-oxidation coating in a high-temperature aerobic environment.

[0090] Anything not described in the present invention can be achieved by adopting or drawing on existing technologies.

[0091] The above are merely specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various modifications or substitutions within the technical scope disclosed in the present invention, and such modifications or substitutions are intended to be within the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be subject to the scope of protection of the claims.

[0092] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0093] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature identified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0094] In the present invention, unless otherwise expressly specified or limited, terms such as "mounted," "connected," "connect," and "fixed" should be understood broadly. For example, they may refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0095] In the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Furthermore, a first feature being "above," "toward," or "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," or "below" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0096] The disclosure above provides many different embodiments or examples for realizing different structures of the present invention. In order to simplify the disclosure of the present invention, the components and settings of specific examples are described above. Of course, they are merely examples and are not intended to limit the present invention. In addition, the present invention may repeat reference numerals and / or reference letters in different examples, and such repetition is for the purpose of simplicity and clarity and does not in itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the present invention provides examples of various specific processes and materials, but those skilled in the art will recognize the application of other processes and / or the use of other materials.

Claims

1. A performance testing system for high-temperature anti-oxidation coatings of aerospace engines, characterized in that: The system comprises: The sample testing platform includes a platform body and a sample clamping platform A and a sample clamping platform B. The platform body includes a support base and positioning devices A and B. The positioning devices A and B are arranged on the support base and can move horizontally on the support base. The sample clamping platform A and the sample clamping platform B are respectively fixed to the positioning devices A and B and can move on the support base with the positioning devices A and B. The sample clamping platform A includes a bracket, a clamping device, an upper sample electrode and a lower sample electrode correspondingly arranged above and below, the bracket has a connecting portion connected to the clamping device and a supporting member supporting the lower sample electrode, the clamping device can move up and down in the vertical direction within the connecting portion, the upper sample electrode and the lower sample electrode are arranged between the clamping device and the supporting member, detachable modules are provided at the relative positions of the upper sample electrode and the lower sample electrode, grooves are provided in the opposite surfaces of the detachable modules, and the shapes of the grooves of a pair of the detachable modules match to clamp one end of the sample to be tested, and cooling water pipes are provided inside the upper sample electrode and the lower sample electrode; The sample clamping platform B is symmetrically arranged with the sample clamping platform A to clamp both ends of the sample to be tested; A detection system, the detection system comprising at least a high-precision colorimetric infrared laser thermometer, a complex impedance spectroscopy measuring device, and an acoustic emission detection device disposed within the platform body, the high-precision colorimetric infrared laser thermometer being used to detect the temperature of the sample to be detected and output a temperature signal accordingly, the complex impedance spectroscopy measuring device comprising at least an electrode capable of being connected to the sample to be detected to detect impedance changes in the coating upon oxidation of the sample to be detected and output an impedance change data signal accordingly, and the acoustic emission detection device comprising at least a guide rod capable of being connected to the sample to be detected to detect damage to the surface morphology of the sample to be detected after high-temperature oxidation and output a damage acoustic emission data signal accordingly; A cooling system, the cooling system comprising at least an exhaust fan and a water cooler, the exhaust fan being disposed on the top of the platform body, the water cooler being disposed inside the platform body, the water cooler being connected to the cooling water pipe so that cooling water circulates between the cooling water pipe and the water cooler; a control system capable of receiving the temperature signal and adjusting the current in the upper sample electrode and the lower sample electrode and / or the operating state of the cooling system based on the temperature signal; the control system capable of receiving the impedance change data signal and obtaining information on internal structural changes of the coating of the sample to be tested during a high-temperature oxidation process based on the impedance change data signal; and the control system capable of receiving the damage acoustic data signal and monitoring the generation and / or healing of high-temperature oxidation cracks in the coating of the sample to be tested based on the damage acoustic emission data signal; When in working state, the clamping device is moved so that the sample clamping platform A and the sample clamping platform B respectively clamp the two ends of the sample to be tested. One of the positioning device A and the positioning device B is fixed on the support seat, and the other is movably set on the support seat. When the sample to be tested is deformed by heat, the movably set positioning device can move to offset the deformation of the sample to be tested.

