A turbine powder starting test device

Abstract

The present application relates to a kind of turbine powder starting test device, to solve the technical problem that existing turbojet engine powder starting test bench cannot simulate rotor damage, turbine blade loss and other rotor unbalance state, it is difficult to verify the reliability of turbine starting under this special condition.The device includes jig, gas generator, guide rail, support, turbine, measurement monitoring component, transmission component and data processing component;Guide rail and turbine coaxial center and are provided with T-shaped sliding slot, and support is slidably installed by T-shaped sliding block;Tungsten alloy material clamping counterweight block is detachably installed on turbine blade, simulating rotor dynamic balance destruction state, and starting torque and blade deformation data are collected by torque meter and displacement sensor, and transmitted to controller for analysis by acquisition box.The present application can accurately simulate specific unbalance condition, obtain key parameters, and provide scientific basis for turbine starting system reliability evaluation and optimization.

Description

Technical Field

[0001] This invention belongs to the technical field of aero-engine test equipment, specifically relating to a turbine propellant start-up test device, and more particularly to a test device for simulating rotor dynamic balance failure and specifically testing the turbine propellant start-up performance of turbojet engines. Background Technology

[0002] As the core power component of a turbojet engine, the turbine's starting reliability directly determines the engine's operational safety. In actual use, the turbine may suffer rotor damage or blade shedding due to high temperature and high pressure environments, foreign object impacts, etc., leading to rotor dynamic imbalance, which in turn affects torque transmission, blade stress, and overall stability during the starting process, and may even cause starting failure.

[0003] Existing turbojet engine propellant start-up test benches can only test start-up performance under normal dynamic balance conditions and cannot simulate rotor imbalance fault conditions. Because special scenarios such as rotor damage and blade loss cannot be reproduced, the test data cannot reflect the start-up reliability under actual fault conditions. Engineers find it difficult to predict start-up risks and cannot carry out targeted optimization designs, resulting in a limited testing range for the test benches and failing to provide comprehensive support for the safety assessment of the engine's entire life cycle. Summary of the Invention

[0004] This invention provides a turbine propellant start-up test device, specifically solving the following technical problems: (1) The existing test bench cannot simulate the rotor imbalance caused by rotor damage and turbine blade loss, and cannot carry out start-up performance tests under special working conditions; (2) Existing test benches cannot simultaneously acquire key parameters such as the initial torque of turbine startup and blade deformation under unbalanced conditions, making it difficult to assess startup reliability.

[0005] To address the above technical problems, this invention provides a turbine propellant start-up test device, characterized by comprising a fixture 3, a gas generator 1, a guide rail 2, a support 11, a turbine 5, a measurement and monitoring component, a transmission component, and a data processing component; the guide rail 2 is fixed on the fixture 3 and arranged coaxially with the turbine 5, and the support 11 is slidably mounted on the guide rail 2; the turbine 5 is fixedly mounted to a locking member 6 via a transmission rod 14, and the transmission rod 14 is non-contact with the fixture 3; a counterweight 12 is detachably clamped on the blade of the turbine 5, and the clamping counterweight 12 is installed at the blade tip, middle, or root position to simulate the rotor dynamic balance failure state; the measurement and monitoring component is mounted on the support 11 and the transmission rod 14, the transmission component is fixed on the fixture 3 and connected to the transmission rod 14, and the data processing component is mounted on the support 11 and signal-connected to the measurement and monitoring component.

[0006] Furthermore, the measurement and monitoring component includes a displacement sensor 10 and a torque meter 13; the displacement sensor 10 is fixed on the bracket 11; the torque meter 13 is installed in series at the end of the transmission rod 14.

[0007] Furthermore, the transmission assembly includes an adjustable damper 15; the damper 15 is fixed on the fixture 3, and the input end of the damper 15 is connected to the end of the torque meter 13 away from the transmission rod 14.

[0008] Furthermore, the data processing component includes a data acquisition box 8 and a controller 16; the data acquisition box 8 is mounted on the bracket 11 via a horizontal adjustment slot 9 and is electrically connected to the displacement sensor 10 and the torque meter 13 respectively, for synchronously acquiring signals and transmitting them to the controller 16 for analysis, storage and display.

[0009] Furthermore, the gas generator 1 is fixed to one side of the fixture 3, with the gas injection direction facing the force-bearing surface of the turbine 5 blades, a rated working pressure of 0.5–2 MPa, and a gas temperature of 800–1200℃.

