Test bed for testing high-pressure and high-speed aviation hydraulic pump

Abstract

The invention discloses a test bed for testing a high-pressure and high-speed aviation hydraulic pump, and belongs to the technical field of hydraulic pressure. The test bench is mainly composed of a power driving system, a hydraulic control system, an electrical control system, a data acquisition and processing system and the like. Shafting centering is achieved through an integrated box body, a tested pump, a torque rotating speed sensor and a high-speed variable frequency motor form a transmission mechanism through a star-shaped zero-backlash coupler, the high-speed variable frequency motor drives the high-pressure high-speed aviation hydraulic pump to operate through the coupler, and the precise zero-backlash coupler is free of transmission gaps and has good transmission synchronism. According to the high-pressure high-speed pump testing device, various parameters such as the torque, the rotating speed, the pressure, the flow and the temperature of the high-pressure high-speed pump can be accurately tested, and a displacement verification running-in test, an efficiency test, an impact test, a full-load test, efficiency inspection, sealing performance inspection and the like are completed.

Description

Technical Field

[0001] The invention belongs to the technical field of hydraulics in mechanical engineering, and in particular relates to a high-pressure and high-speed aviation hydraulic pump test bench. Background Art

[0002] As the power element of a hydraulic system, a high-pressure, high-speed aviation hydraulic pump is a key component that influences the performance of the entire system. Therefore, accurate performance testing of high-pressure, high-speed aviation hydraulic pumps is crucial during their development. It serves as a crucial means of verifying and evaluating their performance, and provides a crucial basis for improving their structural design and processing technology.

[0003] At present, it is difficult for the test bench of aviation hydraulic pumps to maintain a relatively stable balance under high speed conditions, especially the alignment error between the drive motor and the pump shaft system needs to be controlled at the micron level. If the mounting ring or clamping plate is poorly designed, slight offsets will cause vibrations, aggravate mechanical wear and interfere with sensor readings. In the prior art, the utility model patent with publication number CN222254283U proposes a correction clamping technology. By using two clamping plates that can move relative to each other, it can not only clamp and fix the base of the hydraulic pump to be tested, but also perform position correction on the hydraulic pump to be tested so that the axis of the hydraulic pump to be tested and the axis of the drive motor are on the same straight line. However, the complex structure of this technology increases the difficulty of maintenance. In addition, under high-pressure and high-speed conditions, signal noise interferes with measurement accuracy, resulting in insufficient test accuracy. Therefore, there is a need for a hydraulic pump test bench that can perform stable, high-precision and automated testing under high-speed conditions. Summary of the Invention

[0004] The present invention aims to address the deficiencies of the prior art and to provide a high-pressure and high-speed aviation hydraulic pump test bench.

[0005] The object of the present invention is achieved through the following technical solutions: a high-pressure and high-speed aviation hydraulic pump test bench, the test bench consisting of a power drive system, a hydraulic control system, an electrical control system and a data acquisition system; The power drive module is tested using an open hydraulic system, with an oil supply pump supplying oil. The two-way oil supply of the pump is achieved through a reversing circuit composed of a two-way cartridge valve. The hydraulic control system is composed of a loading control unit and a flow test circuit switching unit. The loading control unit is used to test various performance parameters under different loads, and the test circuit switching unit is used to test the output flow at different speeds. The electrical control system is composed of low-voltage electrical appliances and a programmable controller (PLC). The PLC controls the entire test process of the hydraulic pump through logic operations, sequential control, and arithmetic operation instructions, as well as the input and output of digital and analog signals. The data acquisition and processing system includes a pressure sensor, a temperature sensor, a flow sensor, a torque and speed sensor and a host computer, and realizes signal detection, data processing, graph drawing, test report output and data management.

[0006] Furthermore, in the hydraulic control system, shaft alignment is achieved through an integrated box. The measured pump, torque and speed sensor, and high-speed variable frequency motor form a transmission mechanism through a star-shaped zero-backlash coupling. The high-speed variable frequency motor drives the high-pressure and high-speed aviation hydraulic pump through the star-shaped zero-backlash coupling. The zero-backlash coupling has no transmission clearance.

[0007] Furthermore, a butterfly valve is provided in the hydraulic control system to test the self-priming ability of the pump under test as needed.

[0008] Furthermore, a pressure sensor module is installed at the oil inlet of the pump under test.

[0009] Furthermore, the flow direction conversion of the inlet and outlet media of the hydraulic control system is formed into a two-position four-way reversing circuit through a two-way cartridge valve control module.

