Aircraft engine oil scavenger pump all-working-condition comprehensive testing device and testing method

Abstract

The invention provides an aircraft engine oil scavenger pump all-working-condition comprehensive testing device and testing method, and belongs to the technical field of aviation hydraulic system testing. The testing device comprises an oil tank, a vacuum pressure composite simulation unit, an oil cleanliness control unit, a temperature control unit and a multi-station parallel testing unit. The oil tank is used for storing oil; the vacuum pressure composite simulation unit is used for simulating a high-altitude pressure environment of an inlet of the to-be-tested oil scavenger pump; the temperature control unit is used for adjusting the temperature of the oil liquid to a preset temperature; the cleanliness control unit is used for filtering oil liquid; and the multi-station parallel test unit is used for carrying out parallel test on the to-be-tested oil scavenger pump on the plurality of stations. According to the device, dynamic pressure adjustment is achieved through the vacuum pressure composite simulation unit, the test efficiency is improved through the multi-station parallel test unit, extreme working conditions are accurately simulated through the temperature control unit and the cleanliness control unit, the test precision of an aero-engine oil scavenger pump can be effectively improved, the test period is shortened, and the requirement of the aviation-grade cleanliness standard is met.

Description

Technical Field

[0001] This invention belongs to the field of aviation hydraulic system testing technology, specifically relating to a comprehensive testing device and method for the full operating conditions of an aircraft engine return oil pump. Background Technology

[0002] The aircraft engine return oil pump is a core component of the lubrication system, responsible for drawing lubricating oil back to the oil tank after it has circulated in the engine bearings and gearbox, ensuring a continuous supply of lubricating oil and proper thermal management. Its design directly affects the engine's reliability, cooling efficiency, and lifespan.

[0003] The aircraft engine return oil pump tester is a specialized device used to test and verify the performance of engine return oil pumps, and is a core component of aero-engine lubrication system testing equipment. Its core function is to simulate real-world engine operating conditions, ensuring the return oil pump operates reliably under various conditions to meet airworthiness standards and design requirements.

[0004] The existing aircraft engine return oil pump tester has the following defects:

[0005] 1. Traditional equipment relies on mechanical pressure regulating valves, which are insufficient for simulating high-altitude pressure. For example, changes in helicopter flight altitude (0-6000m) cause fluctuations in the vacuum pressure or absolute pressure at the return oil pump inlet, and existing equipment cannot accurately simulate dynamic pressure changes.

[0006] 2. Poor adaptability to extreme temperature ranges (-40℃ low temperature cold start, 150℃ high temperature working conditions), insufficient temperature control accuracy of the tester (5℃), resulting in distortion of oil viscosity simulation;

[0007] 3. The testing cycle of single-station equipment is long (24 hours / time), which cannot meet the requirements for synchronous disassembly and assembly testing of dual pumps;

[0008] 4. Oil cleanliness does not meet the standard: The traditional three-stage filtration system only reaches NAS1638 Class 8, which cannot meet the aviation-grade GJB420A-7 standard.

[0009] In conclusion, a testing device capable of overcoming at least one of the above defects is urgently needed. Summary of the Invention

[0010] The purpose of this invention is to solve the problems existing in the prior art and provide a comprehensive testing device and method for the full operating conditions of an aircraft engine oil return pump, so as to solve the problems of low testing efficiency, poor accuracy and incomplete operating condition coverage of the existing testing devices.

[0011] This invention is achieved through the following technical solution:

[0012] In a first aspect, the present invention provides a comprehensive testing device for the full operating conditions of an aircraft engine return oil pump. The testing device includes: an oil tank, a vacuum pressure composite simulation unit, an oil cleanliness control unit, a temperature control unit, and a multi-station parallel testing unit; the vacuum pressure composite simulation unit, the oil cleanliness control unit, the temperature control unit, and the multi-station parallel testing unit are all connected to the oil tank.

[0013] The oil tank is used to store oil.

[0014] The vacuum pressure composite simulation unit is used to simulate the high-altitude pressure environment at the inlet of the oil return pump under test, and dynamically adjust the output pressure of the oil within a preset pressure range.

[0015] The temperature control unit is used to adjust the temperature of the oil to a preset temperature;

[0016] The cleanliness control unit is used to filter the oil.

[0017] The multi-station parallel testing unit is used to perform parallel testing on the return oil pumps under test at multiple stations.

[0018] A further improvement of the present invention is that:

[0019] The vacuum pressure composite simulation unit includes a rotary vane vacuum pump, a proportional control valve, a PID controller, and a pressure waveform generator. The PID controller is electrically connected to the rotary vane vacuum pump, the proportional control valve, and the pressure waveform generator, respectively.

[0020] A further improvement of the present invention is that:

[0021] The multi-station parallel testing unit includes multiple break-in stations and one performance station. Each station is equipped with a quick-change connector and a hydraulic self-locking fixture, which includes a hydraulically driven wedge block.

