Turbine driven rocket engine bearing, seal run test apparatus and method

Abstract

The application discloses a turbine-driven rocket engine bearing and sealing operation test device, and solves the problems of slow starting and stopping process, low maximum rotating speed and poor sensitivity of rotating speed to load change in the prior art bearing and sealing operation test in which a motor is used as a driving device; the application installs a to-be-tested part on a shafting inside a tester, connects the shafting with an output end of a driving turbine, passes gas into the driving turbine through a gas supply assembly, drives the driving turbine to rotate the to-be-tested part, changes the state of the to-be-tested part, and thus influences the rotating speed of the shafting; a rotating speed sensor detects the rotating speed change, and an upper computer observes simultaneously; a turbine gas supply valve controls the gas inlet of the driving turbine, a pressure reducing valve controls the gas pressure, and thus the rotating speed of the driving turbine is changed; a pressure sensor detects the gas pressure in real time, the driving turbine starts and stops rapidly, the maximum rotating speed is higher than that of an ordinary motor, and the rotating speed is sensitive to load change.

Description

Technical Field

[0001] This invention relates to a rocket engine operation test apparatus, specifically to a turbine-driven rocket engine bearing, a sealed operation test apparatus and method. Background Technology

[0002] Bearings and seals are key components of rocket engine turbopumps. During engine development or routine inspections, ground-based simulated operation tests are required to assess their performance and reliability. The typical test procedure involves installing the bearings and seals in a test chamber simulating the engine's installation state, then driving the chamber to perform tests on the bearings and seals.

[0003] The structure of the existing test apparatus 2 is as follows: Figure 1 As shown, a shaft system is rotatably mounted inside the test apparatus 2 via a process bearing 23. The bearing or seal to be tested is mounted on the shaft system. The outer wall of the test apparatus 2 is provided with a test medium inlet 21 and a test medium outlet 22. The test medium inlet 21 is used to introduce the test medium into the test apparatus 2 to simulate the working environment of the bearing or seal, while the test medium outlet 22 is used to discharge the test medium during the test, so that the test medium is in a flowing state.

[0004] The time it takes for a rocket engine turbopump to accelerate from zero to its rated speed of tens of thousands of revolutions is typically only about two seconds. Since the commonly used drive device is an electric motor, the following problems arise when using an electric motor for operational testing:

[0005] 1) The motor starts and stops slowly, making it impossible to achieve such high acceleration and deceleration, thus failing to accurately simulate the real starting and stopping process of bearings and seals.

[0006] 2) The maximum operating speed of the motor is only a few thousand revolutions per minute, while the rated speed of the rocket engine turbopump is basically over 10,000 revolutions per minute. Using a motor drive cannot accurately simulate the rated speed test conditions.

[0007] 3) When the motor is used as a drive device for operation testing, its speed is stable, but it is not sensitive to speed changes caused by changes in the load of the tester and cannot promptly reflect the operating fault status of the bearings and seals. Summary of the Invention

[0008] The purpose of this invention is to solve the technical problems of slow start-up and shutdown processes, low maximum speed, and poor sensitivity of speed to load changes when using an electric motor as a drive device in existing bearing and seal operation tests. The invention provides a turbine-driven rocket engine bearing and seal operation test device and method.

[0009] To achieve the above objectives, the technical solution provided by this invention is as follows:

[0010] A turbine-driven rocket engine bearing and sealed operation test device, including a test apparatus; its special feature is:

[0011] It also includes a drive turbine, a turbine air supply valve, a host computer, sensor components, an air supply assembly, and a pressure reducing valve;

[0012] The inside of the testing apparatus is used to install the test piece, and the test piece is installed on the shaft system inside the testing apparatus;

[0013] The drive turbine is located outside the test apparatus, and its output end is connected to the shaft input end of the test apparatus.

[0014] The turbine air supply valve, pressure reducing valve, and air supply assembly are connected in sequence through pipelines, and the air intake end of the turbine is connected to the turbine air supply valve.

[0015] The sensor assembly includes a speed sensor and a pressure sensor. The speed sensor is mounted on a shaft inside the test apparatus, and the pressure sensor is mounted on a pipeline between a pressure reducing valve and a turbine air supply valve.

