Oil pump testing equipment for turboprop aircraft engines

Abstract

This invention discloses an oil pump testing device for a turboprop aero-engine. During oil pump testing, the mid- and rear bearing oil pump, transmission box oil pump, and torque measuring pump share a single hydraulic system. The test parameters for different oil pumps are set through an electrical system, and then data acquisition, equipment action control, and safety interlock protection are performed separately. This device can meet the needs of break-in tests for three types of oil pumps, flow tests and sealing tests at different speeds and pressures, as well as high-altitude performance tests for the mid- and rear bearing oil pump. It achieves three tests in one machine, greatly improving the versatility of the oil pump testing device. Furthermore, it can perform tests on at least two oil pumps simultaneously, improving testing efficiency.

Description

Technical Field

[0001] This invention relates to the field of oil pump testing technology, and in particular, to an oil pump testing device for a turboprop aircraft engine. Background Technology

[0002] As the crown jewel of industry, aero-engines, due to their unique characteristics, require break-in and performance tests on every component or accessory before overall engine assembly to ensure that the overall engine's performance and technical parameters meet requirements. Oil pump testing is crucial in this regard. Turboprop aero-engines have oil pumps including the mid- and rear bearing oil pump, the transmission housing oil pump, and the torque pump. Each type of oil pump requires break-in testing, specifically flow rate and sealing tests at different speeds and pressures. Additionally, the mid- and rear bearing oil pump requires high-altitude performance testing. Currently, testing of these three types of oil pumps is done one pump at a time, requiring separate testing equipment for each pump. This results in poor equipment versatility and low testing efficiency. Furthermore, existing testing equipment uses ordinary motors with pulleys for speed increase to meet high-speed requirements, leading to poor speed control accuracy. Moreover, low-flow-rate tests rely on manual visual measurement using glass rotor float flowmeters, which introduces significant errors, resulting in poor accuracy and reliability of the test results. Summary of the Invention

[0003] This invention provides a test device for oil pumps of turboprop aero engines to solve the technical problems of poor versatility and low test efficiency of existing test devices.

[0004] According to one aspect of the present invention, a test device for an oil pump of a turboprop aircraft engine is provided, comprising an operating cabinet, a hydraulic system, an oil tank mounting bracket, and an oil pump mounting bracket. The operating cabinet is equipped with an electrical system for setting test parameters of different oil pumps, collecting data, controlling equipment actions, and providing safety interlock protection during the test. The oil tank mounting bracket is used to install the oil tank of the hydraulic system. The oil pump mounting bracket is used to install the mid- and rear bearing oil pump, the transmission box oil pump, and the torque measuring pump, as well as the drive motors and transmission mechanisms of each oil pump. During the oil pump test, the mid- and rear bearing oil pump, the transmission box oil pump, and the torque measuring pump share a set of hydraulic systems.

[0005] Furthermore, the hydraulic system includes a first oil circuit system, a second oil circuit system, a third oil circuit system, and a fourth oil circuit system. The first oil circuit system supplies oil to the intermediate and rear bearing oil pump, the second oil circuit system supplies oil to the transmission box oil pump, and the third oil circuit system supplies oil to the torque measuring pump. Each oil pump is connected to a variable frequency high-speed motor via a coupling. The intermediate and rear bearing oil pump and the torque measuring pump are connected to the motor via a coupling with a keyed hole at one end and an internal spline hole at the other end. The transmission box oil pump is connected to the motor via a coupling with a keyed hole at one end and external meshing teeth at the other end. The fourth oil circuit system provides lubricating oil for the gear transmission between the transmission box oil pump and the motor. The first and second oil circuit systems share a common oil tank, while the third and fourth oil circuit systems each have their own separate oil tank.