[0010] Furthermore, the clamping counterweight 12 weighs 5g–50g, is made of high-density tungsten alloy, and can be detachably installed using high-temperature resistant bolts, and is used to simulate rotor imbalance faults of different degrees.

[0011] Furthermore, a T-shaped groove is provided on the guide rail 2 for sliding cooperation with the T-shaped slider at the bottom of the bracket 11.

[0012] Furthermore, the displacement sensor 10 is a laser displacement sensor, and the torque meter 13 is a non-contact dynamic torque sensor.

[0013] Furthermore, the damper 15 is an adjustable hydraulic damper.

[0014] Furthermore, the displacement sensor 10 is installed at the same height as the highest point of the turbine blade, and the measurement direction is perpendicular to the blade surface.

[0015] Compared with the prior art, the present invention has the following significant advantages: (1) Accurately simulate specific unbalanced working conditions: Through the clamping counterweights made of tungsten alloy, with a weight range of 5g-50g and installation positions at the blade tip / middle / root, the typical unbalanced state caused by rotor damage and blade shedding can be accurately reproduced, filling the functional gap of the existing test bench, and the test scenario is closer to the actual fault working conditions. (2) Comprehensive and accurate acquisition of key parameters: The laser displacement sensor and non-contact dynamic torque meter are integrated to simultaneously acquire data on changes in starting torque and blade deformation. The data is highly accurate and has a fast response, providing comprehensive support for starting reliability assessment. (3) Strong structural adaptability and stability: The guide rail and turbine are coaxially designed, the bracket slides smoothly, the counterweight is easy to install and disassemble, the damper can adjust the load, adapt to different specifications of turbines and various unbalanced working conditions, and has high operating stability. (4) High efficiency and intuitive data: The data acquisition and processing are highly automated. The controller displays the test curve in real time, and the data can be directly exported for analysis, reducing the intensity of manual operation and improving the efficiency of the test and the accuracy of data interpretation.

[0016] This invention features a reasonable structural design and focused functions, and can be widely applied to fault condition testing of turbojet engine turbine propellant starting systems, which is of great significance for improving the safety and reliability of aero engines. Attached Figure Description

[0017] Figure 1 This is a frontal cross-sectional view of the present invention.

[0018] Figure 2 This is a three-dimensional structural diagram of the present invention.

[0019] In the diagram: 1. Gas generator; 2. Guide rail; 3. Fixture; 4. Support base; 5. Turbine; 6. Locking element; 7. Exhaust pipe; 8. Data acquisition box; 9. Lateral adjustment groove; 10. Displacement sensor; 11. Bracket; 12. Clamping counterweight; 13. Torque meter; 14. Transmission rod; 15. Damper; 16. Controller. Detailed Implementation

[0020] To make the objectives, contents, and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail below.

[0021] The present invention proposes a turbine propellant start-up test device, comprising: Fixture (3): serves as the mounting reference for the device, providing fixation and support for each functional component, with fixed feet at the bottom to ensure stability; Gas generator (1): Located on one side of the fixture (3), with the injection direction corresponding to the force-bearing surface of the turbine (5), it is used to generate high-temperature and high-pressure gunpowder gas to provide a power source for the turbine (5) to start. Guide rail (2): It is fixedly installed on the fixture (3) and coaxially arranged with the turbine (5). The guide rail (2) is provided with a T-shaped slide groove, and is made of No. 45 steel and quenched. Bracket (11): It is slidably installed in the T-shaped groove of the guide rail (2) by the T-shaped slider at the lower end, and can move along the axial direction of the guide rail (2). The bracket (11) is made of aluminum alloy and has a detachable horizontal adjustment groove (9) on the upper part. Turbine (5): It is fixed to the locking part (6) by the transmission rod (14). The transmission rod (14) and the fixture (3) are set in a non-contact manner. A tungsten alloy clamping counterweight (12) is detachably installed on the blade of the turbine (5). The weight of the clamping counterweight (12) is 5g-50g. It can be installed at the tip, middle or root of the turbine blade to simulate the rotor dynamic balance failure state. Measurement and monitoring components include a displacement sensor (10) and a torque meter (13). The displacement sensor (10) is fixed on the bracket (11) and is used to monitor the blade deformation during the turbine (5) startup process in real time. The torque meter (13) is connected in series at one end of the transmission rod (14) and is used to measure the initial torque of the turbine (5) startup and the torque change during the entire startup process. Transmission assembly: includes a damper (15), which is fixed on a fixture (3) and its input end is connected to the end of a torque meter (13) away from the transmission rod (14) to provide a stable load for starting the turbine (5); Data processing components include a data acquisition box (8) and a controller (16). The data acquisition box (8) is fixed on the transverse adjustment groove (9) and can move along the guide rail (2) with the bracket (11). The data acquisition box (8) is electrically connected to the displacement sensor (10) and the torque meter (13) respectively, and is used to acquire blade deformation data and torque data in real time, and transmit the data to the controller (16). The controller (16) is used for data storage, analysis and display.