[0016] The output terminals of the speed sensor and pressure sensor, as well as the control terminals of the turbine air supply valve and pressure reducing valve, are all electrically connected to the host computer.

[0017] Furthermore, it also includes couplings;

[0018] The input end of the shaft system is connected to the output end of the drive turbine via a coupling.

[0019] Furthermore, the intake end of the drive turbine is connected to a turbine intake pipe, and the turbine air supply valve is connected to the turbine intake pipe;

[0020] The exhaust end of the drive turbine is connected to a turbine exhaust pipe.

[0021] Furthermore, it also includes a heater;

[0022] The heater is installed on the pipeline between the pressure reducing valve and the gas supply assembly, and the control terminal of the heater is electrically connected to the host computer.

[0023] Furthermore, it also includes a temperature sensor;

[0024] The temperature sensor is installed on the pipeline between the pressure reducing valve and the turbine air supply valve, and the output end of the temperature sensor is electrically connected to the host computer.

[0025] Furthermore, the maximum output power of the drive turbine is 400kW, and the maximum speed is 40000rpm;

[0026] The speed sensor has a maximum measuring speed of 40,000 rpm and a maximum permissible measurement error of 0.25%.

[0027] The pressure sensor has a measurement range of 0 to 25 MPa and a maximum permissible measurement error of 0.25%.

[0028] The temperature sensor has a measurement range of -50℃ to 600℃ and an error range of ±2.5℃.

[0029] Meanwhile, the present invention also provides a test method for the sealed operation of a turbine-driven rocket engine bearing, using the aforementioned test device for the sealed operation of a turbine-driven rocket engine bearing; its special feature is that it includes the following steps:

[0030] S1. Install the test piece onto the shaft system inside the tester, then introduce the test medium into the tester, and then open the gas supply assembly, pressure reducing valve and turbine gas supply valve to allow the gas supply assembly to introduce gas into the drive turbine.

[0031] S2. The gas entering the drive turbine first does work on the drive turbine, causing the speed of the drive turbine to increase rapidly, and then it is discharged through the exhaust end of the drive turbine.

[0032] The shaft speed of the test instrument is detected by a speed sensor. and the rotation speed Uploaded to the host computer for continuous monitoring;

[0033] The opening of the pressure reducing valve is controlled by a host computer, thereby changing the gas pressure entering the drive turbine. A pressure sensor continuously monitors the gas pressure and transmits the pressure data to the host computer for monitoring. Changes in gas pressure alter the rotational speed of the drive turbine, which in turn changes the shaft rotational speed of the test apparatus. Until the shaft speed of the tester... Satisfy the following relations:

[0034] ;

[0035] ;

[0036] in: To drive the output torque of the turbine, The shaft speed of the testing equipment. and These are the work efficiencies of the driving turbine and the testing device, respectively. The shaft load torque of the tester. This refers to the work input from the gas to drive the turbine.

[0037] Then maintain this speed. It operates continuously and monitors the operating status of the test piece;

[0038] S3. If the test piece is operating normally, the shaft load torque of the tester is... The shaft speed of the tester will not change. Constant and unchanging;

[0039] If the operating condition of the test piece changes abnormally, the shaft load torque of the tester will be... It will change immediately, as can be seen from the following relationship:

[0040] ;

[0041] ;

[0042] in: The moment of inertia of the test apparatus shaft system. This is the absolute value of the angular acceleration of the test instrument's shaft system;

[0043] Shaft speed of the testing equipment It will change immediately, through the speed sensor to measure the speed. The data is transmitted to the host computer, which then issues an alarm.

[0044] S4. After the test time of the test component is reached, the turbine air supply valve, pressure reducing valve and air supply assembly are closed in sequence to complete the turbine-driven rocket engine bearing and sealing operation test.

