A ceramic matrix composite turbine blade thermal fatigue test system

Abstract

The application belongs to the field of turbine blade design of an aero-engine, and relates to a ceramic matrix composite turbine blade thermal fatigue test system, which comprises a high-temperature gas output system, an adapter section, a test cascade, a secondary flow system, an exhaust section and a test and data acquisition system; the adapter section is connected between the high-temperature gas output system and the test cascade; the high-temperature gas output system can output high-temperature and low-temperature gas; and the test cascade is designed to be closed at the inside and outside; during the test, the high-temperature gas output system is used for outputting gas with temperature periodic change into the adapter section; the gas in the adapter section is input into the test blade of the test cascade; meanwhile, the secondary flow system introduces cold gas with certain temperature, pressure and flow into the test blade of the test cascade; the internal and external flow field simulation of the real working state of the ceramic matrix composite turbine blade is realized; the blade is ensured to be subjected to complete thermal stress; and the problem that the blade is only subjected to thermal stress generated by the temperature field change of the outer surface is solved.

Description

Technical Field

[0001] This application belongs to the field of aero-engine turbine blade design, and specifically relates to a thermal fatigue testing system for ceramic matrix composite turbine blades. Background Technology

[0002] The inlet air temperature of next-generation aero-engine turbines will reach 2100–2300K, and current turbine blade materials and cooling technologies are insufficient to ensure stable operation at this temperature. Ceramic matrix composites possess advantages such as high temperature resistance, low density, and oxidation resistance, meeting the material requirements of next-generation aero-engine turbine guide vanes. Aero-engines operate under various conditions, causing significant variations in the ambient temperature of turbine blades, leading to thermal fatigue. Therefore, thermal fatigue testing must be conducted before the engineering application of ceramic matrix composite turbine blades.

[0003] Currently, there are two methods for testing the thermal fatigue of ceramic matrix composite turbine blades:

[0004] (1) Flame flow heating test method: A fixture is designed to fix the ceramic matrix composite turbine blade. The blade surface is directly heated by chemical fuel combustion. The thermal fatigue effect of high and low temperature cycles is achieved by adjusting the amount of fuel.

[0005] (2) Radiation heating test method: A fixture is designed to fix the ceramic matrix composite turbine blade, and the blade is radiated and heated by a high-power quartz lamp or a high-temperature metal substrate until the surface reaches the test temperature. By adjusting the power or temperature of the radiation source and assisting with the blowing of low-temperature compressed air on the surface, the thermal fatigue effect of high and low temperature cycles is achieved.

[0006] These two testing methods only simulate high- and low-temperature cyclic thermal fatigue on the surface of ceramic matrix composite turbine blades, and cannot simulate the external surface flow field environment of turbine blades during actual operation. Furthermore, the lack of cooling air flow inside the blades means that internal flow field conditions are missing, failing to simulate all the thermal stresses experienced by the blades and thus unable to accurately assess their thermal fatigue resistance. Therefore, it is necessary to design a thermal fatigue testing system for ceramic matrix composite blades that can simulate the actual operating conditions of aero-engines. Summary of the Invention

[0007] The purpose of this application is to provide a thermal fatigue testing system for ceramic matrix composite turbine blades, in order to solve the problem that existing thermal fatigue tests for ceramic matrix composite turbine blades are difficult to simulate their actual working conditions.

[0008] The technical solution of this application is: a thermal fatigue testing system for ceramic matrix composite turbine blades, comprising a high-temperature gas output system, a transition section, a test blade cascade, a secondary flow system, an exhaust section, and a testing and data acquisition system; the transition section is connected between the high-temperature gas output system and the test blade cascade, the high-temperature gas output system is capable of outputting high and low temperature gas, which is input to the test blade cascade through the transition section, the test blade cascade is an internally and externally sealed design, the output end of the secondary flow system is capable of inputting cold air into the interior of the test blade cascade, the exhaust section is connected to the rear of the test blade cascade, the exhaust section is capable of receiving the gas after it has passed through the test blade cascade, and the testing and data acquisition system includes various measuring devices capable of collecting test data from the high-temperature gas output system, the transition section, the test blade cascade, the secondary flow system, and the exhaust section.