[0010] Furthermore, the two-way cartridge valve control module is composed of a cartridge valve, a control cover, a solenoid reversing valve and a one-way valve; the solenoid reversing valve and the one-way valve together form a pilot control circuit to control the opening and closing of the cartridge valve to form different oil supply circuits.

[0011] Furthermore, the loading pressure of the hydraulic control system is realized through a proportional relief valve, and a low-pressure impact switching circuit is composed of a cartridge valve, a control cover plate and an electromagnetic reversing valve, and a proportional relief valve is configured at the same time.

[0012] Furthermore, the host computer in the data acquisition and processing system controls the acquisition card through LabVIEW software. The acquisition card has an analog output function, which provides signal settings for the speed of the oil supply pump and the pump under test, as well as the settings of the oil supply pressure and the oil outlet pressure. The sensor uses current signal transmission, and then transmits the sensor signal to the acquisition card through the current-to-voltage module.

[0013] Compared with the prior art, the present invention has the following beneficial effects: The high-pressure, high-speed aviation hydraulic pump test bench provided by the present invention utilizes power drive, hydraulic control, electrical control, and data acquisition to enable automated, high-precision testing of high-pressure, high-speed aviation hydraulic pump test items. It can accurately test various parameters of the high-speed pump, including torque, speed, pressure, flow rate, and temperature, and perform displacement verification, run-in tests, efficiency tests, impact tests, full-load tests, efficiency checks, and sealing performance checks. The high-pressure, high-speed aviation hydraulic pump test bench provided by the present invention utilizes an integrated housing to achieve shaft alignment, thereby ensuring dynamic balance at high speeds. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is the hydraulic principle diagram of the present invention.

[0015] Figure 2 This is a schematic diagram of the two-way cartridge valve control circuit.

[0016] Figure 1 , Figure 2 Explanation of reference numerals: 5-butterfly valve; 6-frequency conversion motor; 7-vane pump; 8-bell cover; 9-coupling; 13-first high-pressure filter; 14-second high-pressure filter; 15-first cartridge valve; 16-first control cover plate; 17-first solenoid reversing valve; 19-throttling control cover plate; 21-temperature sensor; 27-first flow sensor; 29-second cartridge valve; 30-second control cover plate; 31-second solenoid reversing valve; 32-first Proportional relief valve; 33-second proportional relief valve; 34-check valve; 35-third solenoid reversing valve; 36-second flow sensor; 38-oil cooler; 39-return oil filter; 40-third cartridge valve; 41-third control cover; 42-fourth solenoid reversing valve; 49-high-speed variable frequency motor; 50-torque and speed sensor; 51-digital-to-analog conversion module; 52-first star-shaped zero-backlash coupling; 53-second star-shaped zero-backlash coupling.

[0017] Figure 3 This is a cross-sectional view of the high-pressure and high-speed hydraulic pump test bench.

[0018] Figure 4 This is a top view of the high-pressure and high-speed hydraulic pump test bench.

[0019] Figure 5 This is a schematic diagram of the pump group structure. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described below with reference to the accompanying drawings and examples. It should be understood that the specific examples described herein are only used to explain the present invention and are not intended to limit the present invention.

[0021] like Figure 1-Figure 5 As shown, the present invention provides a high-pressure and high-speed aviation hydraulic pump test bench, the cross-sectional view and top view are as shown in FIG. Figure 3 and Figure 4 As shown, the test bench includes a hydraulic system and an electrical system.

[0022] The hydraulic system of the present invention mainly includes a power drive system and a hydraulic control system.

[0023] Regarding the power drive system, this test bench utilizes an open-loop hydraulic system. To ensure proper pump suction at 14,000 rpm, an oil supply pump is used. A reversing circuit composed of two-way cartridge valves enables bidirectional high-speed pump inlet and outlet flow and rotational direction conversion. The bench also features a pressure control unit and oil filtration unit.

[0024] The hydraulic control system primarily consists of a load control unit and a flow test circuit switching unit. The load control unit enables testing of various performance parameters under varying loads. A test circuit switching unit is included to test output flow at various speeds, ensuring full flow testing of the pump under test. The system is capable of testing a flow range of 0.16 to 150 L / min, detecting ultra-low leakage flows at leak ports, and detecting pressure at the inlet, outlet, and leak ports.