[0006] Furthermore, the first oil circuit system includes a vacuum high-level oil tank and a vacuum pumping system. The vacuum high-level oil tank is equipped with a first electric heater. The vacuum pumping system is connected to the vacuum high-level oil tank and is used to evacuate the vacuum high-level oil tank. The two oil inlets of the intermediate and rear bearing oil pump are each connected to the vacuum high-level oil tank through an oil inlet pipeline, and its oil outlet is connected to the vacuum high-level oil tank through two oil return pipelines. Each oil inlet pipeline is equipped with a first filter, a first electric regulating valve, a first turbine flow meter, and a first pressure sensor in sequence along the oil inlet direction. A second pressure sensor and a second filter are installed at the oil outlet of the intermediate and rear bearing oil pump. A second electric regulating valve is installed on the first oil return pipeline, and a third electric regulating valve and a second turbine flow meter are installed in sequence on the second oil return pipeline. The vacuum high-level oil tank is also connected to an external compressed air source. The pipeline connecting the two is equipped with a first ball valve, a compressed air filter pressure reducing valve, and a second ball valve in sequence along the air inlet direction.

[0007] Furthermore, the vacuum system includes a vacuum pump, a fourth electric regulating valve, an oil-gas separator, and a third ball valve. The third ball valve is installed on the pipeline connecting the oil-gas separator and the high-level vacuum oil tank. The vacuum pump is connected to the oil-gas separator, and the fourth electric regulating valve is installed on the inlet pipeline of the vacuum pump.

[0008] Furthermore, the second oil circuit system includes a third filter, a fifth electric regulating valve, a third pressure sensor, a fourth filter, a sixth electric regulating valve, and a third turbine flow meter. The third filter and the fifth electric regulating valve are sequentially arranged on the oil inlet pipe of the transmission box oil pump along the oil inlet direction, and the third pressure sensor, the fourth filter, the sixth electric regulating valve, and the third turbine flow meter are sequentially arranged on the oil return pipe along the oil return direction.

[0009] Furthermore, the fourth oil circuit system includes a lubricating oil tank, a lubricating oil pump, a fourth ball valve, and a fifth ball valve. The inlet of the lubricating oil pump is connected to the lubricating oil tank. The fourth ball valve is located on the bypass oil circuit of the lubricating oil pump, and the fifth ball valve is located on the main oil circuit of the lubricating oil pump. The lubricating oil pump provides lubricating oil to the gear transmission between the transmission box oil pump and the motor through the main oil circuit. The main oil circuit of the lubricating oil pump is also connected to the vacuum high-level oil tank, and a sixth ball valve is installed on the pipeline connecting the two.

[0010] Furthermore, it also includes an oil collection box for collecting residual oil during the test, the lubricating oil tank being connected to the oil collection box.

[0011] Furthermore, the third oil circuit system includes a low-level oil tank and a circulating pump. The inlet of the circulating pump is connected to the low-level oil tank, and a fifth filter and a seventh ball valve are sequentially installed on the connecting pipeline. A second electric heater is installed inside the low-level oil tank. A sixth filter, an eighth ball valve, a seventh electric regulating valve, and a fourth pressure sensor are sequentially installed on the main oil supply line connecting the circulating pump and the torque measuring pump. The main oil supply line is also connected to the low-level oil tank through two bypass oil lines. A first overflow valve is installed on the first bypass oil line, and a fifth pressure sensor, an eighth electric regulating valve, and a seventh filter are installed on the second bypass oil line. The main return oil line of the torque measuring pump is... The main return oil circuit is equipped with a sixth pressure sensor and a fourth turbine flow meter. After the fourth turbine flow meter, the main return oil circuit splits into three branches. Two of these branches merge and connect to the low-level oil tank, while the other branch connects to the pressure reducing valve. The two merging branches are equipped with a ninth and a tenth electric regulating valve, respectively. An eighth filter is also installed between the two merging branches and the low-level oil tank. The main return oil circuit is also connected to the low-level oil tank via a bypass oil circuit. A second overflow valve is installed on the bypass oil circuit. An eleventh electric regulating valve and a seventh pressure sensor are sequentially installed on the branch connected to the pressure reducing valve. An eighth pressure sensor is installed on the output oil circuit of the pressure reducing valve.

[0012] Furthermore, the main oil supply line of the circulating pump is also connected to the oil replenishment port of the high-level vacuum oil tank. The pipeline connecting the two is equipped with a ninth filter and a ninth ball valve in sequence. The oil outlet of the high-level vacuum oil tank is also connected to the low-level oil tank. The pipeline connecting the two is equipped with a tenth ball valve, thereby realizing oil-liquid complementarity between the two oil tanks.