[0009] Preferably, the test blade cascade includes a CMC blade, a blade sealing device, a liner, an inlet support plate, and an exhaust support plate; the inlet support plate is located between the CMC blade and the transition section, and has an inlet groove in the middle that communicates with the transition section; a high-temperature fiber optic observation window is provided between the inlet support plate and the transition section; the exhaust support plate is located between the CMC blade and the exhaust section, and has an exhaust groove in the middle that communicates with the exhaust section; the liner includes a first liner and a second liner, the first liner and the second liner... The liner bodies are respectively disposed on both sides of the CMC blade and clamp the CMC blade. The blade sealing device includes a fixing device, a top plate, a bottom plate, a side plate, an upper cover plate, and a lower cover plate. The fixing device is fixedly connected to the middle of the CMC. There are two sets of side plates, which are respectively fixedly connected to the outside of the first liner body and the second liner body. The top plate is fixedly connected above the liner body and the side plate. The bottom plate is fixedly connected below the liner body and the side plate. The upper cover plate is disposed above the top plate, and the lower cover plate is disposed below the bottom plate.

[0010] Preferably, a first cold air inlet pipe is provided between the lower cover plate and the fixing device, the first cold air inlet pipe is connected to the secondary flow system, a second cold air inlet pipe is provided between the upper cover plate and the fixing device, the bottom of the first liner is provided with multiple sets of first cooling channels communicating with the first cold air inlet pipe, the bottom of the second liner is provided with multiple sets of second cooling channels, and the first cooling channel (39) and the second cooling channel are both connected to the interior of the CMC blade.

[0011] Preferably, the first liner body has a first mating groove on its side wall that engages with the CMC blade, and the second liner body has a second mating groove on its side wall that engages with the CMC blade; a support plate is provided between the intake support plate and the CMC blade, and a fixing bolt is provided between the support plate and the intake support plate; a square gasket is provided at one end of the support plate near the CMC blade, and the square gasket is fitted onto the inner side wall of the CMC blade; the support plate, the square gasket, and the CMC blade are connected by the fixing bolt; an arc-shaped support strip is provided between the CMC blade and the exhaust section.

[0012] Preferably, the transition section includes a test base and a first cooling water channel. The test base is provided with an outer air intake cavity and an inner air intake cavity. The inner air intake cavity can receive the gas output by the high-temperature gas output system. The test base is provided with a gas temperature probe and a gas pressure probe, which are inserted into the inner air intake cavity. There are multiple sets of the first cooling water channel, which are located at both ends of the test base. The first cooling water channel is connected to the outer air intake cavity.

[0013] Preferably, the high-temperature gas output system includes a compressed air control system, a fuel control system, and a combustion chamber; the compressed air control system is used to output compressed air into the transition section, the combustion chamber is used to output fuel into the transition section, and the fuel control system is used to control the amount of fuel in the combustion chamber.

[0014] The secondary flow system includes a test control module, electric heaters, and pipelines. There are two sets of electric heaters arranged side by side. The two sets of electric heaters are connected to the compressed air control system through pipelines, and a flow monitor is provided between the electric heaters and the compressed air control system. There are two sets of test control modules, which are electrically connected to the two sets of electric heaters respectively. A pressure monitor and a temperature monitor are provided between the electric heaters and the test blades. The electric heaters are also provided with venting branches.

[0015] Preferably, the exhaust section is provided with an inner exhaust cavity and an outer exhaust cavity. The inner exhaust cavity is connected to the interior of the test blade grating. A second cooling water channel is connected to the outer exhaust cavity. A cooling section is provided at the rear end of the exhaust section. A spray head capable of spraying high-pressure water is provided in the cooling section. A back pressure regulating valve is provided at the rear end of the cooling section.