[0025] like Figure 1 As shown, the hydraulic system comprises a pump under test, a torque and speed sensor 50, a digital-to-analog conversion module 51, and a high-speed variable-frequency motor 49, which form a transmission mechanism via a first star-shaped zero-backlash coupling 52 and a second star-shaped zero-backlash coupling 53. The high-speed variable-frequency motor 49 drives the high-pressure, high-speed aviation hydraulic pump through the star-shaped zero-backlash coupling. The precision zero-backlash coupling has no transmission clearance and offers excellent transmission synchronization. The speed increase and decrease of the pump under test are controlled by the high-speed variable-frequency motor 49, with a speed control range of 1000-12000 rpm and a maximum speed of 14000 rpm. During manufacturing, an integrated housing is used to achieve shaft alignment, thereby ensuring dynamic balancing of the test bench at high speeds.

[0026] To ensure the pump under test does not experience cavitation during high-speed operation, the hydraulic system uses an oil supply pump. A variable-frequency motor 6 drives a vane pump 7 through a bell housing 8 and coupling 9. A butterfly valve 5 is installed to test the self-priming capacity of the pump under test as needed. An optional pressure sensor module is installed at the pump's oil inlet, with a detection pressure range of -1 to 5 bar.

[0027] like Figure 2 As shown, to meet the requirements for both inlet and outlet flow and rotational direction conversion for a bidirectional high-speed pump, the inlet and outlet medium flow conversion is implemented through a two-position, four-way reversing circuit using a two-way cartridge valve control module. This module comprises four first cartridge valves 15, a first control cover plate 16, a first solenoid reversing valve 17, and a check valve 34. The solenoid reversing valve 17 and the check valve 34 together form a pilot control circuit, controlling the opening and closing of the first cartridge valves 15 to create different oil supply circuits. This module avoids the switching shock associated with large-diameter electro-hydraulic directional valves and the lower pressure rating of the T-port.

[0028] The hydraulic system selects the steering control of the variable frequency motor 6 to match the switching of the oil supply circuit, thereby meeting the needs of bidirectional testing.

[0029] To ensure the hydraulic system's ability to continuously adjust load pressure, the first proportional relief valve 32 achieves the loading pressure, with a range of 14 to 280 bar. A low-pressure surge switching circuit is formed by the second cartridge valve 29, the second control cover plate 30, and the second solenoid reversing valve 31. A second proportional relief valve 33 is also included, allowing for a loading pressure range of 10 to 60 bar. To ensure no-load flow testing, the first cartridge valve 15 and the throttling control cover plate 19 are used to minimize the impact of the proportional relief valve's minimum opening pressure on the test pressure, ensuring the minimum loading pressure (14 bar) is achieved.

[0030] The third solenoid reversing valve 35, third cartridge valve 40, third control cover plate 41, and fourth solenoid reversing valve 42 are used to switch the flow test circuit. This hydraulic system has the ability to test a flow rate range of 0.16 to 150 L / min. The second flow sensor 36 detects a flow rate range of 1 to 250 L / min.

[0031] A first flow sensor 27 is used to detect ultra-low leakage flow at the oil leakage port, with a detection flow range of 0.16 to 16 L / min. The hydraulic system also has the ability to detect pressure at the oil inlet, outlet, and leakage ports. The inlet and outlet pressure detection range is 0 to 400 bar, and the leakage port pressure detection range is 0 to 10 bar.

[0032] By configuring the temperature sensor 21, the hydraulic system has the ability to detect the temperature of the oil inlet, outlet and leakage port, and the temperature detection range is -50~120℃.

[0033] The torque and speed sensor 50 and the digital-to-analog conversion module 51 are provided to detect torque and speed. The torque detection range is 0-30 N·m, and the speed detection range is 0-20000 rpm.

[0034] By configuring the first high-pressure filter 13 and the second high-pressure filter 14 with filtering accuracies of 10μ and 5μ, it is ensured that the solid particle contamination level of the test oil is not higher than NAS7 level.

[0035] The hydraulic system features an independent circulating cooling and filtration system. The oil cooler (38) has its own oil pump and motor for circulating cooling and filtration, with a cooling capacity of 18,000 kcal / h. The return oil filter (39) has a filtration accuracy of 20 μm. The oil cooler is a fixed temperature type that can be set within the range of 20-45°C according to actual needs.

[0036] According to the test requirements, if it is necessary to test the pressure resistance level of the pump housing and the rotary oil seal, a loading test can be performed on the leakage oil port (this module is not set in the hydraulic principle diagram).

[0037] The electrical system of the present invention is described below, primarily comprising an electrical control system and a data acquisition system. The electrical control system consists of low-voltage electrical equipment and a programmable logic controller (PLC). The PLC controls the entire high-speed pump testing process through operational instructions such as logic operations, sequential control, and arithmetic operations, as well as the input and output of digital and analog signals. Its primary components include circuit breakers, thermal relays, contactors, and frequency converters, enabling functions such as equipment start / stop and motor control.

