CN120626477A - A high-pressure and high-speed aviation hydraulic pump test bench - Google Patents
A high-pressure and high-speed aviation hydraulic pump test benchInfo
- Publication number
- CN120626477A CN120626477A CN202511134821.9A CN202511134821A CN120626477A CN 120626477 A CN120626477 A CN 120626477A CN 202511134821 A CN202511134821 A CN 202511134821A CN 120626477 A CN120626477 A CN 120626477A
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- CN
- China
- Prior art keywords
- pressure
- test
- speed
- pump
- hydraulic pump
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B51/00—Testing machines, pumps, or pumping installations
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
本发明公开了一种高压高速航空液压泵测试试验台，属于液压技术领域。该试验台主要由动力驱动系统、液压控制系统、电气控制系统和数据采集和处理系统等组成。利用一体式的箱体来实现轴系对中，被测泵、转矩转速传感器和高速变频电机通过星形零齿隙联轴器组成传动机构，高速变频电机通过联轴器驱动高压高速航空液压泵运转，精密型零齿隙联轴器无传动间隙，具有良好的传动同步性。本发明可以对高压高速泵的转矩、转速、压力、流量和温度的等各个参数进行精确测试，完成排量验证跑合试验、效率试验、冲击试验、满载试验、效率检查以及密封性能检查等。
The present invention discloses a high-pressure, high-speed aviation hydraulic pump test bench, which belongs to the field of hydraulic technology. The test bench is mainly composed of a power drive system, a hydraulic control system, an electrical control system, and a data acquisition and processing system. An integrated box is used to achieve shaft alignment. The pump under test, the torque and speed sensor, and the 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, high-speed aviation hydraulic pump to operate through the coupling. The precision zero-backlash coupling has no transmission gap and has good transmission synchronization. The present invention can accurately test various parameters such as torque, speed, pressure, flow rate, and temperature of the high-pressure, high-speed pump, and complete displacement verification running-in test, efficiency test, impact test, full-load test, efficiency inspection, and sealing performance inspection.
Description
Technical Field
The invention belongs to the technical field of hydraulic pressure in mechanical engineering, and particularly relates to a high-pressure high-speed aviation hydraulic pump test bed.
Background
The high-pressure high-speed aviation hydraulic pump is used as a power element of a hydraulic system and is a key element for influencing the performance of the whole system. Therefore, the method has important significance for the accurate test of the performance of the high-pressure high-speed aviation hydraulic pump in the research and development process, is an important means for checking and judging the performance of the high-pressure high-speed aviation hydraulic pump, and provides important basis for the improvement of the structural design and the improvement of the processing technology.
At present, under the condition of high rotating speed, the test bed is difficult to maintain stable balance, and especially the shafting centering error between the driving motor and the pump needs to be controlled at a micron level. If the mounting ring or clamping plate is poorly designed, small excursions can cause vibrations that exacerbate mechanical wear and interfere with sensor readings. In the prior art, the utility model patent with the publication number of CN222254283U provides a correction clamping technology, and the clamping plates which can move oppositely can be used for clamping and fixing the base of the hydraulic pump to be tested, and simultaneously, the position of the hydraulic pump to be tested can be corrected, so that the axis of the hydraulic pump to be tested and the axis of the driving motor are positioned on the same straight line, but the complex structure of the technology increases the maintenance difficulty. In addition, signal noise interferes with measurement accuracy under high-pressure and high-speed conditions, resulting in insufficient test accuracy. Therefore, there is a need for a hydraulic pump test stand that can perform stable, high precision and automated testing at high rotational speed conditions.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a high-pressure high-speed aviation hydraulic pump test bed.
The invention aims at realizing the technical scheme that the high-pressure high-speed aviation hydraulic pump test bed consists of a power driving system, a hydraulic control system, an electric control system and a data acquisition system;
The power driving module adopts an open hydraulic system for testing, adopts a mode of supplying oil by an oil supply pump, and realizes bidirectional oil supply of the pump through a reversing loop formed by two-way cartridge valves;
the hydraulic control system consists of a loading control unit and a flow test loop switching unit, the loading control unit is used for testing various performance parameters under different loads, and the test loop switching unit is used for testing output flow under different rotating speeds;
the electrical control system consists of a low-voltage electric appliance and a Programmable Logic Controller (PLC), and the PLC controls the whole testing process of the hydraulic pump through logic operation, sequential control and arithmetic operation instructions, and input and output of digital quantity and analog quantity signals;
The data acquisition and processing system comprises a pressure sensor, a temperature sensor, a flow sensor, a torque and rotation speed sensor and an upper computer, and realizes signal detection, data processing, graph drawing, test report output and data management.