[0045] Furthermore, in step S2, the rotational speed of the drive turbine is changed by altering the gas pressure, thereby changing the shaft rotational speed of the test apparatus. Until the shaft speed of the tester... When the following relations are satisfied:

[0046] ;

[0047] ;

[0048] If the shaft speed of the testing machine If adjusting the pressure reducing valve alone cannot meet the test requirements, the heater is activated via the host computer to heat the gas. A temperature sensor detects the gas temperature and uploads the data to the host computer for continuous monitoring until the shaft speed of the test apparatus reaches its maximum. The relationship is satisfied.

[0049] Compared with the prior art, the present invention has the following beneficial technical effects:

[0050] 1. The turbine-driven rocket engine bearing, sealed operation test device and method provided by the present invention installs the test piece on a shaft system inside the test apparatus, and the input end of the shaft system is connected to the output end of the drive turbine. Gas is supplied to the drive turbine through the gas supply assembly, causing it to rotate rapidly, thereby driving the test piece to rotate. If the state of the test piece changes, it will affect the rotational speed of the shaft system. The rotational speed change is detected by a speed sensor, and if there is a change, it can be observed by a host computer. The intake of the drive turbine is controlled by the turbine gas supply valve, and the pressure of the gas is controlled by the pressure reducing valve, thereby changing the rotational speed of the drive turbine. The pressure sensor can detect the gas pressure in real time, which facilitates the control and adjustment of the pressure reducing valve opening. Compared with the motor, the drive turbine has a rapid start-stop process, and its operating speed can meet the working speed of the test piece, improving the accuracy of the test. At the same time, the drive turbine has good sensitivity to load changes and can indicate the operating status of the test piece based on the speed fluctuation.

[0051] 2. The turbine-driven rocket engine bearing, sealed operation test device and method provided by the present invention can, when adjusting the opening of the pressure reducing valve alone cannot meet the test speed requirements, heat the gas output by the gas supply component by turning on the heater through the host computer, thereby further increasing the speed of the driving turbine.

[0052] 3. In the turbine-driven rocket engine bearing and sealed operation test device provided by the present invention, the shaft input end inside the test device is connected to the output end of the driving turbine through a coupling, so as to adapt to shafts with different shaft diameters and the output end of the driving turbine. Attached Figure Description

[0053] Figure 1 This is a simplified schematic diagram of the test apparatus.

[0054] Figure 2 This is a simplified structural diagram of an embodiment of the turbine-driven rocket engine bearing and sealed operation test device of the present invention.

[0055] The annotations in the attached figures are explained as follows:

[0056] 1-Test piece, 2-Testing apparatus, 21-Test medium inlet, 22-Test medium outlet, 23-Process bearing; 3-Coupling, 4-Drive turbine, 5-Turbine inlet pipe, 6-Turbine air supply valve, 7-Turbine exhaust pipe, 8-Host computer, 9-Speed ​​sensor, 91-Pressure sensor, 92-Temperature sensor; 10-Air supply assembly, 11-Pressure reducing valve, 12-Heater. Detailed Implementation

[0057] To make the objectives, advantages, and features of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. Those skilled in the art should understand that these embodiments are merely used to explain the technical principles of the present invention and are not intended to limit the scope of protection of the present invention.

[0058] like Figure 2 As shown, this embodiment provides a turbine-driven rocket engine bearing and sealed operation test device, including a tester 2, a drive turbine 4, a turbine air supply valve 6, a host computer 8, a sensor assembly, an air supply assembly 10, and a pressure reducing valve 11.

[0059] The interior of the test apparatus 2 is used to install the test piece 1, which can be a bearing or a seal. The test piece 1 is installed on the shaft system inside the test apparatus 2.

[0060] The drive turbine 4 is located outside the test apparatus 2, and the output end of the drive turbine 4 is connected to the shaft input end of the test apparatus 2. In order to improve the adaptability to different shaft systems and the output shaft system, in this embodiment, the shaft input end of the test apparatus 2 and the output end of the drive turbine 4 are connected by a coupling 3.

[0061] The turbine supply valve 6, pressure reducing valve 11, and air supply assembly 10 are connected in sequence through pipelines, and the air intake end of the drive turbine 4 is connected to the turbine supply valve 6. In order to facilitate the connection between the air intake end of the drive turbine 4 and the turbine supply valve 6, a turbine intake pipe 5 is connected to the air intake end of the drive turbine 4. The turbine supply valve 6 is connected to the turbine intake pipe 5. In this way, different sizes of turbine intake pipes 5 can be replaced to adapt to different models of turbine supply valves 6.