[0013] Furthermore, the third oil circuit system also includes a cooler for cooling the oil. The oil inlet and outlet pipes of the cooler are both connected to the main oil supply circuit. An eleventh ball valve is installed on the oil inlet pipe, a twelfth ball valve is installed on the oil outlet pipe, and a thirteenth ball valve is installed on the water inlet pipe of the cooler.

[0014] The present invention has the following effects:

[0015] The oil pump testing equipment for turboprop aero-engines of this invention uses a single hydraulic system for the mid- and rear bearing oil pump, transmission box oil pump, and torque measuring pump during oil pump testing. Different test parameters for each oil pump are set via an electrical system, and data acquisition, equipment motion control, and safety interlock protection are then performed separately. This system can meet the needs of break-in tests for three types of oil pumps, flow rate tests and sealing tests at different speeds and pressures, as well as high-altitude performance tests for the mid- and rear bearing oil pump. It achieves three tests in one machine, greatly improving the versatility of the oil pump testing equipment. Furthermore, it can perform tests on at least two oil pumps simultaneously, increasing testing efficiency.

[0016] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0017] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0018] Figure 1 This is a schematic diagram of the external structure of the oil pump test equipment for a turboprop aero-engine according to a preferred embodiment of the present invention.

[0019] Figure 2 This is a top view schematic diagram of the external structure of the oil pump test equipment for a turboprop aero-engine according to a preferred embodiment of the present invention.

[0020] Figure 3 This is a schematic diagram of the hydraulic principle of a hydraulic system according to a preferred embodiment of the present invention.

[0021] Figure 4 This is a schematic diagram of the electrical control principle of a part of the electrical system of a preferred embodiment of the present invention.

[0022] Figure 5 This is a schematic diagram of the electrical control principle of another part of the electrical system of a preferred embodiment of the present invention.

[0023] Explanation of reference numerals in the attached figures

[0024] 1. Control cabinet; 2. Oil tank mounting bracket; 3. Oil pump mounting bracket; 4. Oil receiving box; 100. Vacuum high-level oil tank; 101. First electric heater; 102. First filter; 103. First electric regulating valve; 104. First turbine flow meter; 105. First pressure sensor; 106. Second pressure sensor; 107. Second filter; 108. Second electric regulating valve; 109. Third electric regulating valve; 110. Second turbine flow meter; 111. Second... 112. Ball valve; 113. Compressed air filter pressure reducing valve; 114. First ball valve; 115. Third ball valve; 116. Oil-gas separator; 117. Fourth electric regulating valve; 118. Vacuum pump; 201. Third filter; 202. Fifth electric regulating valve; 203. Third pressure sensor; 204. Fourth filter; 205. Sixth electric regulating valve; 206. Third turbine flow meter; 401. Lubricating oil tank; 402. Lubricating oil pump; 403. Fourth ball valve; 4 04. Fifth ball valve; 405. Sixth ball valve; 301. Low-level oil tank; 302. Fifth filter; 303. Second electric heater; 304. Seventh ball valve; 305. Circulation pump; 306. Sixth filter; 307. First relief valve; 308. Fifth pressure sensor; 309. Eighth electric regulating valve; 310. Seventh filter; 311. Eighth ball valve; 312. Seventh electric regulating valve; 313. Fourth pressure sensor; 314. Sixth pressure sensor Device; 315, Fourth turbine flow meter; 316, Ninth electric regulating valve; 317, Tenth electric regulating valve; 318, Eighth filter; 319, Second relief valve; 320, Eleventh electric regulating valve; 321, Seventh pressure sensor; 322, Eighth pressure sensor; 323, Ninth filter; 324, Ninth ball valve; 325, Tenth ball valve; 326, Cooler; 327, Eleventh ball valve; 328, Twelfth ball valve; 329, Thirteenth ball valve. Detailed Implementation

[0025] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0026] like Figure 1 and Figure 2As shown, a preferred embodiment of the present invention provides an oil pump testing device for a turboprop aero-engine, including an operating cabinet 1, a hydraulic system, an oil tank mounting bracket 2, and an oil pump mounting bracket 3. The operating cabinet 1 houses an electrical system for setting test parameters for different oil pumps, collecting data, controlling equipment actions, and implementing safety interlock protection during testing. The oil tank mounting bracket 2 is used to mount the oil tank of the hydraulic system. The oil pump mounting bracket 3 is used to mount the mid- and rear bearing oil pump, the transmission box oil pump, and the torque measuring pump, as well as the drive motors and transmission mechanisms of each oil pump. During oil pump testing, the mid- and rear bearing oil pump, the transmission box oil pump, and the torque measuring pump share a single hydraulic system. The operating cabinet 1 is located in the operating room, while the hydraulic system, the oil tank mounting bracket 2, and the oil pump mounting bracket 3 are located in the test chamber, achieving electromechanical separation, eliminating safety hazards, and facilitating maintenance.

