High-temperature high-speed turbine rotor reliability test system

Abstract

The invention relates to a high-temperature high-speed turbine rotor reliability test system which comprises a motor, an air inlet filter, a compressor, a check valve, an air storage tank, a regulating valve, a power turbine, a tested turbine rotor, an analog loader and a high-temperature heating cover. The motor drives the compressor to work, gas enters the compressor through the gas inlet filter and then enters the gas storage tank through the check valve after being pressurized, and high-pressure gas in the gas storage tank enters the power turbine after passing through the adjusting valve to be expanded and cooled, then enters the high-temperature heating cover and is exhausted after passing through a protection plate of the high-temperature heating cover and a cavity in the middle of a heat insulation sleeve of the high-temperature heating cover. The power turbine drives a tested turbine rotor to rotate, an impeller part of the tested turbine rotor is located in the high-temperature heating cover, a high-temperature-resistant elastic ball of the analog loader makes contact with impeller blades of the tested turbine rotor, a cavity in the high-temperature heating cover is filled with a low-pressure gas working medium for working of the tested turbine rotor, and a test load environment is formed. The test system has the characteristics of low cost, good durability, high safety and the like.

Description

Technical Field

[0001] The invention belongs to the technical field of radial flow turbine rotor testing, and in particular relates to a high-temperature and high-speed turbine rotor reliability testing system. Background Art

[0002] As the core component of the radial turbine system, the high-temperature and high-speed turbine rotor is one of the most complex and severe components in the turbine. When the turbine is working, the turbine rotor is in a high-speed rotation state under the action of the high-temperature gas working medium, and its speed can reach tens of thousands of revolutions per minute, and some rotors even reach hundreds of thousands of revolutions per minute. Once the turbine rotor structure fails, it will not only cause the turbine to fail to work normally and fail to realize the conversion of thermal energy into mechanical energy, but also cause damage to other structures in the system. On the basis of reasonable design of the turbine rotor structure and high-quality manufacturing, it is crucial to effectively evaluate and verify the reliability of the turbine rotor to reasonably determine the working life of the high-temperature and high-speed turbine rotor.

[0003] In order to meet the high efficiency and other performance requirements of the turbine system, the inlet temperature and operating speed of the turbine rotor continue to increase, which puts higher requirements on the service life and working reliability of the turbine rotor. High-temperature and high-speed turbine rotors generally have the characteristics of long service life and high power. The reliability assessment of turbine rotors by carrying out whole-machine tests not only requires large energy consumption, but also has high test risks. Once the turbine rotor is damaged during the test, the whole machine will be damaged. Therefore, on the basis of completing the design and manufacture of the turbine rotor, it is a more reasonable technical approach to verify the reliability of the turbine rotor through separate component tests.

[0004] The reliability test of high-temperature and high-speed turbine rotors is aimed at evaluating the working reliability of turbine rotors under the action of high-temperature and high-speed gas working fluids. To this end, the reliability test system of high-temperature and high-speed turbine rotors is required to be able to effectively construct centrifugal load, thermal load and aerodynamic load environment, and effectively apply them to the turbine rotor. In view of the reliability verification requirements of high-temperature and high-speed turbine rotors, the scientific and efficient evaluation and verification of turbine rotor reliability can be achieved through the reasonable design of the test system. Summary of the invention

[0005] Aiming at the reliability verification demand of high-temperature and high-speed turbine rotors, the present invention proposes a high-temperature and high-speed turbine rotor reliability test system. The test system includes a motor, an air intake filter, a compressor, a check valve, an air storage tank, a regulating valve, a power turbine, a test turbine rotor, a simulation loader and a high-temperature heating cover. The motor drives the compressor to work, and the gas first enters the compressor through the air intake filter, and enters the air storage tank through the check valve after being pressurized by the compressor. The high-pressure gas in the air storage tank enters the power turbine after passing through the regulating valve and drives the power turbine to work. The gas after passing through the power turbine expands and cools down and enters the high-temperature heating cover. The high-temperature heating cover is cooled and protected through the cavity between the protective plate of the high-temperature heating cover and the heat insulation sleeve of the high-temperature heating cover. The power turbine drives the test turbine rotor to rotate at high speed, applying a centrifugal load to the test turbine rotor; the impeller part of the test turbine rotor is located inside the high-temperature heating cover, applying a thermal load to the test turbine rotor; the high-temperature resistant elastic ball of the simulation loader is in contact with the impeller blades of the test turbine rotor, applying an equivalent aerodynamic load to the test turbine rotor during rotation; the internal cavity of the high-temperature heating cover is filled with low-pressure gas working fluid for the test turbine rotor, applying a gas atmosphere environment to the test turbine rotor, forming a reliability test load environment for a high-temperature and high-speed turbine rotor.