[0038] The basic functions of a data acquisition and processing system include signal detection, data processing, graphing, test report output, and data management. Detection components include pressure sensors, temperature sensors, flow sensors, torque and speed sensors, and more. Data acquisition and processing is the core of the entire system, encompassing an industrial computer, data acquisition card, and display.

[0039] In the data acquisition system, the host computer controls the acquisition card through LabVIEW software. The acquisition card is a PCI-6229, a high-performance National Instruments (NI) card from the United States. It features 32 16-bit analog inputs (250 kS / s), four 16-bit analog outputs (833 kS / s), 48 digital I / O channels, a 32-bit counter, and a digital trigger. The acquisition card also has analog outputs, providing signals for setting the speed of the oil supply pump and the pump being measured, as well as for setting the oil supply and outlet pressures.

[0040] To prevent interference from signals like pressure, temperature, flow, torque, and speed during long-distance transmission, the sensor uses current signal transmission, which is then transmitted to the acquisition card via a current-to-voltage module. The acquisition card also converts a 5V digital signal into a 24V switching signal via a 5V relay, which is used to control the switching of motors and valves.

[0041] The above embodiments are used to illustrate the present invention rather than to limit the present invention. Any modifications and changes made to the present invention within the spirit of the present invention and the protection scope of the claims shall fall within the protection scope of the present invention.

Claims

1. A high-pressure and high-speed aviation hydraulic pump test bench, characterized in that: The test bench consists of a power drive system, hydraulic control system, electrical control system and data acquisition system; The power drive module is tested using an open hydraulic system, with an oil supply pump supplying oil. The two-way oil supply of the pump is achieved through a reversing circuit composed of a two-way cartridge valve. The hydraulic control system is composed of a loading control unit and a flow test circuit switching unit. The loading control unit is used to test various performance parameters under different loads, and the test circuit switching unit is used to test the output flow at different speeds. The electrical control system is composed of low-voltage electrical appliances and a programmable controller (PLC). The PLC controls the entire test process of the hydraulic pump through logic operations, sequential control, and arithmetic operation instructions, as well as the input and output of digital and analog signals. The data acquisition and processing system includes a pressure sensor, a temperature sensor, a flow sensor, a torque and speed sensor and a host computer, and realizes signal detection, data processing, graph drawing, test report output and data management.

2. The high-pressure and high-speed aviation hydraulic pump test bench according to claim 1, characterized in that: In the hydraulic control system, shaft alignment is achieved through an integrated housing. The pump under test, torque and speed sensor, and high-speed variable frequency motor form a transmission mechanism through a star-shaped zero-backlash coupling. The high-speed variable frequency motor drives the high-pressure and high-speed aviation hydraulic pump through the star-shaped zero-backlash coupling. The zero-backlash coupling has no transmission clearance.

3. The high-pressure and high-speed aviation hydraulic pump test bench according to claim 2, characterized in that: A butterfly valve is set in the hydraulic control system to test the self-priming ability of the pump under test as needed.

4. The high-pressure and high-speed aviation hydraulic pump test bench according to claim 3, characterized in that: Set the pressure sensor module to be installed at the oil inlet of the pump under test.

5. The high-pressure and high-speed aviation hydraulic pump test bench according to claim 1, characterized in that: The flow direction conversion of the inlet and outlet media of the hydraulic control system is formed by a two-position four-way reversing circuit through a two-way cartridge valve control module.

6. The high-pressure and high-speed aviation hydraulic pump test bench according to claim 5, characterized in that: The two-way cartridge valve control module consists of a cartridge valve, a control cover, a solenoid reversing valve and a one-way valve; the solenoid reversing valve and the one-way valve together form a pilot control circuit to control the opening and closing of the cartridge valve to form different oil supply circuits.

7. The high-pressure and high-speed aviation hydraulic pump test bench according to claim 6, characterized in that: The loading pressure of the hydraulic control system is realized through a proportional relief valve. A low-pressure impact switching circuit is composed of a cartridge valve, a control cover plate and an electromagnetic reversing valve, and a proportional relief valve is configured at the same time.

8. The high-pressure and high-speed aviation hydraulic pump test bench according to claim 1, characterized in that: In the data acquisition and processing system, the host computer controls the acquisition card through LabVIEW software. The acquisition card has an analog output function, which provides signal settings for the speed of the oil supply pump and the measured pump, as well as the settings of the oil supply pressure and the oil outlet pressure. The sensor uses current signal transmission, and then transmits the sensor signal to the acquisition card through the current-to-voltage module.

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