Double-pump oil supply device for piston type aero-engine test bed

Abstract

The utility model discloses a piston type aero-engine test bed double-pump oil supply device which comprises a constant-pressure oil supply pump, a first filter and a mounting support, the constant-pressure oil supply pump is arranged at the top end of the mounting support, and the first filter is arranged at the input end of the constant-pressure oil supply pump through a connecting pipeline. An oil suction port connected with the oil tank is formed in the end, away from the constant-pressure oil supply pump, of the first filter, the output end of the constant-pressure oil supply pump is provided with a second filter through a connecting pipeline, and the side, away from the constant-pressure oil supply pump, of the second filter is provided with a two-way adjusting mechanism through a support; the device is provided with a start-stop control contactor which is connected to an original test bench control cabinet, and centralized control is carried out on a bench, so that the configuration on an airplane can be simulated, and an engine can be verified to switch an oil supply pump at any time through the start-stop control contactor.

Description

Technical Field

[0001] The utility model relates to the technical field of piston aeroengines, in particular to a double-pump oil supply device for a piston aeroengine test bench. Background Technique

[0002] In the development process of existing piston aeroengines, a large number of reliability and durability tests need to be carried out on the test bench, and a large amount of operation data is recorded for the development data analysis and the collection of engine performance criteria. During the test process, the speed and load have a great influence on the performance and life of the engine body and the main moving pairs. In order to more realistically simulate the operation conditions and control states of the engine when it is installed on an aircraft, separate verifications will also be carried out for the specific mechanism functions of the aircraft. This requires that the test bench configuration needs to be close to the actual structure of the aircraft. At present, engine tests are all carried out using a complete set of dynamometer test benches.

[0003] However, the existing double-pump oil supply device for a piston aeroengine test bench has the following problems during use: the original test bench does not have the functions of double pumps, independent, and automatic oil supply. It is necessary to transform the original test bench oil supply system, and thus it is impossible to simulate the real state of double-pump oil supply during aircraft operation. The existing test benches need to consider aspects such as reducing R & D costs, reducing operation difficulties, and flexibly configuring piston aeroengine test conditions. Content of the Utility Model

[0004] The purpose of the utility model is to provide a double-pump oil supply device for a piston aeroengine test bench to solve the related problems of not having the functions of double pumps, independent, and automatic oil supply.

[0005] To achieve the above purpose, the utility model provides the following technical solution: A double-pump oil supply device for a piston aeroengine test bench, including a constant-pressure oil supply pump, a first filter, and a mounting bracket. The top of the mounting bracket is provided with a constant-pressure oil supply pump, and the input end of the constant-pressure oil supply pump is provided with a first filter through a connecting pipeline. One end of the first filter away from the constant-pressure oil supply pump is provided with an oil suction port connected to the fuel tank. The output end of the constant-pressure oil supply pump is provided with a second filter through a connecting pipeline, and a two-way adjustment mechanism is respectively arranged on one side of the second filter away from the constant-pressure oil supply pump through a bracket.

[0006] In the double-pump oil supply device for a piston aeroengine test bench provided by the technical solution, a start-stop control contactor is arranged on one side of the mounting bracket, and an oil supply pump cable connected to the input end of the constant-pressure oil supply pump is arranged at the output end of the start-stop control contactor, and a control cable is arranged at the input end of the start-stop control contactor.

[0007] A dual-pump fuel supply device for a piston-type aero-engine test bench provided by the technical solution, wherein the oil pressure of the constant-pressure fuel supply pump is 0.5 - 5.6 bar.

[0008] A dual-pump fuel supply device for a piston-type aero-engine test bench provided by the technical solution, wherein the two-way adjustment mechanism includes a second pressure regulating valve and an oil outlet. A second pressure regulating valve is provided on one side of the second filter, and an oil outlet connected to the engine fuel supply is provided on one side of the second pressure regulating valve through a connecting pipeline.

[0009] A dual-pump fuel supply device for a piston-type aero-engine test bench provided by the technical solution, wherein a first pressure regulating valve is provided between the second filter and the second pressure regulating valve through a tee pipe, and an overpressure oil discharge port connected to the fuel tank is provided on the side of the first pressure regulating valve away from the second filter.

[0010] A dual-pump fuel supply device for a piston-type aero-engine test bench provided by the technical solution, wherein a check valve for oil circuit isolation is provided on the side of the second pressure regulating valve close to the oil outlet.