[0016] This application discloses a thermal fatigue testing system for ceramic matrix composite turbine blades, comprising a high-temperature gas output system, a transition section, a test blade cascade, a secondary flow system, an exhaust section, and a testing and data acquisition system. The transition section connects the high-temperature gas output system and the test blade cascade. The high-temperature gas output system can output high- and low-temperature gas and input it to the test blade cascade through the transition section. The test blade cascade has an internally and externally enclosed design. During the test, the high-temperature gas output system outputs gas with periodically changing temperature into the transition section. The gas in the transition section is input into the test blade of the test blade cascade. At the same time, the secondary flow system introduces cold air with a certain temperature, pressure, and flow rate into the test blade of the test blade cascade, thereby simulating the flow field of the real working state of the ceramic matrix composite turbine blade. This ensures that the blade is subjected to complete thermal stress, solving the problem that the blade is only subjected to thermal stress generated by the temperature field change of the outer surface. Attached Figure Description

[0017] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0018] Figure 1 This is a schematic diagram of the overall process of this application;

[0019] Figure 2 This is a schematic diagram of the cross-sectional structure of the test blade cascade in this application;

[0020] Figure 3 This is a schematic diagram of the connection structure between the test blade cascade, the transition section, and the exhaust section of this application;

[0021] Figure 4 ① is the front view of the first supporting body; ② is the side view of the first supporting body; ③ is the transverse sectional view of the front view of the first supporting body.

[0022] Figure 5 ① is the front view of the second embellishment, ② is the rear view of the second embellishment, and ③ is a cross-sectional schematic diagram of the front view AA of the second embellishment.

[0023] Figure 6 This is a schematic diagram of the transition section structure in this application;

[0024] Figure 7 This is a schematic diagram of the connection structure between the intake support plate and the CMC blade in this application;

[0025] Figure 8 This is a schematic diagram of the overall structure of the secondary flow system in this application;

[0026] Figure 9 This is a schematic diagram of the overall structure of the exhaust section in this application.

[0027] 1. Fuel control system; 2. Combustion chamber; 3. Compressed air control system; 4. Adapter section; 5. Test blade cascade; 6. Exhaust section; 7. Test and data acquisition system; 8. Side plate; 9. First liner; 10. Second liner; 11. Top cover plate; 12. Top plate; 13. Fixing device; 14. Lower cover plate; 15. CMC blade; 16. Base plate; 17. High-temperature fiber optic observation window; 18. Intake support plate; 19. Exhaust support plate; 20. Support plate; 21. Fixing bolt; 22. Square gasket; 23. Test seat; 24. 25. First cooling water chamber; 26. Intake chamber; 27. Intake chamber; 28. Gas temperature probe; 29. ​​Gas pressure probe; 30. Test control module; 31. Electric heater; 32. Flow monitor; 33. Pressure monitor; 34. Temperature monitor; 35. Exhaust chamber; 36. Exhaust chamber; 37. Second cooling water chamber; 38. Cooling section; 39. Back pressure regulating valve; 40. First cooling channel; 41. Second cooling channel; 42. First mating groove; 43. Second mating groove; 44. Arc-shaped support bar. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0029] A thermal fatigue testing system for ceramic matrix composite turbine blades, such as Figure 1 As shown, the system includes a high-temperature gas output system, a transition section 4, a test blade 5, a secondary flow system, an exhaust section 6, and a testing and data acquisition system 7. The transition section 4 connects the high-temperature gas output system and the test blade 5. The high-temperature gas output system can output high and low temperature gas, which is then input to the test blade 5 through the transition section 4. The test blade 5 has an internally and externally enclosed design. The output end of the secondary flow system can input cold air into the test blade 5. The exhaust section 6 is connected to the rear of the test blade 5 and can receive the gas after it has passed through the test blade 5. The testing and data acquisition system 7 includes various measuring devices and can collect test data from the high-temperature gas output system, the transition section 4, the test blade 5, the secondary flow system, and the exhaust section 6.