[0006] The technical solution of the present invention:

[0007] A high-temperature and high-speed turbine rotor reliability test system comprises a motor, an air intake filter, a compressor, a check valve, an air storage tank, a regulating valve, a power turbine, a test turbine rotor, a simulation loader and a high-temperature heating cover.

[0008] The motor is used to drive the compressor to work, and the output shaft of the motor is connected to the compressor rotor shaft.

[0009] The air inlet side of the air inlet filter is connected to the atmospheric environment, and the air outlet side of the air inlet filter is connected to the air inlet of the compressor.

[0010] The rotor shaft of the compressor is connected to the output shaft of the motor, the air intake side of the compressor is communicated with the exhaust side of the air intake filter, and the exhaust side of the compressor is connected to the air intake end of the check valve.

[0011] The check valve is located between the compressor and the air storage tank, the air inlet end of the check valve is connected to the exhaust side of the compressor, and the air outlet end of the check valve is connected to the air inlet end of the air storage tank.

[0012] The gas storage tank is located between the check valve and the regulating valve. The gas storage tank is used to store the high-pressure gas output by the compressor. The air inlet end of the gas storage tank is connected to the air outlet end of the check valve, and the air outlet end of the gas storage tank is connected to the air inlet end of the regulating valve.

[0013] The regulating valve is located between the air storage tank and the power turbine, the air inlet end of the regulating valve is connected to the air outlet end of the air storage tank, and the air outlet end of the regulating valve is connected to the air inlet end of the power turbine.

[0014] The power turbine is located after the regulating valve, the air inlet end of the power turbine is connected to the air outlet end of the regulating valve, the output shaft of the power turbine is connected to the rotating shaft of the test turbine rotor, the power turbine is a symmetrical double-impeller structure, and the power turbine is used to drive the test turbine rotor to rotate at high speed.

[0015] The rotating shaft of the test turbine rotor is connected to the output shaft of the power turbine, the impeller part of the test turbine rotor is located inside the high-temperature heating cover, and the impeller blades of the test turbine rotor are in contact with the elastic ball of the simulated loader.

[0016] The simulated loader consists of a high-temperature resistant elastic ball, a stiffness adjustment rod and a mounting base. The simulated loader is fixed to the internal cavity of the high-temperature heating cover through its mounting base. The high-temperature resistant elastic ball of the simulated loader is in contact with the impeller blades of the test turbine rotor. The stiffness adjustment rod of the simulated loader is a slender rod with a variable cross-section. The simulated loader is evenly arranged along the circumference of the test turbine rotor.

[0017] The high-temperature heating cover is composed of a heating sleeve, an insulating sleeve, a protective plate and an insulating cover plate. The heating sleeve of the high-temperature heating cover is located on the exhaust side and the outer side of the radial rim of the test turbine rotor. The insulating ring of the high-temperature heating cover is located on the outer side of the heating sleeve of the high-temperature heating cover. The protective plate of the high-temperature heating cover is covered on the outer side of the insulating sleeve of the high-temperature heating cover. A cavity through which cooling gas can pass is provided between the protective plate of the high-temperature heating cover and the insulating sleeve of the high-temperature heating cover. The insulating cover plate of the high-temperature heating cover is assembled with the heating sleeve of the high-temperature heating cover and forms a closed cavity with the heating sleeve of the high-temperature heating cover. The insulating cover plate of the high-temperature heating cover is close to the wheel back of the test turbine rotor. The insulating cover plate of the high-temperature heating cover adopts an internally hollow high-temperature ceramic additive manufacturing structure. The internal cavity of the high-temperature heating cover is filled with a low-pressure gas working medium for the test turbine rotor.

[0018] In the reliability test system of the high-temperature and high-speed turbine rotor, the motor drives the compressor to work, the gas first enters the compressor through the air intake filter, and enters the gas storage tank through the check valve after being pressurized by the compressor. The high-pressure gas in the gas storage tank enters the power turbine after passing through the regulating valve and drives the power turbine to work. The gas after the power turbine expands and cools down and enters the high-temperature heating cover. The high-temperature heating cover is cooled and protected through the cavity between the protective plate of the high-temperature heating cover and the heat insulation sleeve of the high-temperature heating cover. The power turbine drives the test turbine rotor to rotate at high speed, applying a centrifugal load to the test turbine rotor; the impeller part of the test turbine rotor is located in the high-temperature heating cover, applying a thermal load to the test turbine rotor; the high-temperature resistant elastic ball of the simulated loader contacts the impeller blades of the test turbine rotor, and applies an equivalent aerodynamic load to the test turbine rotor during the rotation process; the internal cavity of the high-temperature heating cover is filled with a low-pressure gas medium for the test turbine rotor to work, and a gas atmosphere environment is applied to the test turbine rotor, forming a reliability test load environment for the high-temperature and high-speed turbine rotor.

