Testing device and testing method for high-pressure fuel pump of aviation piston type engine

Abstract

The invention discloses an aviation piston type engine high-pressure fuel pump test device and test method, and relates to the technical field of aviation engine high-pressure fuel pump tests, the aviation piston type engine high-pressure fuel pump test device comprises a fuel oil pool, and one side of the fuel oil pool is communicated with the top end of a cooling oil pool through a first oil pipe; a first temperature control meter and a second flow meter are arranged on one side of a first oil pipe at the top end of the cooling oil pool, the rear wall of the fuel oil pool is communicated with the input end of a low-pressure oil pump through one end of a fuel oil inlet pipe, the output end of the low-pressure oil pump is communicated with the input end of a high-pressure fuel oil pump through a second oil pipe, and a first pressure meter is arranged at the second oil pipe. The output end of the high-pressure fuel pump communicates with one end of the energy storage pool through a third oil pipe, and a first flowmeter is arranged at the third oil pipe. According to the device, information of the temperature, the rotating speed and the pressure at the high-pressure fuel pump is checked through the upper computer, and the information flows back to the fuel pool through the energy storage pool; the fuel oil fan, the oil cooler and the fan are used for cooling the fuel oil and then recycling the fuel oil.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine high-pressure fuel pump testing, in particular to an aircraft piston engine high-pressure fuel pump testing device and a testing method. Background Art

[0002] The aviation piston engine is a 4-cylinder, 4-stroke, aviation kerosene, dual overhead camshaft, 4 valves per cylinder, water-cooled, compression-ignition aviation piston engine. The engine is equipped with a gearbox, which integrates a hydraulic governor interface for constant-speed variable-pitch propellers. The propellers and control levers equipped on existing aircraft are used. At the same time, considering factors such as technical maturity, the engine fuel electronic control system selects a high-pressure common rail and full-authority digital control system to achieve a single control lever to control the engine and propeller at the same time. At the same time, in order to improve the reliability of the control system, a dual-channel redundant design is carried out for the EEC and important sensors. In order to ensure the performance of the engine, especially the altitude characteristics, the intake system selects a turbocharger technology solution. In order to ensure the performance of the engine, especially the altitude characteristics, the intake system selects a turbocharger technology solution. The fuel is directly injected through the high-pressure common rail system, and the air enters the cylinder after being pressurized by the supercharging system. The sensors and actuators on the engine components collect information data and control the corresponding actions through the host computer.

[0003] However, the existing aviation piston engine high-pressure fuel pump test equipment and test methods have the following problems during use: the traditional high-pressure fuel pump is tested by mounting the engine, the pump flow cannot be monitored, and when the pressure in the pump is high, a pressure reducing valve is required, which also increases the complexity and cost of the system. Summary of the invention

[0004] The object of the present invention is to provide a test device and a test method for a high-pressure fuel pump of an aviation piston engine, so as to solve the related problems raised in the above-mentioned background technology.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a test device and a test method for a high-pressure fuel pump of an aviation piston engine, comprising a fuel pool, one side of the fuel pool is connected to the top of a cooling oil pool through a first oil pipe, one side of the first oil pipe at the top of the cooling oil pool is provided with a first temperature control meter and a second flow meter, the rear wall of the fuel pool is connected to the input end of a low-pressure fuel pump through one end of a fuel inlet pipe, the output end of the low-pressure fuel pump is connected to the input end of a high-pressure fuel pump through a second oil pipe, and a first pressure gauge is provided at the second oil pipe, and the output end of the high-pressure fuel pump is connected to the input end of a high-pressure fuel pump through a third oil pipe. The oil pipe is connected with one end of the energy storage tank, and the first flow meter is arranged at the third oil pipe, the third temperature control meter is arranged at one end of the high-pressure fuel pump, the energy storage tank and the fuel tank are connected through the fuel return pipe, a driving motor is arranged on one side of the high-pressure fuel pump, a speed sensor is installed at the output end of the driving motor, and the speed sensor, the first pressure gauge and the output end of the third temperature control meter are electrically connected with the input end of the signal generator through a wire, the output end of the signal generator is electrically connected with the input end of the host computer through a wire, and a cooling mechanism for rapid heat exchange is arranged inside the cooling oil pool.

[0006] The technical solution provides an aviation piston engine high-pressure fuel pump test device, wherein the cooling mechanism includes a fan and an oil cooler, the oil cooler is arranged inside the cooling oil pool, and the fan is arranged at the top of the cooling oil pool.

[0007] The technical solution provides an aviation piston engine high-pressure fuel pump test device, wherein the bottom end of the fuel pool is connected to one end of a cooling oil pool through an output pipe, and a second ball valve and a first fuel filter are provided at one end of the fuel pool.

