Wide temperature range multi-carrier erosion burn combined test system suitable for aero-engine power components

Abstract

This invention relates to a wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components. The purpose of this invention is to simulate the low-temperature, high-temperature, and ultra-high-temperature operating conditions faced by aero-engine power components during service. The joint testing system comprises a multi-carrier erosion and burn-off coupling generation system, a multi-stage high-temperature assessment system, an embedded clamping system, and a solid-phase carrier recovery system. The clamping system is installed within a high-temperature heating chamber. In the multi-carrier erosion and burn-off coupling generation system, a solid-phase carrier module and a liquid-phase mixing module are connected in parallel on the gas delivery pipeline. The burn-off generation module contains, sequentially along the gas flow direction, a gas flow propulsion device, a burn-off material supply system, and a burn-off nozzle. This invention introduces a global heating device to construct an adjustable wide-temperature-range testing range, and also introduces a localized burn-off device to simulate the ultra-high-temperature component damage environment. By adjusting the flow pattern, flow rate, and velocity factor of the multiple carriers, the purpose of assessing the power components is achieved.

Description

Technical Field

[0001] This invention belongs to the field of material performance testing technology, specifically relating to a wide-temperature-range multi-carrier erosion and burn-off joint assessment and testing device suitable for aero-engine power components. Background Technology

[0002] As the most important power source, the impact of aero engines on aircraft performance is self-evident, and their development level reflects a country's industrial strength. Their internal power components often face high-temperature combustion gases and complex heterogeneous coupling effects, leading to various forms of damage. Therefore, variable acceleration testing platforms simulating service conditions have emerged. Damage test results under high and low temperature multi-carrier conditions can effectively verify reliability and stability under actual operating conditions, and have practical significance in the field of damage mechanism research.

[0003] Currently, a series of testing platforms have been established for high-temperature testing of engine components, mainly divided into two categories: multi-level variable screening and fitting measurement devices and global jet wind tunnel acceleration testing platforms. Conventional multi-level variable screening and fitting measurement devices often only consider narrow-range high temperatures and the effects of typical three-phase carriers. The small controlled temperature range means that the testing scope is significantly limited. The assignment of values ​​for typical carriers means that the construction of subsequent experimental models deviates from real conditions. At the same time, there are few reports on high-temperature condensed particle erosion conditions based on combustion products. Global jet wind tunnel acceleration testing platforms have high experimental costs and cannot be used as routine experimental models. Therefore, it is urgent to build a comprehensive damage testing and evaluation system to comprehensively test engine components based on the characteristics of a wide temperature range and multiple carriers. Summary of the Invention

[0004] The purpose of this invention is to simulate the low-temperature, high-temperature, and ultra-high-temperature operating conditions faced by aero-engine power components during service. It employs methods of global heating and localized directional burn-off, while also considering the harsh operating conditions of high-temperature, high-speed, multi-carrier components such as sand, volcanic ash, and other erosive carriers during flight. In particular, it considers the high-temperature condensed particles generated by the components themselves during operation. The invention performs graded damage testing on aero-engine power components (intake fan, compressor blades, turbine blades, combustion chamber wall, and exhaust nozzle), thereby providing a wide-temperature-range multi-carrier erosion burn-off joint testing system suitable for aero-engine power components that combines accuracy and efficiency.

[0005] This invention relates to a wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components, comprising a multi-carrier erosion and burn-off coupling generation system, a multi-stage high-temperature testing system, an embedded clamping system, and a solid carrier recovery system. The multi-stage high-temperature testing system includes a high-temperature heating chamber, heating wires, and ceramic protective material. Heating wires are installed on the inner wall of the high-temperature heating chamber, and the heating wires are covered with ceramic protective material. The embedded clamping system is installed inside the high-temperature heating chamber and includes a six-axis robotic arm and an embedded clamp. The six-axis robotic arm is equipped with a three-dimensional rotational balancing device, and the clamp is installed on the three-dimensional rotational balancing device.