[0019] The beneficial effects of the present invention are:

[0020] The present invention proposes a high-temperature and high-speed turbine rotor reliability test system, in which the power turbine is used to drive the test turbine rotor to rotate, and a centrifugal load can be applied to the high-speed turbine rotor; the high-temperature resistant elastic ball of the simulation loader contacts the impeller blades of the test turbine rotor, and an equivalent aerodynamic load can be applied to the test turbine rotor during rotation; the internal cavity of the high-temperature heating cover is filled with a low-pressure gas working medium for the test turbine rotor, and a gas atmosphere environment can be applied to the test turbine rotor. The impeller part of the test turbine rotor is located within the high-temperature heating cover, and a thermal load can be applied to the test turbine rotor. The operation of these technical measures can ensure the authenticity and effectiveness of the load environment of the reliability test of the test turbine rotor. The power turbine adopts a symmetrical double-impeller structure, which can achieve axial force balance and improve the rotor operation stability of the turbine rotor. The heat-insulating cover of the high-temperature heating cover adopts an internally hollow high-temperature ceramic additive manufacturing structure, which can reduce heat damage in the high-temperature heating cover and reduce the reliability test cost. The gas after the power turbine expands and cools down before entering the high-temperature heating cover. The high-temperature heating cover can be cooled and protected through the cavity between the protective plate of the high-temperature heating cover and the heat insulation sleeve of the high-temperature heating cover, further enhancing the durability and safety of the reliability test system. The test system can effectively simulate the load environment of the high-temperature and high-speed turbine rotor, and has the characteristics of low cost, good durability and high safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the high-temperature and high-speed turbine rotor reliability test system.

[0022] 1 Motor 2 Air intake filter 3 Compressor 4 Check valve 5 Air tank 6 Regulating valve

[0023] 7 Power turbine 8 Test turbine rotor 9 Simulation loader 10 High temperature heating cover DETAILED DESCRIPTION

[0024] A high-temperature and high-speed turbine rotor reliability test system comprises a motor 1, an air intake filter 2, a compressor 3, a check valve 4, an air storage tank 5, an air storage tank 6, a power turbine 7, a test turbine rotor 8, a simulation loader 9 and a high-temperature heating cover 10.

[0025] The motor 1 is used to drive the compressor 3 to work, and the output shaft of the motor 1 is connected to the compressor rotor shaft.

[0026] The air intake side of the air intake filter 2 is connected to the atmospheric environment, and the air exhaust side of the air intake filter 2 is connected to the air intake port of the compressor 3 .

[0027] The rotor shaft of the compressor 3 is connected to the output shaft of the motor 1 , the air intake side of the compressor 3 is connected to the exhaust side of the air intake filter 2 , and the exhaust side of the compressor 3 is connected to the air intake end of the check valve 4 .

[0028] The check valve 4 is located between the compressor 3 and the air storage tank 5 , the air inlet end of the check valve 4 is connected to the exhaust side of the compressor 3 , and the air outlet end of the check valve 4 is connected to the air inlet end of the air storage tank 5 .

[0029] The gas storage tank 5 is located between the check valve 4 and the gas storage tank 6. The gas storage tank 5 is used to store the high-pressure gas output by the compressor 3. The air inlet end of the gas storage tank 5 is connected to the air outlet end of the check valve 4, and the air outlet end of the gas storage tank 5 is connected to the air inlet end of the gas storage tank 6.

[0030] The air storage tank 6 is located between the air storage tank 5 and the power turbine 7 , the air inlet end of the air storage tank 6 is connected to the air outlet end of the air storage tank 5 , and the air outlet end of the air storage tank 6 is connected to the air inlet end of the power turbine 7 .

[0031] The power turbine 7 is located behind the air tank 6, the air inlet end of the power turbine 7 is connected to the air outlet end of the air tank 6, the output shaft of the power turbine 7 is connected to the rotating shaft of the test turbine rotor 8, the power turbine 7 is a symmetrical double-impeller structure, and the power turbine 7 is used to drive the test turbine rotor 8 to rotate at high speed.