[0011] Compared with the prior art, the present utility model provides a dual-pump fuel supply device for a piston-type aero-engine test bench, which has the following beneficial effects:

[0012] 1. By installing this device on the original equipment, and there is another set of pumps at the original equipment, and it is connected to the control cabinet of the original test bench through the start-stop control contactor, and is centrally controlled on the test bench, so that the configuration on the aircraft can be simulated, and it can be verified that the fuel supply pump can be switched at any time through the start-stop control contactor.

[0013] 2. In the present utility model, the fuel adjusts the oil circuit pressure and the oil return pressure protection through the second pressure regulating valve and the first pressure regulating valve, and the check valve facilitates the independent operation of the two sets of fuel supply oil circuits, and there will be no interference with the original oil pump delivery port. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a three-dimensional structural schematic diagram of the present utility model.

[0015] In the figure: 1. Constant-pressure fuel supply pump; 2. First filter; 3. First pressure regulating valve; 4. Start-stop control contactor; 5. Check valve; 6. Mounting bracket; 7. Oil suction port; 8. Second filter; 9. Overpressure oil discharge port; 10. Second pressure regulating valve; 11. Oil outlet; 12. Control cable; 13. Fuel supply pump cable. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0016] The following will clearly and completely describe the technical solutions in the embodiments of the present utility model in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without making creative efforts shall fall within the protection scope of the present utility model.

[0017] Embodiment 1, as Figure 1 shown, the present utility model provides a technical solution: a double-pump oil supply device for a piston-type aero-engine test bench, including a constant-pressure oil supply pump 1, a first filter 2 and a mounting bracket 6. The constant-pressure oil supply pump 1 is arranged at the top of the mounting bracket 6, and the input end of the constant-pressure oil supply pump 1 is provided with the first filter 2 through a connecting pipeline. One end of the first filter 2 away from the constant-pressure oil supply pump 1 is provided with an oil suction port 7 connected to the fuel tank. The output end of the constant-pressure oil supply pump 1 is provided with a second filter 8 through a connecting pipeline. On one side of the second filter 8 away from the constant-pressure oil supply pump 1, a two-way regulating mechanism is respectively arranged through a bracket. A start-stop control contactor 4 is arranged on one side of the mounting bracket 6, and the output end of the start-stop control contactor 4 is provided with an oil supply pump cable 13 connected to the input end of the constant-pressure oil supply pump 1. The input end of the start-stop control contactor 4 is provided with a control cable 12. The oil pressure of the constant-pressure oil supply pump 1 is 0.5 - 5.6 bar. The two-way regulating mechanism includes a second pressure regulating valve 10 and an oil outlet 11. The second pressure regulating valve 10 is arranged on one side of the second filter 8, and an oil outlet 11 connected to the engine oil supply is arranged on one side of the second pressure regulating valve 10 through a connecting pipeline. By combining this device with the original test bench oil supply system to form a double-pump oil supply system, the start-stop control contactor 4 is connected to the original test bench control cabinet through startup, and centralized control is carried out on the test bench, so as to simulate the configuration on the aircraft and verify that the engine can switch the oil supply pump at any time through the start-stop control contactor 4.

[0018] Embodiment 2, as Figure 1 shown, the present utility model provides a technical solution: a first pressure regulating valve 3 is arranged between the second filter 8 and the second pressure regulating valve 10 through a three-way pipe, and an overpressure oil discharge port 9 connected to the fuel tank is arranged on one side of the first pressure regulating valve 3 away from the second filter 8. A one-way valve 5 for oil circuit isolation is arranged on one side of the second pressure regulating valve 10 close to the oil outlet 11. In order to ensure the cleanliness of the oil circuit during transportation, the first filter 2 and the second filter 8 are used for filtration, and this filtration adopts the oil suction and oil discharge filtration methods. Then, the fuel adjusts the oil circuit pressure and the oil return pressure protection through the second pressure regulating valve 10 and the first pressure regulating valve 3, and the one-way valve 5 facilitates the independent operation of the two sets of oil supply oil circuits, and there will be no interference with the original oil pump delivery port.