[0030] Based on the blade profile, a specific transition section 4 and experimental blade cascade 5 are designed to simulate the flow field under the actual working conditions of ceramic matrix composite turbine blades.

[0031] During the test, the high-temperature gas output system outputs gas with periodically changing temperature into the transition section 4. The gas in the transition section 4 is then input into the test blade of the test blade cascade 5. At the same time, the secondary flow system introduces cold air with a certain temperature, pressure, and flow rate into the test blade of the test blade cascade 5. This simulates the flow field under the real working condition of the ceramic matrix composite turbine blade, ensuring that the blade is subjected to complete thermal stress. This solves the problem that the blade is only subjected to thermal stress generated by the change of temperature field on the outer surface. It can more realistically assess the blade's resistance to thermal fatigue and provide experimental support for the engineering application of ceramic matrix composite turbine blades.

[0032] During the operation of the test blade cascade 5, the working parameters of the test blade cascade 5 are collected in real time by the test and data acquisition system 7, thereby judging and assessing the blade's ability to resist thermal fatigue. The gas input into the test blade cascade 5 is then output through the exhaust section 6.

[0033] like Figure 2-3 As shown, preferably, the test blade cascade 5 includes a CMC blade 15, a blade sealing device, a liner, an inlet support plate 18, and an exhaust support plate 19. The inlet support plate 18 is located between the CMC blade 15 and the transition section 4. The inlet support plate 18 has an inlet groove in its middle that communicates with the transition section 4. A high-temperature fiber optic observation window 17 is located between the inlet support plate 18 and the transition section 4. The high-temperature fiber optic observation window 17 is connected to the testing and data acquisition system for real-time observation of the temperature inside the CMC blade 15. The exhaust support plate 19 is located between the CMC blade 15 and the exhaust section 6. The exhaust support plate 19 has an exhaust groove in its middle that communicates with the exhaust section 6. The exhaust section 6 is connected to the rear end of the CMC blade 15. The inlet angle between the inlet support plate 18 and the transition section 4 (e.g., ...) is... Figure 3 ①) The exhaust angle between the exhaust support plate 19 and the exhaust section 6 (e.g.) Figure 3 ②) Design according to the working state of CMC blade 15 to ensure that the high-temperature gas flow direction on the outer surface of the blade is the same as that of the engine.

[0034] The liner includes a first liner 9 and a second liner 10. The first liner 9 and the second liner 10 are respectively disposed on both sides of the CMC blade 15 and clamp the CMC blade 15. The blade sealing device includes a fixing device 13, a top plate 12, a bottom plate 16, a side plate 8, an upper cover plate 11, and a lower cover plate 14.

[0035] The fixing device 13 is fixedly connected to the middle of the CMC. There are two sets of side plates 8, which are fixedly connected to the outside of the first liner 9 and the second liner 10 respectively. The top plate 12 is fixedly connected to the liner and the side plate 8 above. The bottom plate 16 is fixedly connected to the liner and the side plate 8 below. The upper cover plate 11 is located above the top plate 12, and the lower cover plate 14 is located below the bottom plate 16.

[0036] The fixing device 13, top plate 12, bottom plate 16, side plate 8, upper cover plate 11 and lower cover plate 14 work together to seal the CMC blade 15. The flow section of the blade cascade is the same as the assembly fan surface of the engine blade to ensure that the flow state of the high temperature gas remains unchanged.

[0037] Combination Figure 4-5 Preferably, a first cold air inlet pipe is provided between the lower cover plate 14 and the fixing device 13, and the first cold air inlet pipe is connected to the secondary flow system. A second cold air inlet pipe is provided between the upper cover plate 11 and the fixing device 13. The bottom of the first liner 9 is provided with multiple sets of first cooling channels 39 communicating with the first cold air inlet pipe, and the bottom of the second liner 10 is provided with multiple sets of second cooling channels 40. The first cooling channels 39, the second cooling channels 40, and the second cold air inlet pipe are all connected to the interior of the CMC blade 15. The design of the cooling structure ensures that the first liner 9 and the second liner 10 operate normally in a high-temperature gas environment.