[0022] A further improvement of the present invention is that:

[0023] The performance workstation unit includes a gear flow meter, which is used to monitor flow pulsation in real time.

[0024] A further improvement of the present invention is that:

[0025] The oil cleanliness control unit includes a three-stage tubular filter and a magnetic adsorber, which are connected in parallel.

[0026] A further improvement of the present invention is that:

[0027] The three-stage tubular filter includes tubular filters with diameters of 10μm, 5μm, and 3μm connected in series.

[0028] A further improvement of the present invention is that:

[0029] The temperature control unit includes a heating module and a cooling module.

[0030] A further improvement of the present invention is that:

[0031] The testing device also includes a control unit, which includes an industrial computer and a programmable logic controller (PLC). The industrial computer and the PLC are communicatively connected, and the PLC is electrically connected to the vacuum pressure composite simulation unit, the multi-station parallel testing unit, the oil cleanliness control unit, and the temperature control unit, respectively.

[0032] A second aspect of the present invention provides a comprehensive testing method for an aircraft engine return oil pump under all operating conditions, applied to the comprehensive testing device for an aircraft engine return oil pump under all operating conditions as described in any one of the first aspects above, the testing method comprising:

[0033] The high-altitude pressure environment at the inlet of the oil return pump under test was simulated using a vacuum pressure composite simulation unit.

[0034] The oil temperature is adjusted to the preset temperature by the temperature control unit;

[0035] The oil is filtered by a cleanliness control unit;

[0036] The multi-station parallel test unit starts the return oil pumps under test at multiple stations and performs parallel tests on the return oil pumps under test at multiple stations.

[0037] Collect flow rate and / or pressure information of the oil return pump to be tested at each workstation;

[0038] The test results of the return oil pump under test are generated based on the flow information and / or the pressure information.

[0039] A further improvement of the present invention is that:

[0040] The test results of the return oil pump under test include the performance test results and the break-in operation test results of the return oil pump.

[0041] Compared with the prior art, the beneficial effects of the present invention are as follows: The present invention provides a comprehensive testing device and method for the full-condition testing of an aircraft engine return oil pump, which realizes dynamic pressure regulation through a vacuum pressure composite simulation unit, improves testing efficiency through a multi-station parallel testing unit, and accurately simulates extreme operating conditions by combining a temperature control unit and a cleanliness control unit. It has the advantages of improving the testing accuracy of the aircraft engine return oil pump, shortening the testing cycle, and meeting the aviation-grade cleanliness standards. Attached Figure Description

[0042] The above and other objects, features, and advantages of the present invention will become more apparent from the more detailed description of the embodiments of the invention in conjunction with the accompanying drawings. The drawings are provided to further illustrate the embodiments of the invention and form part of the specification. They are used together with the embodiments of the invention to explain the invention and do not constitute a limitation thereof.

[0043] Figure 1 This is a schematic diagram of the structure of an aircraft engine return oil pump full-condition integrated test device according to an embodiment of the present invention;

[0044] Figure 2 This is a schematic diagram of the principle and connection relationship of an aircraft engine return oil pump full-condition integrated test device according to an embodiment of the present invention;

[0045] Figure 3 This is a schematic diagram of the principle and connection relationship of the aircraft engine return oil pump full-condition integrated test device according to another embodiment of the present invention;

[0046] Figure 4 This is a flowchart illustrating a comprehensive testing method for the full operating conditions of an aircraft engine return oil pump according to an embodiment of the present invention. Detailed Implementation

[0047] To make the objectives, technical solutions, and advantages of the present invention more apparent, exemplary embodiments according to the present invention will be described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are merely a part of the embodiments of the present invention, and not all of the embodiments of the present invention. It should be understood that the present invention is not limited to the exemplary embodiments described herein. Based on the embodiments of the present invention described herein, all other embodiments obtained by those skilled in the art without inventive effort should fall within the protection scope of the present invention.

[0048] To address the problems of low testing efficiency, poor accuracy, and incomplete operating condition coverage in existing comprehensive testing devices for aircraft engine return oil pumps, this invention proposes a comprehensive testing device and method for aircraft engine return oil pumps under all operating conditions. This method can improve testing efficiency and accuracy, and meet the testing requirements under all operating conditions. The invention will now be described in further detail with reference to the accompanying drawings.

[0049] First refer to Figure 1This invention describes a comprehensive testing device for the full operating conditions of an aircraft engine return oil pump, based on some embodiments of the present invention.

[0050] like Figure 1 As shown, the comprehensive testing device for the full operating conditions of the aircraft engine return oil pump includes: an oil tank 10, a vacuum pressure composite simulation unit 20, an oil cleanliness control unit 30, a temperature control unit 40, and a multi-station parallel testing unit 50; the vacuum pressure composite simulation unit 20, the oil cleanliness control unit 30, the temperature control unit 40, and the multi-station parallel testing unit 50 are all connected to the oil tank 10.