[0008] The technical solution provides an aviation piston engine high-pressure fuel pump test device, wherein a second temperature control meter for monitoring the fuel temperature is arranged above the fuel pool, and a second fuel filter is arranged inside the fuel pool.

[0009] The technical solution provides an aviation piston engine high-pressure fuel pump test device, wherein a first ball valve is provided at one end of the fuel inlet pipe close to the fuel pool.

[0010] The technical solution provides an aviation piston engine high-pressure fuel pump test device, wherein a fuel fan for cooling is arranged on one side of the fuel return pipe, and a flow control valve and a third ball valve are respectively installed at both ends of the fuel return pipe.

[0011] The technical solution provides an aviation piston engine high-pressure fuel pump test device, wherein the energy storage tank is provided with a second pressure gauge for controlling the pressure in the cavity at one end away from the first flow meter.

[0012] The technical solution provides an aviation piston engine high-pressure fuel pump test device, wherein one end of the drive motor is connected to the electric control box.

[0013] The technical solution provides a test method for an aviation piston engine high-pressure fuel pump test device, comprising the following steps: S1, start the low-pressure fuel pump to transport the fuel in the fuel pool to the input end of the high-pressure fuel pump; S2, start the high-pressure fuel pump to deliver the oil pressure to the energy storage tank; S3, feeding back the oil pressure information to the input terminal of the host computer through the low-pressure oil pump, the drive motor and the first flow meter; S4. Check the temperature, speed and pressure of the high-pressure fuel pump through the host computer; S5. The fuel flows back to the fuel tank through the energy storage tank, and the fuel is cooled by the fuel blower, oil cooler and fan before being recycled.

[0014] Compared with the prior art, the present invention provides an aviation piston engine high-pressure fuel pump test device and test method, which has the following beneficial effects: The present invention starts the low-pressure oil pump to transfer the fuel in the fuel pool to the input end of the high-pressure fuel pump, and then starts the high-pressure fuel pump to transfer the oil pressure to the energy storage tank. The oil pressure information is fed back to the input end of the host computer through the low-pressure oil pump, the drive motor and the first flow meter. The temperature, speed and pressure information at the high-pressure fuel pump are checked by the host computer. The fuel flows back to the fuel pool through the energy storage tank, and the fuel is cooled by a fuel blower, an oil cooler and a fan. In addition, impurities can be filtered through the first fuel filter element position so that the fuel flows to the cooling oil pool. This structure is convenient for cooling the fuel and recycling it. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the internal circuit structure of the present invention.

[0016] In the figure: 1. host computer; 2. signal generator; 3. electric control box; 4. drive motor; 5. speed sensor; 6. fuel inlet pipe; 7. low-pressure oil pump; 8. first pressure gauge; 9. high-pressure fuel pump; 10. first flow meter; 11. energy storage tank; 12. second pressure gauge; 13. flow control valve; 14. fan; 15. first temperature control meter; 16. second flow meter; 17. second temperature control meter; 18. first ball valve; 19. oil cooler; 20. second ball valve; 21. first fuel filter element; 22. fuel tank; 23. second fuel filter element; 24. third ball valve; 25. fuel fan; 26. third temperature control meter; 27. fuel return pipe. DETAILED DESCRIPTION

[0017] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0018] Embodiment 1, as Figure 1 As shown, the present invention provides a technical solution: a high-pressure fuel pump test device for an aviation piston engine, comprising a fuel pool 22, one side of the fuel pool 22 is connected to the top of a cooling oil pool through a first oil pipe, one side of the first oil pipe at the top of the cooling oil pool is provided with a first temperature control meter 15 and a second flow meter 16, the rear wall of the fuel pool 22 is connected to the input end of a low-pressure fuel pump 7 through one end of a fuel inlet pipe 6, the output end of the low-pressure fuel pump 7 is connected to the input end of a high-pressure fuel pump 9 through a second oil pipe, and a first pressure gauge 8 is provided at the second oil pipe, and the output end of the high-pressure fuel pump 9 is connected to the input end of an energy storage tank 11 through a third oil pipe. One end is connected, and a first flow meter 10 is arranged at the third oil pipe, a third temperature control meter 26 is arranged at one end of the high-pressure fuel pump 9, the energy storage tank 11 and the fuel tank 22 are connected through a fuel return pipe 27, a driving motor 4 is arranged on one side of the high-pressure fuel pump 9, a speed sensor 5 is installed on the output end of the driving motor 4, and the speed sensor 5, the first pressure gauge 8 and the output end of the third temperature control meter 26 are electrically connected to the input end of the signal generator 2 through a wire, and the output end of the signal generator 2 is electrically connected to the input end of the host computer 1 through a wire, and a cooling mechanism for rapid heat exchange is arranged inside the cooling oil pool, and the cooling mechanism The structure includes a fan 14 and an oil cooler 19. The oil cooler 19 is arranged inside the cooling oil pool. The fan 14 is arranged at the top of the cooling oil pool. The bottom of the fuel pool 22 is connected to one end of the cooling oil pool through an output pipe. A second ball valve 20 and a first fuel filter element 21 are arranged at one end of the fuel pool 22. A fuel fan 25 for cooling is arranged on one side of a fuel return pipe 27. A flow control valve 13 and a third ball valve 24 are respectively installed at both ends of the fuel return pipe 27. The fuel fan 25 is connected to the fuel return pipe 27 to cool the fuel. The fuel flows to the fuel pool 22 through the fuel return pipe 27. The fuel pool 22 The fuel temperature is monitored by the second temperature control meter 17. When the fuel temperature is higher than the set value, the oil cooler 19 is started to control the fuel temperature within the product requirement range. The oil cooler 19 is connected to the fan 14, the first temperature control meter 15, the second flow meter 16, the second ball valve 20, and the first fuel filter element 21. When the fuel temperature monitored by the second temperature control meter 17 in the fuel pool 22 reaches the product requirement, the oil cooler 19 is turned off, and impurities are filtered through the second fuel filter element 23 in the fuel pool 22. Impurities can be filtered through the position of the first fuel filter element 21 so that they flow to the cooling oil pool. This structure is convenient for recycling the fuel after cooling.