[0062] The turbine 4 is connected to a turbine exhaust pipe 7 at its outlet end, which facilitates the diversion and discharge of exhaust gas.

[0063] In general operation tests, the speed of the drive turbine 4 can be adjusted by changing the opening of the pressure reducing valve 11, and the speed adjustment range can generally cover the working speed range of the test piece 1. If there are special requirements for the test piece 1, simply changing the opening of the pressure reducing valve 11 cannot meet its test requirements. Therefore, this embodiment also provides a heater 12. The heater 12 is installed on the pipeline between the pressure reducing valve 11 and the air supply assembly 10, which can heat the gas output by the air supply assembly 10. After the heated gas is input into the drive turbine 4, its speed can be further increased.

[0064] The sensor assembly includes a speed sensor 9, a pressure sensor 91, and a temperature sensor 92. The outputs of all three are electrically connected to the host computer 8. The speed sensor 9 is installed on the shaft system inside the test apparatus 2 to detect the rotational speed of the shaft system and upload the speed data to the host computer 8. The pressure sensor 91 and the temperature sensor 92 are both installed on the pipeline between the pressure reducing valve 11 and the turbine air supply valve 6 to detect the gas pressure and temperature inside the input drive turbine 4 and upload the pressure data and temperature data to the host computer 8 respectively. The operator can directly view various data through the host computer 8.

[0065] The control terminals of the turbine air supply valve 6, pressure reducing valve 11, and heater 12 are electrically connected to the host computer 8, which can control all three. In this embodiment, the maximum output power of the drive turbine 4 is 400kW, and the maximum speed is 40,000rpm; the maximum measuring speed of the speed sensor 9 is 40,000rpm, and the maximum permissible measurement error is 0.25 grade; the measurement range of the pressure sensor 91 is 0 to 25MPa, and the maximum permissible measurement error is 0.25 grade; the measurement range of the temperature sensor 92 is -50℃ to 600℃, and the error range is ±2.5℃.

[0066] Meanwhile, the present invention also provides a test method for the sealed operation of a turbine-driven rocket engine bearing, using the aforementioned test device for the sealed operation of a turbine-driven rocket engine bearing, comprising the following steps:

[0067] S1. Install the test piece 1 onto the shaft system inside the tester 2, then introduce the test medium into the tester 2, and then open the air supply assembly 10, the pressure reducing valve 11 and the turbine air supply valve 6 to introduce gas into the drive turbine 4 through the air supply assembly 10.

[0068] S2. The gas entering the drive turbine 4 first does work on the drive turbine 4, causing the speed of the drive turbine 4 to increase rapidly, and then it is discharged through the exhaust end of the drive turbine 4.

[0069] The shaft speed of tester 2 is detected by speed sensor 9. and the rotation speed Uploaded to host computer 8, where continuous monitoring is performed;

[0070] The host computer 8 controls the opening of the pressure reducing valve 11, thereby changing the gas pressure entering the drive turbine 4. The pressure sensor 91 continuously monitors the gas pressure and transmits the pressure data to the host computer 8 for monitoring. The change in gas pressure alters the rotational speed of the drive turbine 4, which in turn changes the shaft rotational speed of the test apparatus 2. Until the shaft speed of test apparatus 2 reaches its maximum. The following relationship must be satisfied:

[0071] ;

[0072] ;

[0073] in: The output torque driving turbine 4 is expressed in N·m.

[0074] The shaft rotation speed of test apparatus 2 is expressed in rad / s.

[0075] and These are the working efficiencies of the drive turbine 4 and the test device 2, respectively, with values ​​between 0 and 1, and have been calibrated before the test began;

[0076] The shaft load torque of tester 2 is constant under normal operating conditions for the same bearing or seal, and the unit is N·m;

[0077] The input work of the gas on the driving turbine 4 is expressed in W.