[0006] The multi-carrier erosion and burn-off coupling system includes a solid-phase carrier module, a liquid-phase mixing module, and a burn-off generation module. The outlet of the air compressor is connected to a gas storage device via a pipeline. An airflow delivery pipeline is installed at the outlet of the gas storage device. The solid-phase carrier module and the liquid-phase mixing module are connected in parallel on the airflow delivery pipeline. The solid-phase carrier module includes a large-particle solid-phase reaction device, a simulated secondary erosion debris solid-phase reaction device, a simulated combustion product solid-phase reaction device, and an induction heating device. The large-particle solid-phase reaction device, the simulated secondary erosion debris solid-phase reaction device, and the simulated combustion product solid-phase reaction device are connected in parallel. The large-particle solid-phase reaction device contains large-particle solid material, the simulated secondary erosion debris solid-phase reaction device contains erosion debris, and the simulated secondary erosion debris solid-phase reaction device contains combustion products. The outlets of the large-particle solid-phase reaction device, the simulated secondary erosion debris solid-phase reaction device, and the simulated combustion product solid-phase reaction device are connected to the solid-phase carrier nozzle via a first delivery pipe. An induction heating device is installed on the first delivery pipe.

[0007] The liquid phase mixing module includes a simulated rainwater droplet reaction device, a first type of silicate reaction device, a second type of phosphate reaction device, and a liquid phase mixing device. The simulated rainwater droplet reaction device, the first type of silicate reaction device, and the second type of phosphate reaction device are connected in parallel. The outlets of the simulated rainwater droplet reaction device, the first type of silicate reaction device, and the second type of phosphate reaction device are connected to the inlet of the liquid phase mixing device. The outlet of the liquid phase mixing device is connected to the liquid phase carrier nozzle through a second delivery pipe.

[0008] The burnout generation module includes an airflow propulsion device, a burnout material supply system, and a burnout nozzle. One end of the connecting pipe is connected to the airflow outlet of the airflow propulsion device, and the other end of the connecting pipe is connected to the burnout nozzle. A burnout material supply system is installed on the connecting pipe, and aviation gasoline or aviation kerosene is added inside the burnout material supply system.

[0009] The solid carrier recovery system includes a suction port, a recovery chamber, a negative pressure device, and a solid separation filter element. The suction port is located on the wall of the high-temperature heating chamber and is connected to the recovery chamber. The negative pressure device and the solid separation filter element are installed in the recovery chamber and are connected to the negative pressure device.

[0010] This invention studies the separation of variables under actual working conditions and performs nonlinear fitting, comprehensively considers the influence weight of each damage factor on service life, and completes precise adjustment by controlling the hierarchical transformation of multivariate parameters and coordinating with the robotic arm at the testing end, so that the damage test results can fully match the working conditions of engine components.

[0011] This invention combines a multi-carrier erosion and burn-off coupling system, a multi-stage high-temperature testing system, an embedded clamping system, and a solid-phase carrier recovery system. It innovatively constructs an adjustable wide-temperature testing range using a global heating device. Additionally, a localized burn-off device is introduced to simulate the damage environment of ultra-high-temperature components. A six-axis robotic arm and embedded fixture are used to adjust the erosion-corrosion angle of the sample's curved surface. A real-time monitoring device allows for adjustment of the sample's position during the high-temperature erosion and burn-off process. This invention offers the advantages of simple and precise operation and can meet the requirements for graded damage testing and analysis of aero-engine power components under multi-carrier conditions in high-temperature and high-pressure working environments.