[0019] Working principle: First, connect the external power supply. Integrate the constant-pressure fuel supply pump 1, the first filter 2, the first pressure regulating valve 3, the one-way valve 5 and accessories such as connecting pipelines onto the mounting bracket 6 in the functional sequence, and reserve the oil suction port 7, the oil outlet 11, and the overpressure oil discharge port 9 for connection with the original test bench fuel supply system. This device is installed on the original equipment, and there is also a set of pumps at the original equipment. It is connected to the original test bench control cabinet through the start-stop control contactor 4, and is centrally controlled on the test bench, so as to simulate the configuration on the aircraft and verify that the fuel supply pump can be switched at any time through the start-stop control contactor 4. The operation process is as follows: The test bench starts the constant-pressure fuel supply pump 1 according to the operation requirements. A negative pressure is formed at the oil suction port 7 of the constant-pressure fuel supply pump 1, and the fuel passes through the first filter 2 to the constant-pressure fuel supply pump 1. The oil pressure at the outlet of the constant-pressure fuel supply pump 1 is 0.5 - 5.5 bar and passes through the second filter 8, and then through the second pressure regulating valve 10, the fuel is divided into two paths. One path goes to the engine, and the other path returns to the fuel tank through the first pressure regulating valve 3. A set of start-stop control contactors 4 is added to the original test bench fuel pump control circuit and connected to the PLC control module to achieve the purpose of dual-pump, independent, and automatic fuel supply. The structural form of the dual-pump fuel supply device for this piston-type aero-engine test bench fully simulates the actual fuel supply mode of the aircraft. This device is applied to the development test of domestic general aviation piston engines for the first time. On the premise of meeting the test requirements, this device has the advantages of low cost, convenient operation, and movable test laboratory site, etc. It avoids repeated investment and can effectively reduce the R & D cost. Currently, it is operating well.

[0020] Finally, it should be noted that the above content is only used to illustrate the technical solution of the present invention, rather than a limitation on the protection scope of the present invention. Any simple modification or equivalent replacement made by those of ordinary skill in the art to the technical solution of the present invention does not depart from the essence and scope of the technical solution of the present invention.

Claims

1. A dual-pump fuel supply device for a piston-type aero-engine test bench, comprising a constant-pressure fuel supply pump (1), a first filter (2) and a mounting bracket (6), characterized in that: The top of the mounting bracket (6) is provided with a constant-pressure oil supply pump (1), and the input end of the constant-pressure oil supply pump (1) is provided with a first filter (2) through a connecting pipeline. One end of the first filter (2) far from the constant-pressure oil supply pump (1) is provided with an oil suction port (7) connected to the fuel tank. The output end of the constant-pressure oil supply pump (1) is provided with a second filter (8) through a connecting pipeline, and a two-way adjustment mechanism is respectively arranged on one side of the second filter (8) far from the constant-pressure oil supply pump (1) through a bracket.

2. The double-pump fuel supply device for a piston-type aero-engine test bench according to claim 1, wherein: One side of the mounting bracket (6) is provided with a start-stop control contactor (4), and the output end of the start-stop control contactor (4) is provided with an oil supply pump cable (13) connected to the input end of the constant-pressure oil supply pump (1). The input end of the start-stop control contactor (4) is provided with a control cable (12).

3. The double-pump fuel supply device for a piston-type aero-engine test bench according to claim 1, characterized in that: The oil pressure of the constant-pressure oil supply pump (1) is 0.5 - 5.6 bar.

4. A double-pump fuel supply device for a piston-type aero-engine test bench according to claim 1, characterized in that: The two-way adjustment mechanism includes a second pressure regulating valve (10) and an oil outlet (11). One side of the second filter (8) is provided with the second pressure regulating valve (10), and an oil outlet (11) connected to the engine oil supply is arranged on one side of the second pressure regulating valve (10) through a connecting pipeline.

5. A double-pump fuel supply device for a piston-type aero-engine test bench according to claim 4, characterized in that: A first pressure regulating valve (3) is arranged between the second filter (8) and the second pressure regulating valve (10) through a three-way pipe, and an overpressure oil discharge port (9) connected to the fuel tank is arranged on one side of the first pressure regulating valve (3) far from the second filter (8).

6. The dual-pump fuel supply device for a piston-type aero-engine test bench according to claim 4, characterized in that: A one-way valve (5) for oil circuit isolation is arranged on one side of the second pressure regulating valve (10) close to the oil outlet (11).

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