[0051] Oil tank 10 is used to store oil. Specifically, oil tank 10 may include a break-in oil tank 11 and a performance oil tank 12. The effective volume of the break-in oil tank is not less than 200L, and the effective volume of the performance oil tank is not less than 250L.

[0052] The vacuum pressure composite simulation unit 20 is used to simulate the high-altitude pressure environment at the inlet of the oil return pump under test, and dynamically adjusts the output pressure of the oil within a preset pressure range.

[0053] The cleanliness control unit 30 is used to filter the oil.

[0054] Temperature control unit 40 is used to adjust the temperature of the oil to a preset temperature.

[0055] The multi-station parallel testing unit 50 is used to perform parallel testing on multiple return oil pumps under test at multiple stations. Specifically, the multi-station parallel testing unit 50 includes at least one break-in test station and at least one performance test station, the specific number of which can be set according to testing requirements. For example, the multi-station parallel testing unit 50 may include a break-in test station 1, a break-in test station 2, and a performance test station 53, thereby enabling simultaneous break-in operation testing of two return oil pumps and performance testing of one return oil pump. Performance testing includes, but is not limited to, ground performance testing and high-altitude performance testing.

[0056] The vacuum pressure composite simulation unit refers to a pressure generation system that combines a vacuum pump and a pressure regulating device to form a closed-loop control. Specifically, it can use a rotary vane vacuum pump and a proportional pressure valve working together, with a PID controller adjusting the output pressure waveform in real time to accurately simulate dynamic pressure changes in high-altitude environments. The temperature control unit is a device with bidirectional temperature regulation capabilities to ensure that the oil viscosity meets the requirements of different operating conditions. The oil cleanliness control unit is a multi-stage filtration system, which can specifically use a combination of series-connected tubular filters and magnetic adsorbers to progressively intercept particulate matter and metal debris, ensuring that the oil cleanliness meets aviation standards.

[0057] The testing device of this invention is used to simulate the real working conditions of an engine, and to realize the break-in operation test, ground performance test, high-altitude performance test, flow characteristic analysis and dynamic parameter acquisition of the return oil pump and lubricating oil accessories. It is applicable to helicopters, such as Z-8 / Z-20, SA365N and other models, as well as the testing and inspection of fixed-wing aircraft engines. It is suitable for maintenance and support of army aviation, shipborne and fixed-wing aircraft.

[0058] The full operating conditions of the aircraft engine return oil pump in this invention include:

[0059] Pressure range: 15.47 kPa (high altitude) - 1 MPa (ground level);

[0060] Flow range: 2L / min (idle speed) - 150L / min (maximum power), covering the performance limits of return oil pumps in models such as Z-8 and Z-20;

[0061] Speed ​​range: 0-10000 r / min (torque accuracy ±0.1 Nm).

[0062] In this invention, the testing device further includes a control unit, which may include an industrial computer and a programmable logic controller (PLC). The industrial computer and the PLC are communicatively connected, and the PLC is electrically connected to the vacuum pressure composite simulation unit, the multi-station parallel testing unit, the oil cleanliness control unit, and the temperature control unit, respectively.

[0063] The industrial control computer acts as the host computer, while the PLC serves as the main control device (i.e., the slave computer). Based on the test requirements, it controls the equipment's actions and status adjustments through the control program, collects relevant test data during the test, records, processes, and saves the data, and finally generates a test report.

[0064] Product testing can be conducted in both automatic and manual modes. In manual control, the start / stop of the servo motor, speed control, and adjustment of the product outlet pressure can be accomplished via panel buttons or knobs. In automatic control, the test process can be automated by setting parameters.

[0065] During system operation, all test sensor signals are transmitted to the industrial computer for processing, display and storage via the PLC data acquisition module. After inputting commands on the panel, the PLC controls the speed of the servo motor and controls the system pressure through the PLC analog output module. For example, after receiving commands, the PLC controls the pump start and stop, the solenoid valve on and off, etc. through the output module.

[0066] Priority is that the industrial computer can also automatically generate test curves, perform fault diagnosis, and trace historical data.

[0067] This invention provides a comprehensive testing device for the return oil pump of an engine under all operating conditions. It achieves independent testing at multiple stations through a multi-station parallel testing unit, improving testing efficiency; it accurately simulates dynamic pressure changes through a vacuum pressure composite simulation unit, meeting the testing requirements of all operating conditions; it achieves high-precision temperature control through a temperature control unit; and it performs multi-stage filtration through an oil cleanliness control unit, thereby improving testing accuracy. Ultimately, it solves the problems of low efficiency, poor accuracy, and incomplete operating condition coverage of existing equipment.

[0068] It should be noted that Figure 1 The components and structure of the aircraft engine return oil pump full-condition integrated test device shown are merely exemplary and not limiting. The test device may also have other components and structures as needed.