[0012] This invention introduces a global heating device to construct an adjustable wide-temperature range test range, and a localized burn-off device (burn-off generation module) to simulate the damage environment of ultra-high temperature components. The generation end introduces complex multi-carrier coupled damage conditions under high temperature. By adjusting the flow pattern, flow rate, and velocity factor of the multiple carriers, the system aims to assess power components (intake fan, compressor blades, turbine blades, combustion chamber wall, and exhaust nozzle). Simultaneously, nonlinear parameters such as temperature, corrosion, and applied stress are introduced for graded control. A six-axis robotic arm is introduced at the testing end to clamp different components. Furthermore, this assessment system combines real-time monitoring and 3D mapping functions. Damage test results under high and low temperature multi-carrier conditions can effectively verify the reliability and stability under actual working conditions, achieving an innovative breakthrough in the field of corrosion-erosion coupled material performance testing, and further advancing the development of aerospace material performance testing. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall structure of the wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components, applicable to the present invention.

[0014] Figure 2 The diagram shows the structure of the embedded fixture for the sample, with the left image being the top view of the embedded fixture and the right image being the front view of the embedded fixture.

[0015] In the diagram: 1-High-temperature heating chamber, 2-Heating wire, 3-Ceramic protective material, 4-Temperature control panel, 5-Internal temperature sensor, 6-Air compressor, 7-Atmosphere buffer device, 8-Gas storage device, 9-Intelligent gas turbine flow meter, 10-Large particle size solid-phase reaction device, 11-Simulated secondary erosion debris solid-phase reaction device, 12-Simulated combustion product solid-phase reaction device, 13-Induction heating device, 13-1-Induction coil, 14-Simulated rainwater droplet reaction device, 15-Class I silicate reaction device, 1 6-Secondary phosphate reaction apparatus, 17-Liquid phase mixing device, 18-Liquid flow meter, 19-Airflow propulsion device, 20-Burning raw material supply system, 20-1-Gas valve, 21-Burning raw material flow meter, 22-Cooling device, 23-Control system, 24-Solid carrier recovery system, 25-Six-axis robotic arm, 26-Monitoring camera, 27-Three-dimensional rotating balancing device, 28-Embedded fixture, 29-Solid carrier nozzle, 30-Liquid carrier nozzle, 31-Burning nozzle, 32-Suction port, 33-Connecting plate. Detailed Implementation

[0016] Specific Implementation Method 1: This implementation method is applicable to a wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components, including a multi-carrier erosion and burn-off coupling generation system, a multi-stage high-temperature testing system, an embedded clamping system, and a solid carrier recovery system 24. The multi-stage high-temperature testing system includes a high-temperature heating chamber 1, heating wires 2, and ceramic protective material 3. Heating wires 2 are installed on the inner wall of the high-temperature heating chamber 1, and the heating wires 2 are covered with ceramic protective material 3. The embedded clamping system is installed inside the high-temperature heating chamber 1. The embedded clamping system includes a six-axis robotic arm 25 and an (embedded) clamp 28. The six-axis robotic arm 25 is equipped with a cooling device 22 and a three-dimensional rotational balancing device 27. The clamp 28 is installed on the three-dimensional rotational balancing device 27.

[0017] The multi-carrier erosion and burn-off coupling system includes a solid-phase carrier module, a liquid-phase mixing module, and a burn-off generation module. The outlet of the air compressor 6 is connected to the air storage device 8 via a pipeline. An airflow delivery pipeline is installed on the outlet of the air storage device 8. The solid-phase carrier module and the liquid-phase mixing module are connected in parallel on the airflow delivery pipeline. The solid-phase carrier module includes a large-particle-size solid-phase reaction device 10, a simulated secondary erosion debris solid-phase reaction device 11, a simulated combustion product solid-phase reaction device 12, and an induction heating device 13. The large-particle-size solid-phase reaction device 10, the simulated secondary erosion... The solid phase reaction device 11 for debris and the solid phase reaction device 12 for simulated combustion products are connected in parallel. The solid phase reaction device 10 for large particle size contains large particle size solid material. The solid phase reaction device 11 for simulated secondary erosion debris contains erosion debris and the solid phase reaction device 12 for simulated secondary erosion debris contains combustion products. The outlets of the solid phase reaction device 10 for large particle size, the solid phase reaction device 11 for simulated secondary erosion debris, and the solid phase reaction device 12 for simulated combustion products are connected to the solid phase carrier nozzle 29 via a first conveying pipe. An induction heating device 13 is installed on the first conveying pipe.