[0027] It is understood that the oil pump testing equipment for turboprop aero-engines in this embodiment uses a single hydraulic system for the mid- and rear bearing oil pump, transmission box oil pump, and torque measuring pump during oil pump testing. The test parameters for different oil pumps are set through the electrical system, and then data acquisition, equipment action control, and safety interlock protection are performed separately. This can meet the needs of break-in tests for the three types of oil pumps, flow tests and sealing tests at different speeds and pressures, as well as high-altitude performance tests for the mid- and rear bearing oil pump. It achieves three tests in one machine, greatly improving the versatility of the oil pump testing equipment. Furthermore, it can perform at least two oil pump tests simultaneously, improving testing efficiency.

[0028] It is understood that the hydraulic system includes a first oil circuit system, a second oil circuit system, a third oil circuit system, and a fourth oil circuit system. The first oil circuit system supplies oil to the intermediate and rear bearing oil pump, the second oil circuit system supplies oil to the transmission box oil pump, and the third oil circuit system supplies oil to the torque measuring pump. Each oil pump is connected to a variable frequency high-speed motor via a coupling. The intermediate and rear bearing oil pump and the torque measuring pump are connected to the motor via a coupling with a keyway at one end and an internal spline at the other. The transmission box oil pump is connected to the motor via a coupling with a keyway at one end and external meshing teeth at the other. The fourth oil circuit system provides lubricating oil for the gear transmission between the transmission box oil pump and the motor. The first and second oil circuit systems share a common oil tank, while the third and fourth oil circuit systems each have their own separate oil tank. The variable frequency high-speed motor adjusts its speed via a frequency converter, meeting the test speed requirements with high control accuracy, and has a built-in encoder for easy speed measurement.

[0029] Specifically, such as Figure 3As shown, the first oil circuit system includes a vacuum high-level oil tank 100 and a vacuum system. The vacuum high-level oil tank 100 is equipped with a first electric heater 101, which can control the oil temperature as needed. Additionally, the vacuum high-level oil tank 100 is also equipped with a thermometer and a pressure gauge for testing the oil temperature and pressure within the tank. The vacuum system is connected to the vacuum high-level oil tank 100 and is used to evacuate the tank, ensuring adequate vacuum control during high-altitude performance tests of the mid- and rear bearing oil pumps. The two inlets of the intermediate and rear bearing oil pump are each connected to the vacuum high-level oil tank 100 via an inlet pipeline, and its outlet is connected to the vacuum high-level oil tank 100 via two return pipelines. Each inlet pipeline is equipped with a first filter 102, a first electric regulating valve 103, a first turbine flow meter 104, and a first pressure sensor 105 sequentially along the oil inlet direction, which can detect the oil flow rate and oil pressure of each inlet pipeline. The first filter 102 is a coarse filter with a filtration accuracy of 80μm. A second pressure sensor 106 and a second filter 107 are installed at the outlet of the intermediate and rear bearing oil pump. A second electric regulating valve 108 is installed on the first return pipeline, and a third electric regulating valve 109 and a second turbine flow meter 110 are sequentially installed on the second return pipeline. The vacuum high-level oil tank 100 is also connected to an external compressed air source. The pipeline connecting the two is provided with a first ball valve 113, a compressed air filter and pressure reducing valve 112, and a second ball valve 111 in sequence along the air intake direction.

[0030] The vacuum system includes a vacuum pump 117, a fourth electric regulating valve 116, an oil-gas separator 115, and a third ball valve 114. The third ball valve 114 is installed on the pipeline connecting the oil-gas separator 115 and the high-level vacuum oil tank 100. The vacuum pump 117 is connected to the oil-gas separator 115, and the fourth electric regulating valve 116 is installed on the air inlet pipeline of the vacuum pump 117.