2. The performance testing system for aerospace engine high-temperature anti-oxidation coating according to claim 1, characterized in that: The control system further includes a power controller, which is electrically connected to an external power supply and the upper sample electrode and the lower sample electrode respectively, and is used to adjust the current in the upper sample electrode and the lower sample electrode.

3. The performance testing system for aerospace engine high-temperature anti-oxidation coating according to claim 1, characterized in that: The support seat includes a support seat body, and a slide rail, a slider and a limit block arranged in the support seat body. The slider and the limit block are respectively arranged on the slide rail, the limit block is connected to a fixed positioning device, and the slider is connected to a movably arranged positioning device. The slider can move along the slide rail to realize the displacement of the positioning device.

4. The performance testing system for aerospace engine high-temperature anti-oxidation coating according to claim 1, characterized in that: An insulating member is provided between the upper sample electrode and the clamping device, and another insulating member is provided between the lower sample electrode and the supporting member.

5. The performance testing system for aerospace engine high-temperature anti-oxidation coating according to claim 1, characterized in that: The upper sample electrode, the lower sample electrode and the detachable module are connected by bolts. At least one type of pad is provided in the groove of the detachable module. The pad is detachably connected in the groove. Different types of pads have different shapes to adapt to samples to be tested with different cross-sectional shapes, so that the sample to be tested is fixed between the upper sample electrode and the lower sample electrode.

6. The performance testing system for aerospace engine high-temperature anti-oxidation coating according to claim 1, characterized in that: The control system includes at least a controllable programmer and a touch-screen industrial computer. The controllable programmer is signal-connected to the touch-screen industrial computer. The controllable programmer is signal-connected to the high-precision colorimetric infrared laser thermometer, the exhaust fan and the water cooler respectively. The touch-screen industrial computer is signal-connected to the complex impedance spectroscopy measuring device and the acoustic emission detection device respectively.

7. The performance testing system for aerospace engine high-temperature anti-oxidation coating according to claim 1, characterized in that: The system further comprises: An experimental console comprises a closed chassis, on which an observation element is provided, through which the state of a sample to be tested can be observed.

8. The performance testing system for aerospace engine high-temperature anti-oxidation coating according to claim 7, characterized in that: The experimental console also includes a control module and a display module. The control module is provided with at least an alarm element, an emergency stop element, a power switch and a data acquisition submodule. The data acquisition submodule is used to collect experimental parameters, and the display module is used to at least display the collected experimental parameters.

9. A performance testing method for high-temperature anti-oxidation coatings of aerospace engines, characterized in that: The testing method uses the performance testing system for aerospace engine high-temperature anti-oxidation coating according to any one of claims 1 to 8, and the testing method comprises the following steps: Move the clamping device so that the sample clamping platform A and the sample clamping platform B respectively clamp the two ends of the sample to be tested; One of the positioning device A and the positioning device B is fixed on the support base, and the other is movably arranged on the support base; The upper sample electrode and the lower sample electrode are used to heat the sample to be tested by current, and the sample to be tested is heated to the target temperature according to the preset heating time; Keep the sample to be tested warm according to the preset constant temperature oxidation time, and maintain the temperature within 1°C above or below the target temperature; The experimental parameters of the high-precision colorimetric infrared laser thermometer, complex impedance spectroscopy measurement device, and acoustic emission detection device were obtained and recorded respectively.

10. The performance testing method for aerospace engine high-temperature anti-oxidation coating according to claim 9, characterized in that: The method further comprises: Use electric current to heat the sample to be tested; The experiment is carried out according to the pre-set heating time, holding time and cooling time in the thermal shock cycle process. The sample to be tested is heated to the target temperature and maintained at the target temperature for 15 seconds before cooling down to complete a thermal shock cycle. Repeat the previous step according to the preset number of cycles; The experimental parameters of the high-precision colorimetric infrared laser thermometer, complex impedance spectroscopy measurement device, and acoustic emission detection device were obtained and recorded respectively.

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