[0018] The liquid phase mixing module includes a simulated rainwater droplet reaction device 14, a first type of silicate reaction device 15, a second type of phosphate reaction device 16, and a liquid phase mixing device 17. The simulated rainwater droplet reaction device 14, the first type of silicate reaction device 15, and the second type of phosphate reaction device 16 are connected in parallel. The outlets of the simulated rainwater droplet reaction device 14, the first type of silicate reaction device 15, and the second type of phosphate reaction device 16 are connected to the inlet of the liquid phase mixing device 17. The outlet of the liquid phase mixing device 17 is connected to the liquid phase carrier nozzle 30 through a second delivery pipe.

[0019] The burnout generation module includes an airflow propulsion device 19, a burnout raw material supply system 20, and a burnout nozzle 31. One end of the connecting pipe is connected to the airflow outlet of the airflow propulsion device 19, and the other end of the connecting pipe is connected to the burnout nozzle 31. The burnout raw material supply system 20 is provided on the connecting pipe, and aviation gasoline or aviation kerosene is added inside the burnout raw material supply system 20.

[0020] The solid carrier recovery system includes a suction port 32, a recovery chamber 24, a negative pressure device 24-1, and a solid phase separation filter element 24-2. The suction port 32 is opened on the wall of the high-temperature heating chamber 1 and is connected to the recovery chamber 24. The negative pressure device 24-1 and the solid phase separation filter element 24-2 are installed in the recovery chamber 24 and are connected to the negative pressure device 24-1.

[0021] In this embodiment, all sensors involved in the experiment can be integrated, displayed, and controlled in the control system 23. When the ambient temperature end component of the aero-engine air intake does not require heating by the high-temperature heating chamber 1, and the induction heating device 13 is turned off, damage testing of the power components under ambient temperature conditions can be performed.

[0022] This implementation method, based on erosion damage testing under normal temperature conditions, sets up a wide-temperature-range variable-temperature environment. The high-temperature heating chamber door allows for sample clamping and adjustment of the testing device's degrees of freedom. The heating coils within the high-temperature heating chamber can control simulated conditions from room temperature to 800°C. Ceramic protective materials protect the heating coils from damage during multi-carrier erosion. An internal temperature sensor allows for accurate setting of the experimental temperature on the control panel. In ultra-high temperature testing environments above 800°C, to prevent high-temperature oxidation failure of the clamping system, a localized burn-off device is used for ultra-high temperature directional testing. Simultaneously, the high-temperature heating chamber maintains a certain level of ambient temperature.

[0023] This implementation method can meet the damage analysis requirements of erosion and burn-off of aero-engine power components in high-temperature, high-speed, and high-pressure multi-carrier operating environments. It constructs high-temperature condensed-phase particle conditions by selecting and adding combustion product solid carriers and silicate droplets. A six-axis robotic arm and sample embedded fixture can be designed to determine the erosion-burn-off angle of the sample. An additional real-time monitoring device can adjust the sample position during the experiment. This effectively addresses the challenging problem of wide-temperature-range multi-carrier erosion-burn-off coupled damage assessment of aero-engine hot-end power component samples, offering advantages such as ease of operation and precision.

[0024] Specific Implementation Method Two: The difference between this implementation method and Specific Implementation Method One is that a temperature sensor 5 is also installed inside the high-temperature heating chamber 1.

[0025] Specific Implementation Method 3: This implementation method differs from Specific Implementation Method 1 or 2 in that a monitoring camera 26 is installed on the six-axis robotic arm 25.

[0026] This embodiment uses a monitoring camera 26 to monitor the location of erosion and burning in real time, and can also be combined with the control system 23 to perform emergency stop operations.

[0027] Specific Implementation Method Four: This implementation method differs from one of the specific implementation methods one to three in that a pressure gauge 8-1 and a pressure sensor 8-2 are installed on the gas storage device 8.