Further, in the hydraulic control system, shaft centering is realized through an integrated box body, a transmission mechanism is formed by a tested pump, a torque rotating speed sensor and a high-speed variable frequency motor through a star-shaped zero-backlash coupler, the high-speed variable frequency motor drives a high-pressure high-speed aviation hydraulic pump to operate through the star-shaped zero-backlash coupler, and the zero-backlash coupler has no transmission clearance.
Further, a butterfly valve is arranged in the hydraulic control system, and self-priming capability test of the tested pump is carried out according to the requirement.
Further, a pressure sensor module is arranged and installed at an oil inlet of the pump to be tested.
Further, the flow direction of inlet and outlet media of the hydraulic control system is converted through a two-way cartridge valve control module to form a two-position four-way reversing loop.
The two-way cartridge valve control module is composed of a cartridge valve, a control cover plate, an electromagnetic reversing valve and a one-way valve, wherein the electromagnetic reversing valve and the one-way valve form a pilot control loop together, and the opening and closing of the cartridge valve are controlled to form different oil supply loops.
Furthermore, the loading pressure of the hydraulic control system is realized through a proportional overflow valve, a low-pressure impact switching loop is formed through a cartridge valve, a control cover plate and an electromagnetic reversing valve, and the proportional overflow valve is arranged at the same time.
Further, an upper computer in the data acquisition and processing system controls an acquisition card through labview software, the acquisition card has an analog output function, signal setting is provided for the rotating speeds of the oil supply pump and the tested pump, oil supply pressure setting and oil outlet pressure setting are respectively provided for the oil supply pump and the tested pump, a sensor adopts current signal transmission, and sensor signals are transmitted to the acquisition card through a current-voltage conversion module.
Compared with the prior art, the invention has the following beneficial effects:
The high-pressure high-speed aviation hydraulic pump test bench provided by the invention can realize the automation and high-precision test of high-pressure high-speed aviation hydraulic pump test projects through power driving, hydraulic control, electric control and data acquisition, can accurately test various parameters such as torque, rotating speed, pressure, flow and temperature of a high-speed pump, and can complete displacement verification running-in test, efficiency test, impact test, full load test, efficiency test, sealing performance test and the like. The high-pressure high-speed aviation hydraulic pump test bed provided by the invention realizes shafting centering by utilizing the integrated box body, thereby guaranteeing the dynamic balance of the test bed under high rotating speed.
Drawings
Fig. 1 is a hydraulic schematic of the present invention.
FIG. 2 is a schematic diagram of a two-way cartridge valve control loop.
The reference numbers of fig. 1 and 2 show that the valve comprises a 5-butterfly valve, a 6-variable frequency motor, a 7-vane pump, an 8-bell jar, a 9-coupler, a 13-first high-pressure filter, a 14-second high-pressure filter, a 15-first cartridge valve, a 16-first control cover plate, a 17-first electromagnetic reversing valve, a 19-throttling type control cover plate, a 21-temperature sensor, a 27-first flow sensor, a 29-second cartridge valve, a 30-second control cover plate, a 31-second electromagnetic reversing valve, a 32-first proportional overflow valve, a 33-second proportional overflow valve, a 34-one-way valve, a 35-third electromagnetic reversing valve, a 36-second flow sensor, a 38-oil cooler, a 39-oil return filter, a 40-third cartridge valve, a 41-third control cover plate, a 42-fourth electromagnetic reversing valve, a 49-high-speed variable frequency motor, a 50-torque speed sensor, a 51-temperature sensor, a 52-first star-shaped zero backlash coupler and a 53-second star-shaped zero backlash coupler.
Fig. 3 is a cross-sectional view of a high-pressure high-speed hydraulic pump test stand.
Fig. 4 is a top view of a high pressure, high speed hydraulic pump test stand.
Fig. 5 is a schematic diagram of a pump set.
Detailed Description
The present invention will be further described with reference to the drawings and examples in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the detailed description and specific examples, while indicating the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.
The invention provides a high-pressure high-speed aviation hydraulic pump test stand, as shown in fig. 1-5, and a cross-sectional view and a top view are shown in fig. 3 and 4, wherein the test stand comprises a hydraulic system and an electric system.
The hydraulic system mainly comprises a power driving system and a hydraulic control system.
In the aspect of a power driving system, the test bed adopts an open hydraulic system to test, and adopts a mode of supplying oil by an oil supply pump in order to ensure the normal oil absorption of the pump at a high speed of 14000 rpm. Meanwhile, through a reversing loop formed by two-way cartridge valves, the flow direction conversion and the rotation direction conversion of inlet and outlet media of the bidirectional high-speed pump are realized. Meanwhile, the hydraulic oil filter is also provided with a pressure control unit and an oil filtering unit.