[0069] In some embodiments of the present invention, the vacuum pressure composite simulation unit includes a rotary vane vacuum pump, a proportional regulating valve, a PID controller, and a pressure waveform generator. The PID controller is electrically connected to the rotary vane vacuum pump, the proportional regulating valve, and the pressure waveform generator, respectively, and supports dynamic adjustment of absolute pressure from 15.47 to 101.3 kPa.

[0070] Specifically, the pressure waveform generator can load the dynamic pressure curve corresponding to a typical helicopter flight profile (climb rate 5m / s, dive angle 30°). By simulating the physical process of atmospheric pressure changing with altitude and attitude, it determines the flight environment pressure load that should be provided to the equipment under test. A rotary vane vacuum pump is linked to a proportional control valve. The rotary vane vacuum pump simulates the absolute pressure at high altitude through a PID controller, and the pressure is controlled in a closed loop by switching via the proportional control valve. This allows for pressure switching from 15.47kPa to 101.3kPa within 0.5 seconds, with a dynamic response frequency of 2Hz.

[0071] The proportional control valve receives analog signals from the PID controller and controls the gas inflow / outflow by linearly adjusting the valve opening, thereby achieving the following functions: introducing outside atmosphere when pressurizing (from 15.47kPa to 101.3kPa), and cooperating with the vacuum pump to adjust the exhaust volume and control the pressure drop rate when depressurizing.

[0072] In this embodiment, by linking the vacuum pump with the proportional valve, the transient pressure changes at an altitude of 0-6000m can be accurately reproduced, with a pressure transient switching accuracy of ±0.5%, which is better than the requirements of military standard GJB6389-2008. Moreover, the control accuracy is significantly improved compared to the pressure control error (±5%) of existing testing devices.

[0073] In some embodiments of the present invention, the multi-station parallel testing unit includes multiple break-in station units and a performance station unit. Each station unit is equipped with a quick-change connector and a hydraulic self-locking fixture, wherein the hydraulic self-locking fixture includes a hydraulically driven wedge block.

[0074] The break-in station unit refers to an independent module used to perform break-in operation tests on the return oil pump. It can be implemented using parallel oil circuits and independent drive interfaces, with each station having independent pressure supply and data acquisition channels. The performance station unit refers to a module used to perform performance parameter tests, which can be implemented using a high-precision sensor array and closed-loop control oil circuits.

[0075] The wedge block utilizes the principle of inclined planes, and is hydraulically driven to wedge itself between the workpiece and the fixture base, converting the hydraulic thrust into a clamping force perpendicular to the inclined plane. When the hydraulic system is depressurized, the wedge block remains stationary due to friction, achieving "self-locking".

[0076] For example, the quick-change coupling can use the SAE J518 coupling to achieve quick clamping of the pump body in 3 minutes.

[0077] In this embodiment, each workstation is equipped with an independent hydraulic circuit, and each workstation's hydraulic circuit is independently controlled by a solenoid ball valve. This allows for simultaneous testing at multiple break-in workstations and parallel verification of single-pump performance. When a dual break-in workstation unit is configured, break-in operation tests on two return oil pumps and ground performance tests on one return oil pump can be performed simultaneously, reducing the test cycle from 24 hours to 8 hours and increasing test efficiency by 300%.

[0078] The performance station includes a gear flow meter, which is used to monitor flow pulsation in real time.

[0079] Through the above technical solutions, this application achieves simultaneous testing and rapid replacement of multiple return oil pumps, shortening the single testing cycle to less than one-third of the original equipment, thus meeting the capacity requirements of the aero-engine maintenance workshop for parallel testing of dual pumps. The closed-loop displacement control of the hydraulic self-locking clamp effectively avoids pump body deformation caused by overload clamping, ensuring the safety of the testing process. The application of quick-change couplings significantly reduces oil loss during station switching, making the testing device more suitable for high-frequency batch testing scenarios.

[0080] In some embodiments of the present invention, the temperature control unit includes a heating module and a cooling module.

[0081] Specifically, the heating module uses a semiconductor heater that utilizes the Peltier effect. When current passes through a thermocouple made of semiconductor material (such as bismuth telluride alloy), one end absorbs heat (cooling) and the other end releases heat (heating). The heating / cooling mode can be switched by changing the direction of the current.

[0082] The refrigeration module adopts a cascade compressor refrigeration unit, which works in series through two or more independent refrigeration cycles (high temperature stage + low temperature stage). The heat released when the high temperature stage refrigerant (such as R404A) condenses is absorbed by the low temperature stage refrigerant (such as R23), thereby achieving ultra-low temperature refrigeration from -40℃ to -150℃, with oil temperature uniformity ≤±1℃. Compared with the existing test equipment (temperature uniformity 5%), the temperature control accuracy is greatly improved.