[0031] In addition, the second oil circuit system includes a third filter 201, a fifth electric regulating valve 202, a third pressure sensor 203, a fourth filter 204, a sixth electric regulating valve 205, and a third turbine flow meter 206. The third filter 201 and the fifth electric regulating valve 202 are sequentially arranged on the oil inlet pipe of the transmission box oil pump along the oil inlet direction, and the third pressure sensor 203, the fourth filter 204, the sixth electric regulating valve 205, and the third turbine flow meter 206 are sequentially arranged on the oil return pipe along the oil return direction.

[0032] Additionally, the fourth oil circuit system includes a lubricating oil tank 401, a lubricating oil pump 402, a fourth ball valve 403, and a fifth ball valve 404. The inlet of the lubricating oil pump 402 is connected to the lubricating oil tank 401. The fourth ball valve 403 is located on the bypass oil circuit of the lubricating oil pump 402, and the fifth ball valve 404 is located on the main oil circuit of the lubricating oil pump 402. The lubricating oil pump 402 provides lubricating oil to the gear transmission between the transmission box oil pump and the motor through the main oil circuit. The main oil circuit of the lubricating oil pump 402 is also connected to the vacuum high-level oil tank 100, and a sixth ball valve 405 is installed on the pipeline connecting the two. The lubricating oil tank 401 is mounted on the oil pump mounting bracket 3.

[0033] Optionally, the oil pump testing equipment further includes an oil collection box 4 for collecting residual oil during the test. The oil collection box 4 is located below the three oil pumps and the pressure reducing valve, and the lubricating oil tank 401 is connected to the oil collection box 4.

[0034] Additionally, the third oil circuit system includes a low-level oil tank 301 and a circulation pump 305. The inlet of the circulation pump 305 is connected to the low-level oil tank 301. A fifth filter 302 and a seventh ball valve 304 are sequentially installed on the connecting pipeline. A second electric heater 303 is installed inside the low-level oil tank 301. A sixth filter 306, an eighth ball valve 311, a seventh electric regulating valve 312, and a fourth pressure sensor 313 are sequentially installed on the main oil supply line connecting the circulation pump 305 and the torque measuring pump. The main oil supply line is also connected to the low-level oil tank 301 through two bypass oil lines. A first overflow valve 307 is installed on the first bypass oil line, and a fifth pressure sensor 308, an eighth electric regulating valve 309, and a seventh filter 310 are installed on the second bypass oil line. The torque measuring pump... The main return oil line is sequentially equipped with a sixth pressure sensor 314 and a fourth turbine flow meter 315. After the fourth turbine flow meter 315, the main return oil line splits into three branches. Two of these branches merge and connect to the low-level oil tank 301, while the other branch connects to a pressure reducing valve. The two merging branches are respectively equipped with a ninth electric regulating valve 316 and a tenth electric regulating valve 317. An eighth filter 318 is also installed between the two merging branches and the low-level oil tank 301. The main return oil line is also connected to the low-level oil tank 301 via a bypass oil line. The bypass oil line is equipped with a second overflow valve 319. The branch connected to the pressure reducing valve is sequentially equipped with an eleventh electric regulating valve 320 and a seventh pressure sensor 321. An eighth pressure sensor 322 is installed on the output oil line of the pressure reducing valve. The low-level oil tank 301 and the vacuum high-level oil tank 100 are mounted on the oil tank mounting bracket 2.

[0035] In addition, the main oil supply line of the circulating pump 305 is also connected to the oil replenishment port of the vacuum high-level oil tank 100. The pipeline connecting the two is equipped with a ninth filter 323 and a ninth ball valve 324 in sequence. The oil outlet of the vacuum high-level oil tank 100 is also connected to the low-level oil tank 301. The pipeline connecting the two is equipped with a tenth ball valve 325, thereby realizing oil-liquid complementarity between the two oil tanks.

[0036] In addition, the third oil circuit system also includes a cooler 326 for cooling the oil. The oil inlet and oil outlet of the cooler 326 are both connected to the main oil supply circuit. An eleventh ball valve 327 is installed on the oil inlet, a twelfth ball valve 328 is installed on the oil outlet, and a thirteenth ball valve 329 is installed on the water inlet of the cooler 326.