[0038] Preferably, the first liner 9 has a first mating groove 41 on its side wall that engages with the CMC blade 15, and the second liner 10 has a second mating groove 42 on its side wall that engages with the CMC blade 15; both the first mating groove 41 and the second mating groove 42 are blade-shaped structures so as to be compatible with both sides of the CMC blade 15.

[0039] Due to the limitations of CMC blades (15 grade) such as poor toughness, susceptibility to damage, and inability to weld insulation, a novel blade fixing structure is designed, combining... Figure 7 Specifically, a support plate 20 is provided between the intake support plate 18 and the CMC blade 15, and a fixing bolt 21 is provided between the support plate 20 and the intake support plate 18. A square gasket 22 is provided at one end of the support plate 20 near the CMC blade 15. The square gasket 22 is made of high-temperature resistant flexible material and is fitted onto the inner wall of the CMC blade 15. The support plate 20, the square gasket 22, and the CMC blade 15 are connected by the fixing bolt 21. An arc-shaped support strip 43 is provided between the CMC blade 15 and the exhaust section 6. Through the combined design of the support plate 20, the square gasket 22, and the fixing bolt 21, the ceramic matrix composite blade is stably installed in the test blade cascade 5 channel, ensuring that the blade does not suffer damage beyond the thermal shock test assessment during the test. At the same time, the installation structure is easy to disassemble and disassemble, and is easy to periodically disassemble and inspect during the test.

[0040] like Figure 6As shown, preferably, the transition section 4 includes a test base 23 and a first cooling water channel 24. The test base 23 has an outer air intake cavity 26 and an inner air intake cavity 25. The inner air intake cavity 25 can receive the gas output from the high-temperature gas output system. The test base 23 is equipped with a gas temperature probe 27 and a gas pressure probe 28, which are inserted into the inner air intake cavity 25. There are multiple sets of the first cooling water channel 24, which are located at both ends of the test base 23 and are connected to the outer air intake cavity 26. When high-temperature gas is introduced into the inner air intake cavity 25, cooling water is introduced into the outer air intake cavity 26 to protect the inner cavity. The gas temperature probe 27 and the gas pressure probe 28 are electrically connected to the test and data acquisition system 7, which can monitor the temperature and pressure of the gas during the test.

[0041] In summary, the designed test blade cascade 5 can control the following parameters: gas temperature, pressure, flow rate, Mach number, gas flow cross section, and angle, thereby simulating the external flow field environment of the CMC blade 15 under real engine conditions.

[0042] Preferably, the high-temperature gas output system includes a compressed air control system 3, a fuel control system 1, and a combustion chamber 2; the compressed air control system 3 is used to output compressed air into the transition section 4, the combustion chamber 2 is used to output fuel into the transition section 4, and the fuel control system 1 is used to control the amount of fuel in the combustion chamber 2. By controlling and changing the flow rates of fuel and compressed air, periodically varying high and low temperature gas is provided.

[0043] Combination Figure 8 The secondary flow system includes a test control module 29, an electric heater 30, and pipelines. There are two sets of electric heaters 30 arranged side by side. The two sets of electric heaters 30 are connected to the compressed air control system 3 through pipelines. A flow monitor 31 is provided between the electric heater and the compressed air control system 3. There are two sets of test control modules, which are electrically connected to the two sets of electric heaters 30 respectively. A pressure monitor 32 and a temperature monitor 33 are provided between the electric heaters 30 and the test blade 5. An air vent branch is also provided on the electric heaters 30.

[0044] By controlling the power of the electric heater through the test control module 29, and cooperating with the compressed air control system 3 to provide the required cooling air, the CMC blade 15 can be provided with specific flow rate, temperature and pressure of cooling air in the blade cavity during the thermal fatigue test according to the actual working state of the CMC blade 15, so as to ensure that the CMC blade 15 can withstand the full thermal stress during the test.