[0032] The rotating shaft of the test turbine rotor 8 is connected to the output shaft of the power turbine 7, the impeller part of the test turbine rotor 8 is located inside the high-temperature heating cover 10, and the impeller blades of the test turbine rotor 8 are in contact with the elastic ball of the simulated loader 9.

[0033] The simulated loader 9 is composed of a high-temperature resistant elastic ball, a stiffness adjustment rod and a mounting base. The simulated loader 9 is fixed to the internal cavity of the high-temperature heating cover 10 through its mounting base. The high-temperature resistant elastic ball of the simulated loader 9 is in contact with the impeller blades of the test turbine rotor 8. The stiffness adjustment rod of the simulated loader 9 is a slender rod with a variable cross-section. The simulated loader 9 is evenly arranged along the circumference of the test turbine rotor 8.

[0034] The high-temperature heating cover 10 is composed of a heating sleeve, an insulating sleeve, a protective plate and an insulating cover plate. The heating sleeve of the high-temperature heating cover 10 is located on the exhaust side and the outer side of the radial rim of the test turbine rotor 8. The insulating ring of the high-temperature heating cover 10 is located on the outer side of the heating sleeve of the high-temperature heating cover 10. The protective plate of the high-temperature heating cover 10 is covered on the outer side of the insulating sleeve of the high-temperature heating cover 10. A cavity through which cooling gas can pass is provided between the protective plate of the high-temperature heating cover 10 and the insulating sleeve of the high-temperature heating cover 10. The insulating cover plate of the high-temperature heating cover 10 is assembled with the heating sleeve of the high-temperature heating cover 10 and forms a closed cavity with the heating sleeve of the high-temperature heating cover 10. The insulating cover plate of the high-temperature heating cover 10 is close to the wheel back of the test turbine rotor 8. The insulating cover plate of the high-temperature heating cover 10 adopts an internally hollow high-temperature ceramic additive manufacturing structure. The internal cavity of the high-temperature heating cover 10 is filled with a low-pressure gas working medium for the test turbine rotor 8.

[0035] In the high-temperature and high-speed turbine rotor reliability test system, the motor 1 drives the compressor 3 to work, the gas first enters the compressor 3 through the air intake filter 2, and enters the air storage tank 5 through the check valve 4 after being pressurized by the compressor 3. The high-pressure gas in the air storage tank 5 passes through the air storage tank 6 and enters the power turbine 7 to drive the power turbine 7 to work. After passing through the power turbine 7, the gas expands and cools down and enters the high-temperature heating cover 10. The high-temperature heating cover 10 is cooled and protected by the cavity between the protective plate of the high-temperature heating cover 10 and the insulation sleeve of the high-temperature heating cover 10. The power turbine 7 drives the test turbine rotor 8 to rotate at a high speed, applying a centrifugal load to the test turbine rotor 8; the impeller part of the test turbine rotor 8 is located within the high-temperature heating cover 10, applying a thermal load to the test turbine rotor 8; the high-temperature resistant elastic ball of the simulation loader 9 is in contact with the impeller blades of the test turbine rotor 8, applying an equivalent aerodynamic load to the test turbine rotor 8 during the rotation process; the internal cavity of the high-temperature heating cover 10 is filled with a low-pressure gas working medium for the test turbine rotor 8, applying a gas atmosphere environment to the test turbine rotor 8, forming a reliability test load environment for a high-temperature and high-speed turbine rotor.