[0019] Embodiment 2, as Figure 1 As shown, the present invention provides a technical solution: a high-pressure fuel pump test device for an aviation piston engine, comprising a second temperature control meter 17 for monitoring the fuel temperature arranged above a fuel pool 22, a second fuel filter element 23 arranged inside the fuel pool 22, a first ball valve 18 arranged at one end of a fuel inlet pipe 6 close to the fuel pool 22, a second pressure gauge 12 for controlling the pressure in the cavity arranged at one end of an energy storage tank 11 away from a first flow meter 10, one end of a driving motor 4 is connected to an electric control box 3, when a host computer 1 receives an instruction from a signal generator 2, it commands the driving motor 4 to rotate, the driving motor 4 is connected to a speed sensor 5, the speed sensor 5 feeds back the speed of the driving motor 4 to the host computer 1 in real time, the driving motor 4 is connected to a high-pressure fuel pump 9, and both ends of the high-pressure fuel pump 9 are connected to the first pressure gauge 8, a third temperature control meter 26, a first flow meter 10, and a front end of the first pressure gauge 8 are connected to a low-pressure oil pump 7, and the low-pressure oil pump 7 absorbs the fuel in the fuel pool 22 through the fuel inlet pipe 6. The fuel pool 22 is connected to a first ball valve 18 and a second fuel filter element 23. The low-pressure oil pump 7 transmits the fuel in the fuel pool 22 to the high-pressure fuel pump 9 through the fuel inlet pipe 6. The fuel in the fuel pool 22 is pressurized by the high-pressure fuel pump 9 to the energy storage tank 11. The energy storage tank 11 controls the pressure in the cavity through the second pressure gauge 12. When the set pressure is reached, the flow control valve 13 opens to discharge the excess fuel through the fuel return pipe 27. The temperature, pressure, and speed of the entire mechanism can be monitored by the host computer 1.

[0020] Working principle: First, connect the external power supply. When the upper computer 1 receives the instruction of the signal generator 2, it commands the drive motor 4 to rotate. The drive motor 4 is connected to the speed sensor 5. The speed sensor 5 feeds back the speed of the drive motor 4 to the upper computer 1 in real time. The drive motor 4 is connected to the high-pressure fuel pump 9. The two ends of the high-pressure fuel pump 9 are connected to the first pressure gauge 8, the third temperature control gauge 26, and the first flow meter 10. The front end of the first pressure gauge 8 is connected to the low-pressure oil pump 7. The low-pressure oil pump 7 absorbs the fuel in the fuel pool 22 through the fuel inlet pipe 6. The fuel pool 22 is connected to the first ball valve 18 and the second fuel filter element 23. The low-pressure oil pump 7 transmits the fuel in the fuel pool 22 to the high-pressure fuel pump 9 through the fuel inlet pipe 6. The fuel in the fuel pool 22 is pressurized by the high-pressure fuel pump 9 and then reaches the energy storage tank 11. The energy storage tank 11 controls the pressure in the cavity through the second pressure gauge 12. When the set pressure is reached, the flow control valve 13 opens to discharge the excess fuel through the fuel return pipe 27. The fuel return pipe 27 is connected to the fuel fan 25 to cool the fuel. The fuel flows to the fuel pool 22 through the fuel return pipe 27. The fuel temperature is monitored by the second temperature control meter 17 in the fuel pool 22. When the fuel temperature is higher than the set value, the oil cooler 19 is started to control the fuel temperature within the product requirement range. The oil cooler 19 is connected to the fan 14, the first temperature control meter 15, the second flow meter 16, the second ball valve 20, and the first fuel filter element 21. When the second temperature control meter 17 in the fuel pool 22 monitors that the fuel temperature reaches the product requirement, the oil cooler 19 is closed. This structure is convenient for cooling the fuel and recycling it.