[0045] Combination Figure 9Preferably, the exhaust section 6 is provided with an exhaust inner cavity 34 and an exhaust outer cavity 35. The exhaust inner cavity 34 is connected to the interior of the test blade 5. The exhaust outer cavity 35 is connected to a second cooling water channel 36. The exhaust section 6 is provided with a cooling section 37 at its rear end. The cooling section 37 is provided with a spray head that can spray high-pressure water. The spray head is connected to a cooling water pipe. The cooling section 37 is provided with a back pressure regulating valve 38 at its rear end.

[0046] The exhaust chamber 34 draws high-temperature combustion gas from the outlet of the test blade 5 and introduces cooling water from the exhaust chamber 35 to ensure that the exhaust chamber 34, through the spray head, sprays high-pressure water in the cooling section 37 area to reduce the combustion gas temperature and protect the back pressure regulating valve 38. During the test, the pressure at the outlet section of the test blade 5 is regulated by controlling the opening of the back pressure regulating valve 38, thereby ensuring that the high-temperature combustion gas flow state on the outer surface of the CMC blade 15 is the same as the actual working state.

[0047] The testing and data acquisition system 7 includes a temperature measuring instrument, a pressure scanning valve, a high-temperature fiber optic temperature measuring device, and the KingSCADA software system. The high-temperature fiber optic observation window 17 is connected to the high-temperature fiber optic temperature measuring device. The temperature measuring instrument and pressure scanning valve are respectively located on the high-temperature gas output system, the transition section 4, the test blade cascade 5, the secondary flow system, and the exhaust section 6, used to collect test data such as temperature, pressure, and flow rate of each system, surface wall temperature of the CMC blade 15, flow rate, temperature, and pressure of the cold air flowing inside the blade, test time, and number of cycles. The KingSCADA software system is an existing system used to process the cold air flow rate, temperature, and pressure data, and to send control signals to the fuel control system 1 and the compressed air control system 3.

[0048] The above are merely specific embodiments of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A thermal fatigue testing system for ceramic matrix composite turbine blades, characterized in that: The system includes a high-temperature gas output system, a transfer section (4), a test blade grid (5), a secondary flow system, an exhaust section (6), and a test and data acquisition system (7). The transfer section (4) is connected between the high-temperature gas output system and the test blade grid (5). The high-temperature gas output system can output high and low temperature gas and input it into the test blade grid (5) through the transfer section (4). The test blade grid (5) is designed with internal and external closure. The output end of the secondary flow system can input cold air into the test blade grid (5). The exhaust section (6) is connected to the rear of the test blade grid (5). The exhaust section (6) can receive the gas after passing through the test blade grid (5). The test and data acquisition system (7) includes a variety of measuring devices and can collect test data from the high-temperature gas output system, the transfer section (4), the test blade grid (5), the secondary flow system, and the exhaust section (6). The test blade cascade (5) includes a CMC blade (15), a blade sealing device, a liner, an inlet support plate (18), and an exhaust support plate (19); the inlet support plate (18) is located between the CMC blade (15) and the transition section (4), and the inlet support plate (18) has an inlet groove in the middle that communicates with the transition section (4), and a high-temperature fiber optic observation window (17) is located between the inlet support plate (18) and the transition section (4); the exhaust support plate (19) is located between the CMC blade (15) and the exhaust section (6), and the exhaust support plate (19) has an exhaust groove in the middle that communicates with the exhaust section (6); the liner includes a first liner (9) and a second liner (10), the first liner (9) and the second liner (10) being divided into The blade sealing device is located on both sides of the CMC blade (15) and clamps the CMC blade (15). The blade sealing device includes a fixing device (13), a top plate (12), a bottom plate (16), a side plate (8), an upper cover plate (11), and a lower cover plate (14). The fixing device (13) is fixedly connected to the middle of the CMC blade (15). There are two sets of side plates (8) which are fixedly connected to the outside of the first liner (9) and the second liner (10) respectively. The top plate (12) is fixedly connected above the liner and the side plate (8). The bottom plate (16) is fixedly connected below the liner and the side plate (8). The upper cover plate (11) is located above the top plate (12), and the lower cover plate (14) is located below the bottom plate (16). A first cold air inlet pipe is provided between the lower cover plate (14) and the fixing device (13), and the first cold air inlet pipe is connected to the secondary flow system. A second cold air inlet pipe is provided between the upper cover plate (11) and the fixing device (13). The bottom of the first liner (9) is provided with multiple sets of first cooling channels (39) that communicate with the first cold air inlet pipe. The bottom of the second liner (10) is provided with multiple sets of second cooling channels (40). The first cooling channels (39) and the second cooling channels (40) are both connected to the interior of the CMC blade (15).