[0083] In some embodiments of the present invention, the testing device further includes a servo drive system connected to the test piece—the return oil pump. The return oil pump is connected to a drive servo motor and, according to hydraulic principles, is connected to the corresponding oil pump interface, enabling both automatic and manual electrical control. The parameters of the test piece can be adjusted and set according to user requirements.

[0084] Specifically, the servo drive system can use Siemens 1PH series motors, which support stepless speed regulation from 0 to 10000 r / min and torque accuracy of ±0.1 Nm.

[0085] In this embodiment, a data acquisition system is also configured to collect parameters such as flow rate, pressure, and temperature in real time through a gear flow meter and a pressure sensor, with a sampling frequency of 200ms. The collected data is sent to the PLC and the industrial control computer, and the industrial control computer outputs corresponding control commands based on the real-time status of the system.

[0086] During testing, the performance oil tank (V=250L) and the break-in oil tank (V=200L) were first connected to their respective three-stage tubular filters via rigid pipes. A gear flow meter of the data acquisition system was installed at the performance oil tank, and pressure sensors were installed at both the performance oil tank and the break-in oil tank.

[0087] This invention addresses the full-condition performance verification requirements of the return oil pump in the hydraulic system of an aircraft engine. It provides a comprehensive testing device for the engine return oil pump, which includes functions such as high-altitude pressure dynamic simulation, multi-station parallel testing, high-precision temperature control, and intelligent data analysis. It can meet the testing requirements of helicopters under special operating conditions with flight altitude changes from 0 to 6000m and extreme temperature ranges from -40℃ to 150℃.

[0088] Next, refer to Figure 2 This invention describes an embodiment of an aircraft engine return oil pump full-condition integrated testing device.

[0089] Figure 2The diagram shows the components used in the comprehensive testing device for the full operating conditions of the aircraft engine return oil pump for performing the run-in test of the return oil pump. Specifically, these components include: first oil tank 1a, visual level gauge 2a, circulating motor pump group 3a, three-stage filter assembly 4a, air cooler 5, servo motors 6a and 6b, diaphragm high-speed couplings 7a and 7b, quick-release tooling for oil inlet 8a and 8b, quick-release tooling for oil outlet 9a and 9b, speed sensors 11a and 11b, pressure sensors 12a, 12b, 12c and 12d, tubular filter 13a, temperature sensor 14a, level relay 15a, level transmitter 16a, proportional control valves 17a and 17b, ball valves 18a, 18b and 18c, oil receiving tank with oil receiving pan 19, solenoid valves 20a, 20b and 20c, pneumatic pressure reducing valve 21a, and pneumatic triplet 23.

[0090] The first oil tank 1a serves as the break-in oil tank, used to store oil. The first oil tank 1a is equipped with a visual level gauge 2a, installed on the side wall of the first oil tank 1a in an easily observable location, for real-time display of the oil level. The first oil tank 1a also includes a temperature sensor 14a, a level relay 15a, a ball valve 18c for manual venting, and ball valves for each oil supply and return port (not shown in the figure). The temperature sensor 14a, level relay 15a, and ball valve 18c are mounted on the cover plate of the first oil tank 1a. The first oil tank is made of 304 stainless steel, and the exterior of the performance oil tank is equipped with an insulation layer.

[0091] A cleanliness control unit, consisting of a circulating motor pump assembly 3a and a three-stage filtration assembly 4a, is used to filter the oil. The three-stage filtration assembly 4a includes a three-stage tubular filter and a magnetic adsorber, which are connected in parallel. Specifically, the three-stage tubular filter comprises tubular filters with diameters of 10μm, 5μm, and 3μm connected in series, thereby achieving an output oil particle size ≤5μm and a particle rejection rate >99.8%. Existing testing equipment can only achieve NAS1638 Class 8 oil cleanliness, while the oil cleanliness control unit in this embodiment can significantly improve the oil cleanliness to NAS1638 Class 6.

[0092] After the system is powered on, the circulating motor pump unit 3a is started by manually pressing the button to filter the oil in the first oil tank 1a. The filtration adopts a three-stage filtration method, with tubular filters with precision of 10μm, 5μm and 3μm connected in series at the outlet of the circulating motor pump unit 3a. Through circulation by the circulating pump, the oil can be purified to the GJB420A-7 standard within 60 minutes.

[0093] Figure 2The system includes two parallel testing stations for parallel testing of return oil pumps 10a and 10b at the two stations. Each testing station is equipped with servo motors 6a and 6b, diaphragm-type high-speed couplings 7a and 7b, inlet quick-connect fixtures 8a and 8b, and outlet quick-connect fixtures 9a and 9b. The inlet and outlet quick-connect fixtures 8a and 8b are equipped with quick-change couplings and hydraulic self-locking clamps, which include hydraulically driven wedge blocks.

[0094] In this embodiment, the oil inlets of return oil pumps 10a and 10b are equipped with filters 13a with a filtration accuracy of 25μm to ensure that the cleanliness of the oil entering return oil pumps 10a and 10b meets the basic requirements.