[0037] Understandable, such as Figure 4 and Figure 5As shown, the electrical system can control the start / stop and speed of multiple motors, as well as the opening of multiple electric regulating valves and the start / stop of electric heaters. The control circuits for the multiple motors and electric regulating valves are connected in parallel. Each electrical component connected to the main circuit is equipped with a circuit breaker, contactor, or other control element. The operating state of each control element is controlled to control the operating state of the corresponding electrical component. Additionally, thermal relays are installed on the control circuits of the circulating pump motor, lubrication pump motor, and vacuum pump motor. The electrical system comprises a PLC, KingSCADA software, sensors, an industrial computer, a monitor, a printer, and other electrical control accessories. Its main functions include: equipment motion control, sensor parameter acquisition, data table recording and printing, and safety interlock protection. The equipment operating voltage is 380V±10%, three-phase, and the frequency is 50Hz±2%. The lubricating oil working medium is heated by an electric heater and controlled by a solid-state relay temperature control system to meet process requirements. The three tested oil pumps are each driven by a variable frequency motor, with speed regulation via a frequency converter. The operating speed of the pumps is set in the equipment's operating software to meet process requirements. Process parameters such as outlet pressure, inlet pressure, operating speed, flow rate, and temperature are collected by sensors, conditioned, and then input to the PLC for display in the data acquisition software. The system allows users to set protection values ​​for the operating status. When the equipment's operating status exceeds the protection value, it automatically shuts down to ensure safe operation. Essentially, this equipment integrates three test objects into a single testing unit. The three test objects operate independently without interference and have an automatic data acquisition function, improving testing efficiency. The operator only needs to adjust the motor speed and oil pressure according to the test process to complete the test. The equipment automatically determines whether the test results are acceptable and provides operator feedback. Furthermore, the equipment has comprehensive protection functions; it automatically shuts down when operator error occurs or equipment parameters exceed preset safety values.

[0038] As is understandable, the test contents for the intermediate and rear bearing oil pump are shown in Table 1:

[0039] Table 1. Test Items for Middle and Rear Bearing Oil Pumps

[0040]

[0041] The testing process for the intermediate and rear bearing oil pump is as follows:

[0042] A. Install the test oil pump and connect the two inlet oil lines and one return oil line of the test oil pump;

[0043] B. Heat the oil in the high-level oil tank to meet the test temperature requirements;

[0044] C. According to the test items 1-7 in Table 1, adjust the opening of the oil pump inlet and return electric valves and the speed of the oil pump drive motor to meet the test pressure and speed requirements, and carry out the oil pump break-in and sealing test.

[0045] D. According to the test item number 8 in Table 1, adjust the opening of the oil pump inlet and return electric valves, adjust the speed of the oil pump drive motor, and at the same time open the compressed air intake of the high-level oil tank to replenish the oil pump inlet pressure to meet the test pressure and speed requirements, and measure the two inlet flow rates of the oil pump.

[0046] E. According to the test item in Serial No. 9 of Table 1, adjust the opening of the oil pump inlet and return electric valves, adjust the speed of the oil pump drive motor, open the electric regulating valve on the return oil line where the flow meter is located, and close the electric regulating valve on the return oil line without the flow meter. After meeting the test pressure and speed requirements, measure the small inlet flow rate of the oil pump at low speed.

[0047] F. According to test item 10 in Table 1, adjust the opening of the oil pump inlet and outlet electric valves, adjust the speed of the oil pump drive motor, close the compressed air inlet valve, open the vacuum pump inlet valve, start the vacuum pump, and after meeting the test pressure and speed requirements, measure the high-altitude performance flow rate of the oil pump.

[0048] In addition, the test contents for the transmission box oil pump are shown in Table 2:

[0049] Table 2. Test Items for the Transmission Box Oil Pump

[0050]

[0051] The test process for the transmission box oil pump is as follows:

[0052] A. Install the test oil pump and connect the inlet and return oil lines of the test oil pump;

[0053] B. Heat the oil in the high-level oil tank to meet the test temperature requirements;

[0054] C. According to the test items 1-8 in Table 2, adjust the opening of the oil pump inlet and return electric valves, adjust the speed of the oil pump drive motor to meet the test pressure and speed requirements, start the oil pump lubrication pump, and carry out the oil pump break-in, sealing and flow performance tests.