2. The ceramic matrix composite turbine blade thermal fatigue testing system as described in claim 1, characterized in that: The first liner (9) has a first mating groove (41) on its side wall that engages with the CMC blade (15), and the second liner (10) has a second mating groove (42) on its side wall that engages with the CMC blade (15). A support plate (20) is provided between the intake support plate (18) and the CMC blade (15), and a fixing bolt (21) is provided between the support plate (20) and the intake support plate (18). A square gasket (22) is provided at one end of the support plate (20) near the CMC blade (15), and the square gasket (22) is fitted onto the inner side wall of the CMC blade (15). The support plate (20), the square gasket (22), and the CMC blade (15) are connected by the fixing bolt (21). An arc-shaped support strip (43) is provided between the CMC blade (15) and the exhaust section (6).

3. The ceramic matrix composite turbine blade thermal fatigue testing system as described in claim 1, characterized in that: The transition section (4) includes a test base (23) and a first cooling water channel (24). The test base (23) is provided with an air intake outer cavity (26) and an air intake inner cavity (25). The air intake inner cavity (25) can receive the gas output by the high-temperature gas output system. The test base (23) is provided with a gas temperature probe (27) and a gas pressure probe (28). The gas temperature probe (27) and the gas pressure probe (28) are inserted into the air intake inner cavity (25). There are multiple sets of the first cooling water channel (24) and they are located at both ends of the test base (23). The first cooling water channel (24) is connected to the air intake outer cavity (26).

4. The ceramic matrix composite turbine blade thermal fatigue testing system as described in claim 1, characterized in that: The high-temperature gas output system includes a compressed air control system (3), a fuel control system (1), and a combustion chamber (2); the compressed air control system (3) is used to output compressed air into the transition section (4), the combustion chamber (2) is used to output gas into the transition section (4), and the fuel control system (1) is used to control the amount of fuel in the combustion chamber (2); The secondary flow system includes a test control module (29), an electric heater (30), and pipelines. There are two sets of electric heaters (30) arranged side by side. The two sets of electric heaters (30) are connected to the compressed air control system (3) through pipelines. A flow monitor (31) is provided between the electric heaters (30) and the compressed air control system (3). There are two sets of test control modules, which are electrically connected to the two sets of electric heaters (30) respectively. A pressure monitor (32) and a temperature monitor (33) are provided between the electric heaters (30) and the test blade (5). An air vent branch is also provided on the electric heaters (30).

5. The ceramic matrix composite turbine blade thermal fatigue testing system as described in claim 1, characterized in that: The exhaust section (6) is provided with an exhaust inner cavity (34) and an exhaust outer cavity (35). The exhaust inner cavity (34) is connected to the interior of the test blade grating (5). The exhaust outer cavity (35) is connected to a second cooling water channel (36). The exhaust section (6) is provided with a cooling section (37) at its rear end. The cooling section (37) is provided with a spray head that can spray high-pressure water. The cooling section (37) is provided with a back pressure regulating valve (38) at its rear end.

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