[0028] Specific Implementation Method 5: This implementation method differs from Specific Implementation Methods 1 to 4 in that an atmosphere buffer device 7 is installed on the pipeline between the air outlet of the air compressor 6 and the air storage device 8.

[0029] Specific Implementation Method Six: This implementation method differs from one of the specific implementation methods one to five in that the induction coil 13-1 of the induction heating device 13 is sleeved outside the first conveying pipe.

[0030] Specific Implementation Method Seven: This implementation method differs from Specific Implementation Methods One to Six in that a water pump 17-1 and a liquid flow meter 18 are installed on the second delivery pipe.

[0031] Specific Implementation Method Eight: This implementation method differs from one of the specific implementation methods one to seven in that a burn-off raw material flow meter 21 is installed on the connecting pipeline between the burn-off raw material supply system 20 and the burn-off nozzle 31.

[0032] Specific Implementation Method Nine: This implementation method differs from Specific Implementation Methods One to Eight in that a dust sensor 24-3 is installed in the recycling chamber 24-1.

[0033] Specific Implementation Method 10: This implementation method differs from Specific Implementation Methods 1 to 9 in that the clamp 28 is a four-jaw chuck.

[0034] Example: This example applies to a wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components. The system includes a multi-carrier erosion and burn-off coupling generation system, a multi-stage high-temperature testing system, an embedded clamping system, and a solid carrier recovery system 24. The multi-stage high-temperature testing system includes a high-temperature heating chamber 1, heating wires 2, and ceramic protective material 3. The high-temperature heating chamber 1 provides a wide-temperature-range condition. Heating wires 2 are installed on the inner wall of the high-temperature heating chamber 1, and the heating wires 2 are covered with ceramic protective material 3. The embedded clamping system is installed inside the high-temperature heating chamber 1. The embedded clamping system includes a six-axis robotic arm 25 and an (embedded) clamp 28. The clamp 28 holds the engine power component under test. The six-axis robotic arm 25 is equipped with a three-dimensional rotational balancing device 27, and the clamp 28 is installed on the three-dimensional rotational balancing device 27.

[0035] The multi-carrier erosion and burn-off coupling system includes a solid-phase carrier module, a liquid-phase mixing module, and a burn-off generation module. The outlet of the air compressor 6 is connected to the gas storage device 8 via a pipeline. An airflow delivery pipeline is installed at the outlet of the gas storage device 8, and a gas turbine flow meter 9 and an airflow regulating valve 9-1 are installed on the airflow delivery pipeline. The solid-phase carrier module and the liquid-phase mixing module are connected in parallel on the airflow delivery pipeline. The solid-phase carrier module includes a large-particle-size solid-phase reaction device 10, a simulated secondary erosion debris solid-phase reaction device 11, a simulated combustion product solid-phase reaction device 12, and an induction heating device 13. The large-particle-size solid-phase reaction device 10, the simulated secondary erosion debris solid-phase... The reaction device 11 and the simulated combustion product solid phase reaction device 12 are connected in parallel. These three solid phase reaction devices (11-13) are equipped with feeding ports 10-1. The large particle size solid phase reaction device 10 contains large particle size solid material, the simulated secondary erosion debris solid phase reaction device 11 contains erosion debris, and the simulated secondary erosion debris solid phase reaction device 11 contains combustion products. The outlets of the large particle size solid phase reaction device 10, the simulated secondary erosion debris solid phase reaction device 11, and the simulated combustion product solid phase reaction device 12 are connected to the solid phase carrier nozzle 29 through the first conveying pipe. The induction coil 13-1 of the induction heating device 13 is sleeved on the first conveying pipe.