[0036] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A high-temperature and high-speed turbine rotor reliability test system, characterized in that: It includes a motor (1), an air intake filter (2), a compressor (3), a check valve (4), an air storage tank (5), a regulating valve (6), a power turbine (7), a test turbine rotor (8), a simulation loader (9) and a high-temperature heating cover (10); The motor (1) is used to drive the compressor (3) to work, and the output shaft of the motor (1) is connected to the compressor rotor shaft; The air intake side of the air intake filter (2) is connected to the atmospheric environment, and the air exhaust side of the air intake filter (2) is connected to the air intake port of the compressor (3); The rotor shaft of the compressor (3) is connected to the output shaft of the motor (1), the air intake side of the compressor (3) is connected to the exhaust side of the air intake filter (2), and the exhaust side of the compressor (3) is connected to the air intake end of the check valve (4); The check valve (4) is located between the compressor (3) and the gas storage tank (5), the air inlet end of the check valve (4) is connected to the exhaust side of the compressor (3), and the air outlet end of the check valve (4) is connected to the air inlet end of the gas storage tank (5); The gas storage tank (5) is located between the check valve (4) and the regulating valve (6), and is used to store high-pressure gas output by the compressor (3). The gas inlet end of the gas storage tank (5) is connected to the gas outlet end of the check valve (4), and the gas outlet end of the gas storage tank (5) is connected to the gas inlet end of the regulating valve (6); The regulating valve (6) is located between the air storage tank (5) and the power turbine (7), the air inlet end of the regulating valve (6) is connected to the air outlet end of the air storage tank (5), and the air outlet end of the regulating valve (6) is connected to the air inlet end of the power turbine (7); The power turbine (7) is located after the regulating valve (6), the air inlet end of the power turbine (7) is connected to the air outlet end of the regulating valve (6), the output shaft of the power turbine (7) is connected to the rotating shaft of the test turbine rotor (8), the power turbine (7) is a symmetrical double-impeller structure, and the power turbine (7) is used to drive the test turbine rotor (8) to rotate at a high speed; The rotating shaft of the test turbine rotor (8) is connected to the output shaft of the power turbine (7), the impeller portion of the test turbine rotor (8) is located within the high-temperature heating cover (10), and the impeller blades of the test turbine rotor (8) are in contact with the elastic ball of the simulated loader (9); The simulated loader (9) is composed of a high-temperature resistant elastic ball, a stiffness adjustment rod and a mounting base. The simulated loader (9) is fixed to the inner cavity of the high-temperature heating cover (10) through its mounting base. The high-temperature resistant elastic ball of the simulated loader (9) is in contact with the impeller blades of the test turbine rotor (8). The stiffness adjustment rod of the simulated loader (9) is a slender rod with a variable cross-section. The high-temperature heating cover (10) is composed of a heating sleeve, a heat insulating sleeve, a protective plate and a heat insulating cover plate. The heating sleeve of the high-temperature heating cover (10) is located on the exhaust side and the outer side of the radial wheel rim of the test turbine rotor (8). The heat insulating ring of the high-temperature heating cover (10) is located on the outer side of the heating sleeve of the high-temperature heating cover (10). The protective plate of the high-temperature heating cover (10) is covered on the outer side of the heat insulating sleeve of the high-temperature heating cover (10). A cavity through which cooling gas can pass is provided between the protective plate of the high-temperature heating cover (10) and the heat insulating sleeve of the high-temperature heating cover (10). The heat insulating cover plate of the high-temperature heating cover (10) is assembled with the heating sleeve of the high-temperature heating cover (10) and forms a closed cavity with the heating sleeve of the high-temperature heating cover (10). The heat insulating cover plate of the high-temperature heating cover (10) is close to the wheel back of the test turbine rotor (8).

2. A high-temperature and high-speed turbine rotor reliability test system according to claim 1, characterized in that: In the high-temperature, high-speed turbine rotor reliability test system, a motor (1) drives a compressor (3) to work, gas first enters the compressor (3) through an air intake filter (2), and enters a gas storage tank (5) through a check valve (4) after being pressurized by the compressor (3). The high-pressure gas in the gas storage tank (5) enters a power turbine (7) after passing through a regulating valve (6) and drives the power turbine (7) to work. After the gas has expanded and cooled after passing through the power turbine (7), it enters a high-temperature heating cover (10), and the high-temperature heating cover (10) is cooled and protected through a cavity between a protective plate of the high-temperature heating cover (10) and a heat insulation sleeve of the high-temperature heating cover (10). The power turbine (7) drives the test turbine rotor (8) to rotate at a high speed, applying a centrifugal load to the test turbine rotor (8); the impeller portion of the test turbine rotor (8) is located within the high-temperature heating cover (10), applying a thermal load to the test turbine rotor (8); the high-temperature resistant elastic ball of the simulation loader (9) contacts the impeller blades of the test turbine rotor (8), applying an equivalent aerodynamic load to the test turbine rotor (8) during the rotation process; The internal cavity of the high-temperature heating cover (10) is filled with a low-pressure gas working medium for the test turbine rotor (8), and a gas atmosphere environment is applied to the test turbine rotor (8) to form a reliability test load environment for the high-temperature and high-speed turbine rotor.

3. A high-temperature and high-speed turbine rotor reliability test system according to claim 1, characterized in that: The simulated loaders (9) are evenly arranged along the circumference of the test turbine rotor (8).

4. A high temperature and high speed turbine rotor reliability test system according to claim 1, characterized in that: The heat-insulating cover plate of the high-temperature heating cover (10) adopts a high-temperature ceramic additive manufacturing structure with a hollow interior.

5. A high temperature and high speed turbine rotor reliability test system according to claim 1, characterized in that: The internal cavity of the high-temperature heating cover (10) is filled with a low-pressure gas working medium for the working of the test turbine rotor (8).

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