[0078] Then maintain this speed. It runs continuously and monitors the operating status of the test piece 1;

[0079] When the turbine air supply valve 6 is opened, the gas will immediately do work on the drive turbine 4, at which point the speed will increase. Very small, and The magnitude is large, and the driving turbine 4 generates a large angular acceleration on the shaft system of the test device 2. This makes the rotational speed The temperature rises rapidly until the two equations above are satisfied;

[0080] If the shaft speed of tester 2 If adjusting the pressure reducing valve 11 alone cannot meet the test requirements, the heater 12 is activated via the host computer 8 to heat the gas. The gas temperature is detected by the temperature sensor 92, and the temperature data is uploaded to the host computer 8 for continuous monitoring until the shaft speed of the test apparatus 2 is reached. The relationship is satisfied;

[0081] S3. If the test piece 1 is operating normally, then the shaft load torque of the tester 2 is... The rotational speed of shaft 2 of the test apparatus will not change. Constant and unchanging;

[0082] If the operating state of test piece 1 changes abnormally, the shaft load torque of tester 2 will be... It will change immediately, as can be seen from the following relationship:

[0083] ;

[0084] ;

[0085] in: The moment of inertia of the two shaft systems of the testing apparatus is expressed in kg·m. 2 ; The absolute value of the angular acceleration of the second axis system of the test apparatus, in rad / s. 2 ;

[0086] Shaft speed of test apparatus 2 The speed will change immediately, as measured by the speed sensor 9. The data is transmitted to host computer 8, which then issues an alarm.

[0087] S4. After the test time of the test component 1 is reached, the turbine air supply valve 6, the pressure reducing valve 11 and the air supply assembly 10 are closed in sequence to complete the turbine-driven rocket engine bearing and sealing operation test.

[0088] When the air supply assembly 10, turbine air supply valve 6, and pressure reducing valve 11 are closed, the gas input power to drive the turbine 4 is reduced. The speed quickly drops to zero. As can be seen from the relationship in step S3, the rotational speed at this point... It's very big. Even at a very small speed, the driving turbine 4 produces a large deceleration and acceleration on the test chamber 2. This makes the rotation speed It quickly dropped to zero.

[0089] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present invention.

Claims

1. A turbine-driven rocket engine bearing and sealing operation test device, comprising a test apparatus (2); characterized in that: It also includes a drive turbine (4), a turbine air supply valve (6), a host computer (8), a sensor assembly, an air supply assembly (10), and a pressure reducing valve (11). The test apparatus (2) is used to install the test piece (1), and the test piece (1) is installed on the shaft system inside the test apparatus (2); The drive turbine (4) is located outside the tester (2), and its output end is connected to the shaft input end of the tester (2); The turbine air supply valve (6), pressure reducing valve (11) and air supply assembly (10) are connected in sequence through pipelines, and the air inlet of the drive turbine (4) is connected to the turbine air supply valve (6). The sensor assembly includes a speed sensor (9) and a pressure sensor (91). The speed sensor (9) is mounted on a shaft inside the tester (2), and the pressure sensor (91) is mounted on a pipeline between the pressure reducing valve (11) and the turbine air supply valve (6). The output terminals of the speed sensor (9) and pressure sensor (91), as well as the control terminals of the turbine air supply valve (6) and pressure reducing valve (11), are all electrically connected to the host computer (8).

2. The turbine-driven rocket engine bearing and sealed operation test device according to claim 1, characterized in that: It also includes couplings (3); The input end of the shaft system is connected to the output end of the drive turbine (4) via a coupling (3).

3. The turbine-driven rocket engine bearing and sealed operation test device according to claim 2, characterized in that: The intake end of the drive turbine (4) is connected to a turbine intake pipe (5), and the turbine supply valve (6) is connected to the turbine intake pipe (5). The exhaust end of the drive turbine (4) is connected to a turbine exhaust pipe (7).

4. The turbine-driven rocket engine bearing and sealed operation test device according to claim 3, characterized in that: It also includes a heater (12); The heater (12) is installed on the pipeline between the pressure reducing valve (11) and the gas supply component (10), and the control terminal of the heater (12) is electrically connected to the host computer (8).