[0095] In this embodiment, the bottom of the two parallel test stations has an oil receiving tank 19a containing a mesh oil receiving tray, and a liquid level transmitter 16a is installed in the oil receiving tank 19a. The liquid level transmitter is used to detect and monitor the position of the liquid in the oil receiving tank 19a, and generates a trigger signal based on the liquid level change. When the tested pump is replaced, the controller controls the solenoid valve 20a to close and the solenoid valve 20b to open based on the trigger signal, so as to pump the scattered oil back to the first oil tank 1a.

[0096] Figure 2 The air cooler 5 in the system serves as the temperature control unit for the first oil tank 1a, using air as the cooling medium to remove heat and control the oil temperature. During operation, the servo motors 6a and 6b drive the return oil pumps 10a and 10b, generating heat that causes the system oil temperature to rise. Since the working oil circuit must be an independent loop, the air cooler 5 is connected in series in the circulating filter device to cool the oil. Feedback from the temperature sensor 14a controls the start and stop of the air cooler, ensuring the oil temperature remains within a reasonable range and meeting the temperature requirements for the break-in of the return oil pumps 10a and 10b.

[0097] Figure 2The pneumatic pressure reducing valve 21a and pneumatic triplet 23 form a vacuum pressure composite simulation unit, used to dynamically adjust the output pressure of the oil within a preset pressure range. The pressure sensor 12d on the first oil tank 1a detects and controls the inlet pressure requirements of the return oil pumps 10a and 10b in real time. The pneumatic pressure reducing valve 21a reduces the pressure of compressed air to the test pressure value. The pneumatic triplet consists of an air filter, a pressure reducing valve, and an oil mist lubricator, mainly used to purify and regulate the air source. The air filter filters impurities and moisture from the compressed air, ensuring the cleanliness of the air source and preventing contamination of pneumatic equipment. The filter effectively removes moisture and particles from the air, protecting the normal operation of downstream equipment. The pressure reducing valve regulates the pressure in the pneumatic system, reducing high-pressure gas to the required working pressure. The pressure reducing valve stabilizes the output pressure, preventing damage to equipment due to air source pressure fluctuations. The oil mist lubricator atomizes lubricating oil and mixes it into the compressed air to lubricate pneumatic components, reduce wear, and extend the service life of the equipment. The oil mist lubricator is particularly suitable for components where direct oiling is inconvenient.

[0098] In this embodiment, speed sensors 11a and 11b are installed on the bell-shaped housing between the motor and the oil pump. Pressure sensors 12c and 12b are installed at the oil inlets of return oil pumps 10a and 10b, respectively. Proportional regulating valves 17a and 17b and sampling ball valves 18a and 18b are also included. Proportional regulating valves 17a and 17b are used to regulate the outlet pressure of the return oil pumps, and sampling ball valves 18a and 18b are used to provide an oil sampling interface to detect its cleanliness.

[0099] Next, refer to Figure 3 This invention describes a comprehensive testing device for the full operating conditions of an aircraft engine return oil pump, according to another embodiment of the present invention.

[0100] like Figure 3 The diagram shows the components used to perform performance tests on the return oil pump in the comprehensive testing device for the full operating conditions of the aircraft engine return oil pump. Specifically, these components include: a second oil tank 1b, a visual level gauge 2b, a circulating motor pump assembly 3b, a three-stage filter assembly 4b, a servo motor 6c, a diaphragm high-speed coupling 7c, an inlet quick-release tooling 8c, an outlet quick-release tooling 9c, a speed sensor 11c, pressure sensors 12e, 12f, and 12g, a tubular filter 13b, temperature sensors 14b and 14c, a level relay 15b, a level transmitter 16b, a proportional control valve 17c, ball valves 18d and 18e, an oil receiving tank 19b, solenoid valves 20d, 20e, and 20f, a pneumatic pressure reducing valve 21b, a vacuum pump 22, a pneumatic triplet 23, an oil temperature controller 24, and a gear flow meter 25.

[0101] In this embodiment, the second oil tank 1b is a performance oil tank, which is equipped with a visual level gauge 2b, a temperature sensor 14b, a level relay 15b, a regulating valve 18e, and a pressure sensor 12g.

[0102] In this embodiment, the vacuum pump 22 can be a rotary vane vacuum pump. The vacuum requirement for the second oil tank 1b is met by switching the solenoid valve 20f, satisfying the inlet pressure requirements of each stage of the pump during the high-altitude test. The pressure sensor 12g on the second oil tank 1b detects and controls the inlet pressure requirements of the return oil pump 10c in real time. Furthermore, an oil mist separator (not shown in the figure) is installed at the outlet of the vacuum pump 22 to separate oil from the air, preventing secondary environmental pollution.