[0022] The measurement and monitoring component is mounted on the bracket (11) or the transmission rod (14). The transmission component is fixed on the fixture (3) and connected to the transmission rod (14). The data processing component is mounted on the bracket (11).

[0023] Example: In this embodiment, the selection and installation methods of each component are as follows: (1) Fixture (3): It is made of high-strength cast iron and is integrally formed. The bottom is equipped with fixed feet. The fixture (3) has a reserved guide rail mounting surface and a damper fixing seat. The flatness of the mounting surface is ≤0.05mm to ensure the stability of the device during the test. (2) Gas generator (1): Select a solid propellant gas generator suitable for turbojet engine turbine start-up, with a rated working pressure of 0.5-2MPa and a gas injection temperature of 800-1200℃. Fix it on one side of the fixture (3) with a bracket. The distance between the injection port and the air inlet end of the turbine (5) blades is adjusted to 50-100mm to ensure that the gas acts efficiently on the turbine blades. (3) Guide rail (2) and bracket (11): The guide rail (2) is 1.5m long, the T-shaped slide is 20mm wide and 15mm deep; the bracket (11) has a reserved displacement sensor mounting hole and a horizontal adjustment groove fixing interface, the T-shaped slider and the slide are fitted with a clearance, the sliding resistance is ≤5N, and bolt locking can be provided; (4) Turbine (5) and clamping counterweight (12): The turbine (5) is selected from the test piece matched with the actual turbojet engine, and the blade material is high temperature alloy; the clamping counterweight (12) is made of tungsten alloy (high density, small volume, reducing interference with airflow), and the weight specifications are divided into four levels: 5g, 10g, 20g and 50g after including high temperature resistant bolts. It can be detached and installed at the tip, middle or root of the turbine blade to accurately simulate different degrees of rotor imbalance. (5) Measurement and monitoring components: The displacement sensor (10) is a laser displacement sensor (model: Keyence IL-300), which is installed at the same height as the highest point of the turbine blade and the measurement direction is perpendicular to the blade surface; the torque meter (13) is a non-contact dynamic torque sensor (model: HBM T40B), which is connected to the transmission rod (14) and the damper (15) through the flange. (6) Transmission components: The transmission rod (14) is made of 40Cr material, with a diameter of 20mm and a length of 300mm, and the surface is chrome-plated; the locking part (6) is a combination of anti-loosening nut and thrust washer to ensure that the turbine (5) is firmly fixed; the damper (15) is an adjustable hydraulic damper (model: SACHS 3150), which is fixed to the damper mounting seat of the fixture (3) by bolts; (7) Data processing components: The acquisition box (8) is a multi-channel data acquisition instrument (model: NI cDAQ-9178) with a sampling rate of ≥10kHz. It supports synchronous acquisition of analog and digital signals and is connected to the displacement sensor (10) and torque meter (13) via an aviation plug. The transverse adjustment groove (9) is a steel slide that can adjust the transverse position of the acquisition box (8). The controller (16) is an industrial tablet computer with built-in data processing software. It can display the torque curve and blade deformation curve in real time and supports data export and report generation.

[0024] The specific testing procedure for this device is as follows: (1) Working condition settings: According to the test requirements, select a tungsten alloy clamping counterweight (12) with a weight in the range of 5g-50g and install it on the tip, middle or root of the turbine (5) blade with high temperature resistant bolts (e.g., install a 20g counterweight at the tip to simulate the imbalance caused by the missing part of the blade); when different degrees of imbalance need to be simulated, change the weight of the counterweight or adjust the installation position. (2) Equipment debugging: Loosen the locking bolts of the bracket (11), move the bracket (11) along the guide rail (2), adjust the distance between the displacement sensor (10) and the turbine blade to 10mm (optimal measurement distance), and then lock the bracket (11); check the gap between the transmission rod (14) and the fixture (3) to ensure no contact interference; start the acquisition box (8) and the controller (16), and calibrate the torque meter (13) and the displacement sensor (10). (3) Load adjustment: Set the target damping torque by adjusting the knob of the damper (15) to simulate the load resistance when the turbine starts; (4) Test run: Start the gas generator (1), and the high temperature and high pressure gas generated by the combustion of gunpowder is injected onto the blades of the turbine (5) to drive the turbine (5) to rotate; the torque meter (13) collects the initial torque and torque change data in real time, the displacement sensor (10) monitors the blade deformation, and the acquisition box (8) transmits the two data to the controller (16) in a synchronized manner. The controller (16) plots the data curve in real time and stores it. (5) Operating condition switching and repeated test: After completing a set of unbalanced operating condition tests, turn off the gas generator (1), wait for the turbine (5) to stop completely and the device to cool down to room temperature, change the weight or installation position of the clamping counterweight (12), and repeat steps (2)-(4). (6) End of test: After all working conditions are tested, shut down all equipment, export the test data in the controller (16), and analyze the reliability of turbine start-up and the variation law of key parameters under different unbalanced conditions.