The hydraulic control system mainly comprises a loading control unit and a flow test loop switching unit. And testing various performance parameters under different loads is realized through the loading control unit. And a test loop switching unit is arranged for testing the output flow at different rotating speeds, so that the full flow test of the tested pump is ensured. The system has the testing capability of a flow range of 0.16-150L/min, the detection capability of ultralow leakage flow of the leakage oil port and the pressure detection capability of the oil inlet, the oil outlet and the leakage oil port.
As shown in fig. 1, a measured pump, a torque rotation speed sensor 50, a digital-to-analog conversion module 51 and a high-speed variable-frequency motor 49 in the hydraulic system form a transmission mechanism through a first star-shaped zero-backlash coupler 52 and a second star-shaped zero-backlash coupler 53, and the high-speed variable-frequency motor 49 drives a high-pressure high-speed aviation hydraulic pump to operate through the star-shaped zero-backlash coupler. The precise zero-backlash coupler has no transmission clearance and good transmission synchronism. The speed up and down of the pump to be tested is controlled by a high-speed variable frequency motor 49, the rotation speed is controlled to be 1000-12000rpm, and the highest rotation speed is 14000rpm. During manufacturing, the integrated box body is adopted to realize shafting centering, so that dynamic balance of the test bed under high rotation speed is realized.
In order to ensure that the pump to be tested cannot generate a suction phenomenon during high-speed operation, a hydraulic system adopts a mode of supplying oil by an oil supply pump. The variable frequency motor 6 drives the vane pump 7 to operate through the bell jar 8 and the coupler 9. And the butterfly valve 5 is arranged, the self-priming capability test of the tested pump can be carried out according to the requirement, and the alternative pressure sensor module is arranged at the oil inlet of the tested pump, and the detection pressure range is-1-5 bar.
As shown in fig. 2, in order to meet the requirements of flow direction conversion and rotation direction conversion of inlet and outlet media of the bidirectional high-speed pump, the flow direction conversion of inlet and outlet media forms a two-position four-way reversing loop through a two-way cartridge valve control module, and the module consists of four first cartridge valves 15, a first control cover plate 16, a first electromagnetic reversing valve 17 and a one-way valve 34. The electromagnetic directional valve 17 and the one-way valve 34 together form a pilot control loop to control the opening and closing of the first cartridge valve 15 so as to form different oil supply loops. The adoption of the module avoids the situation that the pressure resistance level of the T port is lower due to the reversing impact when the large-drift-diameter electro-hydraulic reversing valve is adopted for reversing.
The hydraulic system selects the steering control of the variable frequency motor 6 to match according to the switching of the oil supply loop, thereby meeting the requirement of bidirectional test.
In order to meet the continuous adjustment capability of the hydraulic system on the load pressure, the loading pressure is realized through the first proportional relief valve 32, and the loading pressure range is 14-280 bar. The low-pressure impact switching circuit is formed by the second cartridge valve 29, the second control cover plate 30 and the second electromagnetic directional valve 31, and meanwhile, the second proportional overflow valve 33 is configured, and the loading pressure range is 10-60 bar. In order to ensure the requirement of the empty-load flow test, the first cartridge valve 15 and the throttle control cover plate 19 are selected, so that the influence of the minimum opening pressure of the proportional overflow valve on the test pressure is avoided, and the realization of the minimum loading pressure (14 bar) is ensured.
The third electromagnetic directional valve 35, the third cartridge valve 40, the third control cover plate 41 and the fourth electromagnetic directional valve 42 are used for switching flow test loops, and the hydraulic system has the test capability of a flow range of 0.16-150L/min. The second flow sensor 36 detects a flow rate in a range of 1 to 250L/min.
The first flow sensor 27 is adopted to detect the ultralow leakage flow of the oil leakage port, and the detection flow range is 0.16-16L/min. Meanwhile, the hydraulic system has the pressure detection capability of the oil inlet, the oil outlet and the oil leakage port, the pressure detection range of the oil inlet and the oil outlet is 0-400 bar, and the pressure detection range of the oil leakage port is 0-10 bar.
By configuring the temperature sensor 21, the hydraulic system has the temperature detection capability of the oil inlet, the oil outlet and the oil leakage port, and the temperature detection range is-50-120 ℃.
By providing the torque/rotation speed sensor 50 and the digital-to-analog conversion module 51, the torque and rotation speed are detected, the torque detection range is 0 to 30 N.m, and the rotation speed detection range is 0 to 20000rpm.