[0103] This embodiment provides a performance testing station for testing the performance of the return oil pump 10c. Specific components include: servo motor 6c, diaphragm high-speed coupling 7c, inlet quick-release tooling 8c, outlet quick-release tooling 9c, speed sensor 11c, pressure sensors 12f and 12e, tubular filter 13b, temperature sensor 14c, proportional control valve 17c, and ball valve 18d.

[0104] It should be noted that, unlike the break-in station unit, the performance station unit also includes a temperature sensor 14c located at the inlet of the return oil pump 10c and a gear flow meter 25 located at the outlet of the return oil pump 10c. The gear flow meter 25 is used to monitor flow pulsation in real time.

[0105] In this embodiment, the bottom of the performance testing station has an oil receiving tank 19b containing a mesh oil receiving tray, a liquid level transmitter 16b is installed in the oil receiving tank 19b, and a solenoid valve 20e is connected to the outlet of the oil receiving tank 19b.

[0106] In this embodiment, the solenoid valve 20f, the pneumatic pressure reducing valve 21b, the vacuum pump 22, and the pneumatic triplet 23 form a vacuum pressure composite simulation unit, which is used to simulate the high-altitude pressure environment at the inlet of the oil return pump under test.

[0107] The cleanliness control unit, consisting of the circulating motor pump set 3b and the three-stage filter assembly 4b, is used to filter the oil.

[0108] The functions and connections of the above components are as follows: Figure 2 The components used to perform the run-in test of the return oil pump in the comprehensive test apparatus for the aircraft engine return oil pump shown are the same, and will not be described in detail here. The following only describes the oil temperature control unit 24.

[0109] Figure 3The oil temperature controller 24 serves as the temperature control unit for the second oil tank 1b, adjusting the oil temperature to the preset temperature. The oil temperature controller 24 employs an integrated heating and cooling mode, achieving both heating and cooling of the oil in the second oil tank 1b, and operates independently without interference from the main pipeline. The heating system uses semiconductor heating, achieving automatic control and temperature adjustment through a temperature sensor. The final temperature value is based on the measurement value of the temperature sensor 14c at the inlet of the return oil pump 10c. The temperature sensor 14b on the second oil tank 1b and the temperature sensor built into the heating system itself are only used as references and are not used for data acquisition and recording.

[0110] Next, refer to Figure 4 This invention describes a test method for a hydraulic system according to some embodiments of the present invention.

[0111] like Figure 4 As shown, in some embodiments of the present invention, the testing method for the hydraulic system can be applied to the above-mentioned comprehensive testing device for the full operating conditions of the aircraft engine return oil pump. The testing method includes the following steps S410-S460.

[0112] Step S410: Simulate the high-altitude pressure environment at the inlet of the oil return pump under test using a vacuum pressure composite simulation unit;

[0113] Step S420: Adjust the oil temperature to the preset temperature using the temperature control unit;

[0114] Step S430: Filter the oil through the cleanliness control unit;

[0115] Step S440: Start the return oil pumps under test at multiple stations through the multi-station parallel test unit to perform parallel testing on the return oil pumps under test at multiple stations.

[0116] Step S450: Collect the flow rate and / or pressure information of the oil return pump to be tested at each workstation;

[0117] Step S460: Generate the test results of the oil return pump under test based on the flow information and / or the pressure information.

[0118] Specifically, the test results of the return oil pump under test include the performance test results of the return oil pump and the break-in operation test results of the return oil pump.

[0119] Specifically, during the testing process, a dynamic pressure signal is first generated by a vacuum pressure composite simulation unit. This signal is transmitted to a PID controller, which drives a rotary vane vacuum pump and a proportional pressure valve to work together, causing the oil output pressure to fluctuate continuously within a set range, simulating the pressure environment caused by changes in helicopter flight altitude. The temperature control unit heats or cools the oil according to preset temperature parameters, ensuring the oil viscosity matches real-world operating conditions. The cleanliness control unit performs multi-stage purification of the oil using a three-stage filter and a magnetic adsorber, ensuring the oil particle size meets aviation standards. A multi-station parallel testing unit simultaneously secures multiple pumps under test using hydraulic self-locking clamps. Each station independently collects flow pulsation, vibration spectrum, and temperature data, which are then synchronously transmitted to the control unit for comprehensive analysis.

[0120] The following describes the comprehensive testing method for the aircraft engine return oil pump under all operating conditions of the present invention, combining break-in and operation tests.

[0121] By connecting the oil return pump under test to the drive servo motor using specific tooling, and connecting the corresponding oil pump interface according to hydraulic principles, both automatic and manual electrical control can be achieved. The parameters of the oil return pump can be adjusted and set according to user requirements. Specifically, the parameters include speed, operating time, and oil pump inlet pressure.

[0122] During the test, the high-altitude pressure environment at the inlet of the return oil pump was simulated by a vacuum pressure composite simulation unit, the oil was filtered by a cleanliness control unit, and the outlet pressure of the oil pump was measured at the same time.

[0123] The test results of the break-in operation test of the return oil pump are based on the oil pump outlet pressure.