[0036] The liquid phase mixing module includes a simulated rainwater droplet reaction device 14, a first type of silicate reaction device 15, a second type of phosphate reaction device 16, and a liquid phase mixing device 17. The simulated rainwater droplet reaction device 14, the first type of silicate reaction device 15, and the second type of phosphate reaction device 16 are connected in parallel. Each of the simulated rainwater droplet reaction device 14, the first type of silicate reaction device 15, and the second type of phosphate reaction device 16 has a liquid inlet 14-1. The liquid outlets of the simulated rainwater droplet reaction device 14, the first type of silicate reaction device 15, and the second type of phosphate reaction device 16 are connected to the liquid inlet of the liquid phase mixing device 17. The liquid outlet of the liquid phase mixing device 17 is connected to the liquid phase carrier nozzle 30 via a second delivery pipe. A water pump 17-1 and a liquid flow meter 18 are installed on the second delivery pipe. The solid phase carrier nozzle 29 and the liquid phase carrier nozzle 30 are adjusted to the position of the test sample through a multi-degree-of-freedom fixing device.

[0037] The burnout generation module is used to construct a localized, directional heating ultra-high temperature environment. The burnout generation module includes an airflow propulsion device 19, a burnout raw material supply system 20, and a burnout nozzle 31. One end of the connecting pipe is connected to the airflow outlet of the airflow propulsion device 19, and the other end of the connecting pipe is connected to the burnout nozzle 31. The burnout raw material supply system 20 is provided on the connecting pipe. Aviation gasoline or aviation kerosene is added inside the burnout raw material supply system 20. The airflow generated by the airflow propulsion device 19 drives the gasoline or kerosene in the burnout raw material supply system 20 into the burnout nozzle 31 and ignites it to form a flame.

[0038] The solid carrier recovery system includes a suction port 32, a recovery chamber 24, a negative pressure device 24-1, and a solid phase separation filter element 24-2. The suction port 32 is opened on the wall of the high-temperature heating chamber 1 and is connected to the recovery chamber 24. The negative pressure device 24-1 and the solid phase separation filter element 24-2 are installed in the recovery chamber 24 and are connected to the negative pressure device 24-1. The bottom of the recovery chamber 24 is the recovery chamber 24-4.

[0039] In this embodiment, the six-axis robotic arm 25 is connected to the clamp 28 via the three-dimensional rotational balancing device 27 and the connecting plate 33. The clamp 28 is a four-jaw chuck. In a closed high-temperature environment, the six-axis robotic arm 25 is ensured to operate normally by the cooling device 22. In addition, the real-time monitoring camera 26 is used to monitor the location of erosion and burning.

[0040] In this embodiment, the multi-carrier erosion and burn-off coupling test system draws in air from the air compressor 6, which is connected to the gas storage device 8 via the atmosphere buffer device 7. During the experiment, the connecting pipeline valve is opened, and the gas flow rate is adjusted by the gas turbine flow meter 9 on the pipeline. Multi-component solid carriers are added through the feeding port 10-1. Based on the analysis of actual working conditions, they are added as needed to the large particle size solid phase reaction device 10, the simulated secondary erosion debris solid phase reaction device 11, and the simulated combustion product solid phase reaction device 12. The solid carriers can be preheated by the induction heating device 13 and then fed into the solid carrier nozzle 29.

[0041] Liquid carriers are added as needed to the simulated rainwater droplet reaction device 14, the first type of silicate reaction device 15, and the second type of phosphate reaction device 16. Salt spray droplets or water droplets are drawn in by the mixing container water pump 17-1 and sent into the liquid carrier nozzle 30 by the high-pressure atmosphere in the pipeline. The solid carrier nozzle 29 and the liquid carrier nozzle 30 are adjusted to the position of the test sample by a multi-degree-of-freedom fixing device.