[0025] During the test, the acquisition box (8) synchronously acquired torque data and blade deformation data at a sampling interval of 0.1ms to ensure the capture of peak parameters at the moment of startup; the data analysis software built into the controller (16) automatically extracted key indicators such as initial startup torque, peak torque, torque fluctuation amplitude, and maximum blade deformation, and generated comparison charts. By analyzing the test data under different counterweight conditions, the influence of rotor imbalance on turbine startup performance can be clarified, and it can be determined whether the turbine can start smoothly under different fault conditions.

[0026] This invention can accurately simulate specific unbalanced operating conditions, obtain key parameters, and provide a scientific basis for the reliability assessment and optimization of turbine starting systems.

[0027] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A turbine propellant start-up test device, characterized in that, The device includes a fixture (3), a gas generator (1), a guide rail (2), a bracket (11), a turbine (5), a measurement and monitoring component, a transmission component, and a data processing component. The guide rail (2) is fixed on the fixture (3) and arranged coaxially with the turbine (5). The bracket (11) is slidably mounted on the guide rail (2). The turbine (5) is fixedly mounted to the locking component (6) via a transmission rod (14). The transmission rod (14) is not in contact with the fixture (3). A counterweight (12) is detachably clamped on the blade of the turbine (5). The counterweight (12) is installed at the blade tip, blade middle, or blade root to simulate the rotor dynamic balance failure state. The measurement and monitoring component is mounted on the bracket (11) and the transmission rod (14). The transmission component is fixed on the fixture (3) and connected to the transmission rod (14). The data processing component is mounted on the bracket (11) and connected to the measurement and monitoring component.

2. The turbine propellant start-up test device according to claim 1, characterized in that, The measurement and monitoring components include a displacement sensor (10) and a torque meter (13); the displacement sensor (10) is fixed on the bracket (11); the torque meter (13) is installed in series at the end of the transmission rod (14).

3. The turbine propellant start-up test device according to claim 1, characterized in that, The transmission assembly includes an adjustable damper (15); the damper (15) is fixed on the fixture (3), and the input end of the damper (15) is connected to the end of the torque meter (13) away from the transmission rod (14).

4. The turbine propellant start-up test device according to claim 1, characterized in that, The data processing component includes a data acquisition box (8) and a controller (16). The data acquisition box (8) is mounted on a bracket (11) via a horizontal adjustment slot (9) and is electrically connected to a displacement sensor (10) and a torque meter (13) respectively. It is used to synchronously acquire signals and transmit them to the controller (16) for analysis, storage and display.

5. The turbine propellant start-up test device according to claim 1, characterized in that, The gas generator (1) is fixed to one side of the fixture (3), with the gas injection direction facing the force-bearing surface of the turbine (5) blades. The rated working pressure is 0.5–2 MPa and the gas temperature is 800–1200℃.

6. The turbine propellant start-up test device according to claim 1, characterized in that, The clamping counterweight (12) weighs 5g–50g, is made of high-density tungsten alloy, and can be detached and installed by high-temperature resistant bolts to simulate different degrees of rotor imbalance faults.

7. The turbine propellant start-up test device according to claim 1, characterized in that, The guide rail (2) has a T-shaped groove for sliding cooperation with the T-shaped slider at the bottom of the bracket (11).

8. The turbine propellant start-up test device according to claim 2, characterized in that, The displacement sensor (10) is a laser displacement sensor, and the torque meter (13) is a non-contact dynamic torque sensor.

9. The turbine propellant start-up test device according to claim 3, characterized in that, The damper (15) is an adjustable hydraulic damper.

10. The turbine propellant start-up test device according to claim 2, characterized in that, The displacement sensor (10) is installed at the same height as the highest point of the turbine blade, and the measurement direction is perpendicular to the blade surface.

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