[0021] Finally, it should be noted that the above content is only used to illustrate the technical solution of the present invention, rather than to limit the scope of protection of the present invention. Simple modifications or equivalent substitutions of the technical solution of the present invention by ordinary technicians in this field do not deviate from the essence and scope of the technical solution of the present invention.

Claims

1. An aviation piston engine high pressure fuel pump test device, comprising a fuel pool (22), characterized in that: One side of the fuel pool (22) is connected to the top of the cooling oil pool via a first oil pipe, and a first temperature control meter (15) and a second flow meter (16) are provided on one side of the first oil pipe at the top of the cooling oil pool. The rear wall of the fuel pool (22) is connected to the input end of the low-pressure fuel pump (7) via one end of the fuel inlet pipe (6), and the output end of the low-pressure fuel pump (7) is connected to the input end of the high-pressure fuel pump (9) via a second oil pipe, and a first pressure gauge (8) is provided at the second oil pipe. The output end of the high-pressure fuel pump (9) is connected to one end of the energy storage tank (11) via a third oil pipe, and a first flow meter (10) is provided at the third oil pipe. A third temperature control meter (26) is provided at one end of the high-pressure fuel pump (9); the energy storage tank (11) and the fuel tank (22) are connected via a fuel return pipe (27); a drive motor (4) is provided at one side of the high-pressure fuel pump (9); a speed sensor (5) is installed at the output end of the drive motor (4); the speed sensor (5), the first pressure gauge (8) and the output end of the third temperature control meter (26) are electrically connected to the input end of the signal generator (2) via a wire; the output end of the signal generator (2) is electrically connected to the input end of the host computer (1) via a wire; and a cooling mechanism for rapid heat exchange is provided inside the cooling oil tank.

2. The high-pressure fuel pump test device for an aviation piston engine according to claim 1, characterized in that: The cooling mechanism comprises a fan (14) and an oil cooler (19); the oil cooler (19) is arranged inside the cooling oil pool, and the fan (14) is arranged at the top of the cooling oil pool.

3. The aircraft piston engine high pressure fuel pump test device according to claim 1, characterized in that: The bottom end of the fuel pool (22) is connected to one end of the cooling oil pool via an output pipe, and a second ball valve (20) and a first fuel filter element (21) are provided at one end of the fuel pool (22).

4. The aircraft piston engine high pressure fuel pump test device according to claim 1, characterized in that: A second temperature control meter (17) for monitoring the temperature of the fuel is arranged above the fuel pool (22), and a second fuel filter element (23) is arranged inside the fuel pool (22).

5. The aircraft piston engine high pressure fuel pump test device according to claim 1, characterized in that: A first ball valve (18) is provided at one end of the fuel inlet pipe (6) close to the fuel pool (22).

6. The aircraft piston engine high pressure fuel pump test device according to claim 1, characterized in that: A fuel fan (25) for cooling is provided on one side of the fuel return pipe (27), and a flow control valve (13) and a third ball valve (24) are respectively installed at both ends of the fuel return pipe (27).

7. The aircraft piston engine high pressure fuel pump test device according to claim 1, characterized in that: A second pressure gauge (12) for controlling the pressure in the cavity is provided at one end of the energy storage tank (11) away from the first flow meter (10).

8. The aircraft piston engine high pressure fuel pump test device according to claim 1, characterized in that: One end of the driving motor (4) is connected to the electric control box (3).

9. The test method of the aircraft piston engine high pressure fuel pump test device according to claim 1, characterized in that: The following steps are involved: S1, starting the low-pressure fuel pump (7) to transport the fuel in the fuel pool (22) to the input end of the high-pressure fuel pump (9); S2, starting the high-pressure fuel pump (9) to deliver the fuel pressure to the energy storage tank (11); S3, feeding back the oil pressure information to the input end of the host computer (1) through the low-pressure oil pump (7), the drive motor (4) and the first flow meter (10); S4. Checking information on the temperature, speed, and pressure of the high-pressure fuel pump (9) through the host computer (1); S5. The fuel oil flows back to the fuel oil pool (22) through the energy storage pool (11), and is cooled by the fuel oil blower (25), the oil cooler (19) and the fan (14) before being recycled.

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