[0042] Gasoline or kerosene is added to the burn-off material supply system 20. The high-pressure environment created by the protective gas inside the device 19, propelled by airflow, is used to control the ablation conditions via the burn-off material flow meter 21, constructing a localized, directional, ultra-high temperature heating environment. The heating temperature range of the heating element 2 is controlled via the temperature control panel 4, creating a wide temperature range test range in the high-temperature heating chamber 1. Combined with the temperature sensor 5 inside the chamber, the actual temperature range can be displayed. Based on the comprehensive insulation conditions provided by the high-temperature heating chamber 1, the ultra-high temperature directional test is completed using the localized heating device through the burn-off nozzle 31. The angle and position between the six-axis robotic arm 25 and the solid-phase carrier nozzle 29 and liquid-phase carrier nozzle 30 are adjusted via the control system 23. Combined with the real-time monitoring device 26, the location of erosion and burn-off is adjusted in real time. After the experiment, dust is collected by the dust removal device 24 and enters the recovery system. The system's negative pressure device 24-1 creates a negative pressure atmosphere, causing the solid-phase carrier to move towards the solid-phase separation filter element 24-2. Finally, the solid-phase carrier is graded and recovered through filter elements of different pore sizes.

[0043] The particles added to the solid phase carrier module in this embodiment are mainly: solid hard particles (Al2O3 or SiO2), erosion debris simulating the front-end components, micro carbides generated in the combustion chamber simulating combustion, abnormal solid particles generated by rich oil combustion, small-diameter soot particles and other combustion product particles. Each solid phase reaction vessel is controlled by a separate valve to prevent contamination. The salts added to the liquid phase mixing module are mainly divided into two categories: silicates and phosphates. Silicates and phosphates simulate the CMAS erosion failure conditions faced by aero engines and the service environment of carrier-based aircraft. They can be converted from high-pressure atmosphere into small droplets and injected from the liquid phase carrier nozzle 30.

[0044] The induction heating device designed for the solid support module is used for preheating the solid support before the experiment, and its heating range is from room temperature to 200℃. The solid support nozzle 28 and the liquid support nozzle 29 together constitute a multi-support test generator, and its nozzle can rotate 180° to meet the requirements of different erosion angles of the sample.

[0045] The high-temperature heating chamber 1 is operated via the temperature control panel 4. The heating element 2 has a heating temperature range of 0-900℃. Due to the presence of the ceramic protective material 3, the actual heating temperature is below 900℃. The actual temperature range can be displayed by the temperature sensor 5 inside the chamber, and the actual temperature should be above 800℃. The ultra-high temperature environment provided by the localized burn-off device is controlled by the combustion carrier within the ultra-high temperature range.

[0046] Under the harsh operating conditions of high temperature, high speed, and high pressure, the high-temperature heating chamber 1 of this invention serves as an experimental platform and a comprehensive high-temperature heating environment. The heating temperature range of the heating wires 2 is controlled via the temperature control panel 4, creating a wide temperature range for testing. In ultra-high temperature testing environments, based on the comprehensive insulation conditions provided by the high-temperature heating chamber 1, ultra-high temperature directional testing is completed using a localized heating device through a burn-out nozzle 31.

[0047] This invention constructs an adjustable test range through a global heating device and simulates the damage environment of ultra-high temperature components through a localized burn-out device, ultimately achieving the construction of wide-temperature-range damage conditions.