[0055] In addition, the test contents for measuring the torque pump are shown in Table 3:

[0056] Table 3. Test Items for Torque Pumps

[0057]

[0058] The test procedure for the torque pump is as follows:

[0059] A. Install the test oil pump and connect the inlet and return oil lines of the test oil pump;

[0060] B. Heat the oil in the lower oil tank to meet the test temperature requirements;

[0061] C. According to the test items 1-10 in Table 3, adjust the opening of the oil pump inlet and return electric valves, adjust the speed of the oil pump drive motor, meet the test pressure and speed requirements, and carry out oil pump break-in, performance inspection and sealing test.

[0062] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An oil pump test apparatus for a turboprop aircraft engine, characterized in that, The utility model provides a kind of oil pump test device, including operation cabinet (1), hydraulic system, oil tank mounting frame (2), oil pump mounting frame (3), the operation cabinet (1) is provided with electrical system, for setting different oil pump test parameters in test, data acquisition, equipment action control and safety interlock protection, the oil tank mounting frame (2) is used to install the oil tank of hydraulic system, the oil pump mounting frame (3) is used to install middle rear bearing oil pump, transmission box oil pump and measure torsion pump and the drive motor and transmission mechanism of each oil pump, when carrying out oil pump test, middle rear bearing oil pump, transmission box oil pump and measure torsion pump share a set of hydraulic system;The hydraulic system includes first oil circuit system, second oil circuit system, third oil circuit system and fourth oil circuit system, the first oil circuit system is used to supply oil for middle rear bearing oil pump, the second oil circuit system is used to supply oil for transmission box oil pump, the third oil circuit system is used to supply oil for measure torsion pump, each oil pump is connected with a variable frequency high-speed motor by coupling, wherein middle rear bearing oil pump and measure torsion pump are connected with motor by coupling with one end with flat key hole and the other end with internal spline hole, transmission box oil pump is connected with motor by coupling with one end with flat key hole and the other end with external meshing tooth, the fourth oil circuit system is used to provide lubricating oil for gear transmission between transmission box oil pump and motor, the first oil circuit system and the second oil circuit system share an oil tank, the third oil circuit system and the fourth oil circuit system are each provided with an oil tank.

2. The oil pump test apparatus for turboprop aeroengines as claimed in claim 1, characterized in that, The first oil circuit system includes vacuum high oil tank (100) and vacuum system, the first electric heater (101) is provided in the vacuum high oil tank (100), the vacuum system is connected with the vacuum high oil tank (100), for vacuumizing the vacuum high oil tank (100), two oil inlets of middle rear bearing oil pump are connected with the vacuum high oil tank (100) by an oil inlet pipeline respectively, and the oil outlet is connected with the vacuum high oil tank (100) by two oil return pipelines, a first filter (102), a first electric regulating valve (103), a first turbine flowmeter (104) and a first pressure sensor (105) are sequentially arranged on each oil inlet pipeline along the oil inlet direction, a second pressure sensor (106) and a second filter (107) are arranged at the oil outlet of middle rear bearing oil pump, a second electric regulating valve (108) is arranged on the first oil return pipeline, a third electric regulating valve (109) and a second turbine flowmeter (110) are sequentially arranged on the second oil return pipeline, the vacuum high oil tank (100) is also connected with external compressed air source, a first ball valve (113), compressed air filter pressure reducing valve (112) and second ball valve (111) are sequentially arranged on the pipeline connected with both along the air inlet direction.

3. The oil pump test apparatus for turboprop aeroengines as claimed in claim 2, characterized in that, The vacuum system comprises a vacuum pump (117), a fourth electric regulating valve (116), an oil-gas separator (115) and a third ball valve (114), the third ball valve (114) is arranged on a pipeline connecting the oil-gas separator (115) and the vacuum high oil tank (100), the vacuum pump (117) is connected with the oil-gas separator (115), and the fourth electric regulating valve (116) is arranged on an air inlet pipeline of the vacuum pump (117).