5. The turbine-driven rocket engine bearing and sealed operation test device according to claim 4, characterized in that: The sensor assembly also includes a temperature sensor (92). The temperature sensor (92) is installed on the pipeline between the pressure reducing valve (11) and the turbine air supply valve (6), and the output end of the temperature sensor (92) is electrically connected to the host computer (8).

6. The turbine-driven rocket engine bearing and sealed operation test device according to claim 5, characterized in that: The maximum output power of the drive turbine (4) is 400kW and the maximum speed is 40000rpm; The speed sensor (9) has a maximum measuring speed of 40,000 rpm and a maximum permissible measurement error of 0.25%. The pressure sensor (91) has a measurement range of 0 to 25 MPa and a maximum permissible measurement error of 0.25%. The temperature sensor (92) has a measurement range of -50℃ to 600℃ and an error range of ±2.5℃.

7. A method for testing the operation of a turbine-driven rocket engine bearing and its seal, comprising the turbine-driven rocket engine bearing and seal testing apparatus as described in any one of claims 1-6; characterized in that, Includes the following steps: S1. Install the test piece (1) onto the shaft system inside the tester (2), then introduce the test medium into the tester (2), and then open the gas supply assembly (10), pressure reducing valve (11) and turbine gas supply valve (6) so that the gas supply assembly (10) introduces gas into the drive turbine (4). S2. The gas entering the drive turbine (4) first does work on the drive turbine (4), causing the speed of the drive turbine (4) to increase rapidly, and then is discharged through the exhaust end of the drive turbine (4); The shaft rotation speed of the test apparatus (2) is detected by the rotation speed sensor (9). and the rotation speed Uploaded to the host computer (8), where it is continuously monitored; The opening degree of the pressure reducing valve (11) is controlled by the host computer (8), thereby changing the gas pressure entering the drive turbine (4). The gas pressure is continuously detected by the pressure sensor (91), and the pressure data is transmitted to the host computer (8) for monitoring. The speed of the drive turbine (4) is changed by the change in gas pressure, thereby changing the shaft speed of the tester (2). until the shaft speed of the test apparatus (2) reaches its maximum. The following relationship must be satisfied: ； ； in: To drive the output torque of the turbine (4), The shaft rotation speed of the test apparatus (2) and The working efficiency of the driving turbine (4) and the test device (2) are respectively. The shaft load torque of the test apparatus (2) is... The input work of the gas on the driving turbine (4); Then maintain this speed. It continues to operate and monitors the operating status of the test piece (1); S3. If the test piece (1) is in normal operating condition, then the shaft load torque of the tester (2) is... The shaft rotation speed of the test apparatus (2) will not change. Constant and unchanging; If the operating state of the test piece (1) changes abnormally, the shaft load torque of the tester (2) will be... It will change immediately, as can be seen from the following relationship: ； ； in: The moment of inertia of the shaft system of the test apparatus (2) The absolute value of the angular acceleration of the shaft system of the test apparatus (2); Shaft speed of test apparatus (2) The speed will change immediately, and the speed will be measured by the speed sensor (9). The data is transmitted to the host computer (8), and the host computer (8) issues an alarm. S4. When the test time of the test piece (1) is reached, the turbine air supply valve (6), pressure reducing valve (11) and air supply assembly (10) are closed in sequence to complete the turbine-driven rocket engine bearing and sealing operation test.

8. The test method for the bearing and sealed operation of a turbine-driven rocket engine according to claim 7, characterized in that: In step S2, the rotational speed of the drive turbine (4) is changed by the change in gas pressure, thereby changing the shaft rotational speed of the tester (2). until the shaft speed of the test apparatus (2) reaches its maximum. When the following relations are satisfied: ； ； If the shaft speed of the test apparatus (2) If the adjustment of the pressure reducing valve (11) alone cannot meet the test requirements, the heater (12) is turned on by the host computer (8) to heat the gas, and the gas temperature is detected by the temperature sensor (92). The temperature data is then uploaded to the host computer (8) for continuous monitoring until the shaft speed of the test apparatus (2) reaches the specified value. The relationship is satisfied.

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