Claims

1. A wide-temperature-range multi-carrier erosion and burn-off joint testing system suitable for aero-engine power components, characterized in that... The wide-temperature-range multi-carrier erosion and burn-off joint testing system includes a multi-carrier erosion and burn-off coupling generation system, a multi-level high-temperature assessment system, an embedded clamping system, and a solid carrier recovery system (24). The multi-level high-temperature assessment system includes a high-temperature heating chamber (1), heating wires (2), and ceramic protective material (3). Heating wires (2) are installed on the inner wall of the high-temperature heating chamber (1), and the heating wires (2) are covered with ceramic protective material (3). The embedded clamping system is installed inside the high-temperature heating chamber (1). The embedded clamping system includes a six-axis robotic arm (25) and a clamp (28). The six-axis robotic arm (25) is equipped with a three-dimensional rotational balancing device (27), and the clamp (28) is installed on the three-dimensional rotational balancing device (27). The multi-carrier erosion and burn-off coupling generation system includes a solid-phase carrier module, a liquid-phase mixing module, and a burn-off generation module. The outlet of the air compressor (6) is connected to the gas storage device (8) via a pipeline. An airflow delivery pipeline is provided on the outlet of the gas storage device (8). The solid-phase carrier module and the liquid-phase mixing module are connected in parallel on the airflow delivery pipeline. The solid-phase carrier module includes a large-particle-size solid-phase reaction device (10), a simulated secondary erosion debris solid-phase reaction device (11), a simulated combustion product solid-phase reaction device (12), and an induction heating device (13). The large-particle-size solid-phase reaction device (10), the simulated secondary erosion debris... The solid phase reaction device (11) and the simulated combustion product solid phase reaction device (12) are connected in parallel. The large particle size solid phase reaction device (10) contains large particle size solid material, the simulated secondary erosion debris solid phase reaction device (11) contains erosion debris, and the simulated secondary erosion debris solid phase reaction device (11) contains combustion products. The outlets of the large particle size solid phase reaction device (10), the simulated secondary erosion debris solid phase reaction device (11), and the simulated combustion product solid phase reaction device (12) are connected to the solid phase carrier nozzle (29) through the first conveying pipe. An induction heating device (13) is installed on the first conveying pipe. The liquid phase mixing module includes a simulated rainwater droplet reaction device (14), a first type of silicate reaction device (15), a second type of phosphate reaction device (16), and a liquid phase mixing device (17). The simulated rainwater droplet reaction device (14), the first type of silicate reaction device (15), and the second type of phosphate reaction device (16) are connected in parallel. The outlets of the simulated rainwater droplet reaction device (14), the first type of silicate reaction device (15), and the second type of phosphate reaction device (16) are connected to the inlet of the liquid phase mixing device (17). The outlet of the liquid phase mixing device (17) is connected to the liquid phase carrier nozzle (30) through a second conveying pipe. The burnout generation module includes an airflow propulsion device (19), a burnout raw material supply system (20), and a burnout nozzle (31). One end of the connecting pipe is connected to the airflow outlet of the airflow propulsion device (19), and the other end of the connecting pipe is connected to the burnout nozzle (31). A burnout raw material supply system (20) is provided on the connecting pipe. Aviation gasoline or aviation kerosene is added inside the burnout raw material supply system (20). The solid carrier recovery system includes a suction port (32), a recovery chamber, a negative pressure device (24-1), and a solid phase separation filter element (24-2). The suction port (32) is opened on the wall of the high-temperature heating chamber (1) and is connected to the recovery chamber. The negative pressure device (24-1) and the solid phase separation filter element (24-2) are installed in the recovery chamber and are connected to the negative pressure device (24-1).

2. The wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components according to claim 1, characterized in that... A temperature sensor (5) is also installed inside the high-temperature heating chamber (1).

3. The wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components according to claim 1, characterized in that... A monitoring camera (26) is installed on the six-axis robotic arm (25).

4. The wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components according to claim 1, characterized in that... A pressure gauge (8-1) and a pressure sensor (8-2) are installed on the gas storage device (8).

5. The wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components according to claim 1, characterized in that... An atmosphere buffer device (7) is installed on the pipeline between the outlet of the air compressor (6) and the air storage device (8).

6. The wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components according to claim 1, characterized in that... The induction coil (13-1) of the induction heating device (13) is sleeved outside the first delivery pipe.

7. The wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components according to claim 1, characterized in that... A water pump (17-1) and a liquid flow meter (18) are installed on the second delivery pipe.

8. The wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components according to claim 1, characterized in that... A burnout material flow meter (21) is installed on the connecting pipeline between the burnout material supply system (20) and the burnout nozzle (31).

9. The wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components according to claim 1, characterized in that... Dust sensors (24-3) are installed in the recycling room.

10. The wide-temperature-range multi-carrier erosion and burn-off joint testing system for aero-engine power components according to claim 1, characterized in that... The clamp (28) is a four-jaw chuck.

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