4. The oil pump test apparatus for turboprop aeroengines as claimed in claim 2, characterized in that, The second oil system comprises a third filter (201), a fifth electric regulating valve (202), a third pressure sensor (203), a fourth filter (204), a sixth electric regulating valve (205) and a third turbine flowmeter (206), the third filter (201) and the fifth electric regulating valve (202) are sequentially arranged on an oil inlet pipeline of the transmission box oil pump in an oil inlet direction, and the third pressure sensor (203), the fourth filter (204), the sixth electric regulating valve (205) and the third turbine flowmeter (206) are sequentially arranged on an oil return pipeline in an oil return direction.

5. The oil pump test apparatus for turboprop aeroengines as claimed in claim 2, characterized in that, The fourth oil system comprises a lubricating oil tank (401), a lubricating oil pump (402), a fourth ball valve (403) and a fifth ball valve (404), the inlet of the lubricating oil pump (402) is connected with the lubricating oil tank (401), the fourth ball valve (403) is arranged on a bypass pipeline of the lubricating oil pump (402), the fifth ball valve (404) is arranged on a main pipeline of the lubricating oil pump (402), the lubricating oil pump (402) provides lubricating oil for gear transmission between the transmission box oil pump and the motor through the main pipeline, the main pipeline of the lubricating oil pump (402) is also connected with the vacuum high oil tank (100), and a sixth ball valve (405) is arranged on a pipeline connecting the vacuum high oil tank (100).

6. The oil pump test apparatus for turboprop aeroengines, as set forth in claim 5, characterized in that, An oil collecting box (4) for collecting residual oil during the test is further included, and the lubricating oil tank (401) is connected with the oil collecting box (4).

7. The oil pump test apparatus for turboprop aeroengines as claimed in claim 2, characterized in that, The third oil circuit system comprises a low oil tank (301) and a circulating pump (305), the inlet of the circulating pump (305) is connected with the low oil tank (301), a fifth filter (302) and a seventh ball valve (304) are sequentially arranged on the pipeline connected with the two, a second electric heater (303) is arranged in the low oil tank (301), a sixth filter (306), an eighth ball valve (311), a seventh electric regulating valve (312) and a fourth pressure sensor (313) are sequentially arranged on the main oil supply pipeline connected with the circulating pump (305), the main oil supply pipeline is also connected to the low oil tank (301) through two bypass oil circuits, a first overflow valve (307) is arranged on the first bypass oil circuit, a fifth pressure sensor (308), an eighth electric regulating valve (309) and a seventh filter (310) are arranged on the second bypass oil circuit, a sixth pressure sensor (314) and a fourth turbine flowmeter (315) are sequentially arranged on the main oil return pipeline of the torque measuring pump, the main oil return pipeline is divided into three branches after the fourth turbine flowmeter (315), two of the three branches are connected to the low oil tank (301) after being converged, the other branch is connected with a pressure relief valve, a ninth electric regulating valve (316) and a tenth electric regulating valve (317) are arranged on the two converged branches respectively, an eighth filter (318) is further arranged between the two converged branches and the low oil tank (301), the main oil return pipeline is also connected to the low oil tank (301) through a bypass oil circuit, a second overflow valve (319) is arranged on the bypass oil circuit, an eleventh electric regulating valve (320) and a seventh pressure sensor (321) are sequentially arranged on the branch connected with the pressure relief valve, and an eighth pressure sensor (322) is arranged on the output oil circuit of the pressure relief valve.

8. The oil pump test apparatus for turboprop aeroengines, as set forth in claim 7, characterized in that, The main oil supply pipeline of the circulating pump (305) is also connected with the oil supplementing port of a vacuum high oil tank (100), a ninth filter (323) and a ninth ball valve (324) are sequentially arranged on the pipeline connected with the two, the oil outlet of the vacuum high oil tank (100) is also connected with the low oil tank (301), and an tenth ball valve (325) is arranged on the pipeline connected with the two, so that the oil in the two oil tanks is complementary.

9. The oil pump test apparatus for turboprop aeroengines as claimed in claim 7, characterized in that, The third oil circuit system further comprises a cooler (326) for cooling oil, the oil inlet pipeline and the oil outlet pipeline of the cooler (326) are both connected with the main oil supply pipeline, an eleventh ball valve (327) is arranged on the oil inlet pipeline of the cooler (326), and a twelfth ball valve (328) is arranged on the oil outlet pipeline of the cooler (326), and a thirteenth ball valve (329) is arranged on the water inlet pipeline of the cooler (326).

Images