By providing the first high-pressure filter 13 and the second high-pressure filter 14 with a filtration accuracy of 10 mu and 5 mu, the solid particle contamination level of the test oil is ensured to be not higher than the NAS7 level.
The hydraulic system is provided with an independent circulating cooling and filtering system, the oil cooler 38 carries out circulating cooling and filtering by an oil pump motor, the cooling capacity reaches 18000Kcal/h, and the filtering precision of the oil return filter 39 is 20 mu. The oil cooler is of a temperature fixed type and can be set in a range of 20-45 ℃ according to actual needs.
According to the test requirement, if the pressure-resistant pressure grade of the pump shell and the rotary oil seal needs to be tested, the loading test can be carried out on the oil leakage port (the module is not arranged in the hydraulic schematic diagram).
The electrical system of the present invention is described below as comprising mainly an electrical control system and a data acquisition system. The electric control system consists of a low-voltage electric appliance and a programmable controller PLC, and the PLC controls the whole test process of the high-speed pump through operation instructions such as logic operation, sequential control, arithmetic operation and the like, and input and output of digital quantity and analog quantity signals.
The basic functions of the data acquisition and processing system are signal detection, data processing, graphic drawing, test report output and data management, and the detection elements comprise a pressure sensor, a temperature sensor, a flow sensor, a torque and rotation speed sensor and the like. The data acquisition and processing are the core of the whole system, and comprise an industrial personal computer, a data acquisition card, a display and the like.
In the data acquisition system, an upper computer controls an acquisition card through labview software, the acquisition card is PCI-6229, is a high-performance acquisition card of the American NI, and internally comprises 16-bit 32-path analog input (250 kS/s), 4-path 16-bit analog output (833 kS/s), 48-path digital I/O, a 32-bit counter, digital triggering and the like. The acquisition card has an analog output function, and provides signal setting for the rotation speeds of the oil supply pump and the tested pump, as well as setting of oil supply pressure and setting of oil outlet pressure.
In order to prevent signal interference of pressure, temperature, flow, torque, rotating speed and the like in long-distance transmission, the sensor adopts current signal transmission, and then the current-to-voltage module transmits the sensor signal to the acquisition card. In addition, the acquisition card is provided with a 5V digital signal, and the signal is converted into a 24V switching value signal through a 5V relay, so as to control the switching of a motor and a valve.
The above-described embodiments are intended to illustrate the present invention, not to limit it, and any modifications and variations made thereto are within the spirit of the invention and the scope of the appended claims.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202511134821.9A CN120626477A (en) | 2025-08-14 | 2025-08-14 | A high-pressure and high-speed aviation hydraulic pump test bench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202511134821.9A CN120626477A (en) | 2025-08-14 | 2025-08-14 | A high-pressure and high-speed aviation hydraulic pump test bench |
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| CN120626477A true CN120626477A (en) | 2025-09-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202511134821.9A Pending CN120626477A (en) | 2025-08-14 | 2025-08-14 | A high-pressure and high-speed aviation hydraulic pump test bench |
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| CN212155113U (en) * | 2020-01-09 | 2020-12-15 | 上海辛金路流体技术有限公司 | Hydraulic pump performance test bench |
| CN112377487A (en) * | 2020-10-24 | 2021-02-19 | 济宁学院 | Hydraulic comprehensive test platform |
| CN119244510A (en) * | 2024-12-09 | 2025-01-03 | 浙江大学 | A digital hydraulic pump test bench and a digital hydraulic pump control performance verification method |
-
2025
- 2025-08-14 CN CN202511134821.9A patent/CN120626477A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202301255U (en) * | 2011-11-01 | 2012-07-04 | 浙江大学 | High-water-base two-position four-way electro-hydraulic reversing valve |
| DE102011118282A1 (en) * | 2011-11-11 | 2013-05-16 | Robert Bosch Gmbh | Hydraulic pump test stand for hydraulic pump, has electronic feedback controller, which adjusts angle of hydraulic motor as control variable considering circuit temperature of hydraulic fluid |
| CN102852784A (en) * | 2012-08-23 | 2013-01-02 | 上海亿力电器有限公司 | Plunger pump |
| CN104454790A (en) * | 2014-12-03 | 2015-03-25 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Electro-hydraulic servo valve performance test system |
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| CN206919916U (en) * | 2017-07-20 | 2018-01-23 | 广州汽车集团股份有限公司 | The rotation of gearbox built-in motor becomes demarcation test device and system |
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| CN119244510A (en) * | 2024-12-09 | 2025-01-03 | 浙江大学 | A digital hydraulic pump test bench and a digital hydraulic pump control performance verification method |
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