[0124] After the break-in test of the return oil pump is completed, ground performance tests and high-altitude performance tests are conducted. In the ground performance test, the oil temperature heating module in the temperature control unit is activated to ensure that the inlet oil temperature of the return oil pump is above 70℃. Under the condition that the oil suction pressure of the return oil pump reaches 0-0.03MPa, the following tests are conducted: the return oil pump is running at the first preset speed, and the flow rate and outlet pressure of the return oil pump are measured.

[0125] The high-altitude performance test of the return oil pump refers to the test of the return oil pump at the second preset speed, with the inlet oil temperature above 70℃ and the inlet absolute pressure (the vacuum pump achieves constant inlet pressure) at 24.5±1KPa. The flow rate of the oil pump is measured, and the actual output flow rate of the return oil pump is detected by adjusting different inlet absolute pressure values.

[0126] Finally, it should be noted that the above technical solution is only one embodiment of the present invention. For those skilled in the art, based on the application methods and principles disclosed in the present invention, it is easy to make various types of improvements or modifications, and not limited to the methods described in the above specific embodiments of the present invention. Therefore, the methods described above are only preferred and have no limiting significance.

Claims

1. A comprehensive testing device for the full operating conditions of an aircraft engine return oil pump, characterized in that: The testing device includes: an oil tank, a vacuum pressure composite simulation unit, an oil cleanliness control unit, a temperature control unit, and a multi-station parallel testing unit; the vacuum pressure composite simulation unit, the oil cleanliness control unit, the temperature control unit, and the multi-station parallel testing unit are all connected to the oil tank; The oil tank is used to store oil. The vacuum pressure composite simulation unit is used to simulate the high-altitude pressure environment at the inlet of the oil return pump under test, and dynamically adjust the output pressure of the oil within a preset pressure range. The temperature control unit is used to adjust the temperature of the oil to a preset temperature; The cleanliness control unit is used to filter the oil. The multi-station parallel testing unit is used to perform parallel testing on the return oil pumps under test at multiple stations.

2. The full-condition comprehensive testing device for the oil return pump of an aircraft engine according to claim 1, characterized in that: The vacuum pressure composite simulation unit includes a rotary vane vacuum pump, a proportional control valve, a PID controller, and a pressure waveform generator. The PID controller is electrically connected to the rotary vane vacuum pump, the proportional control valve, and the pressure waveform generator, respectively.

3. The comprehensive testing device for the full operating conditions of the aircraft engine return oil pump according to claim 1, characterized in that: The multi-station parallel testing unit includes multiple break-in stations and one performance station. Each station is equipped with a quick-change connector and a hydraulic self-locking fixture, which includes a hydraulically driven wedge block.

4. The comprehensive testing device for the full operating conditions of the aircraft engine return oil pump according to claim 3, characterized in that: The performance workstation unit includes a gear flow meter, which is used to monitor flow pulsation in real time.

5. The comprehensive testing device for the full operating conditions of the aircraft engine return oil pump according to claim 1, characterized in that: The oil cleanliness control unit includes a three-stage tubular filter and a magnetic adsorber, which are connected in parallel.

6. The comprehensive testing device for the full operating conditions of the aircraft engine return oil pump according to claim 5, characterized in that: The three-stage tubular filter includes tubular filters with diameters of 10μm, 5μm, and 3μm connected in series.

7. The comprehensive testing device for the full operating conditions of the aircraft engine return oil pump according to claim 1, characterized in that: The temperature control unit includes a heating module and a cooling module.

8. The comprehensive testing device for the full operating conditions of the aircraft engine return oil pump according to any one of claims 1 to 7, characterized in that: The testing device also includes a control unit, which includes an industrial computer and a programmable logic controller (PLC). The industrial computer and the PLC are communicatively connected, and the PLC is electrically connected to the vacuum pressure composite simulation unit, the multi-station parallel testing unit, the oil cleanliness control unit, and the temperature control unit, respectively.

9. A comprehensive testing method for an aircraft engine return oil pump under all operating conditions, applied to the comprehensive testing apparatus for an aircraft engine return oil pump under all operating conditions as described in any one of claims 1 to 8, characterized in that: The testing method includes: The high-altitude pressure environment at the inlet of the oil return pump under test was simulated using a vacuum pressure composite simulation unit. The oil temperature is adjusted to the preset temperature by the temperature control unit; The oil is filtered by a cleanliness control unit; The multi-station parallel test unit starts the return oil pumps under test at multiple stations and performs parallel tests on the return oil pumps under test at multiple stations. Collect flow rate and / or pressure information of the oil return pump to be tested at each workstation; The test results of the return oil pump under test are generated based on the flow information and / or the pressure information.

10. The comprehensive testing method for the aircraft engine return oil pump under all operating conditions according to claim 9, characterized in that: The test results of the return oil pump under test include the performance test results and the break-in operation test results of the return oil pump.

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