A fuel system for an aircraft engine test bench

Abstract

The present invention discloses a fuel system for an aircraft engine test bench, including a fuel tank, a fuel supply pipeline, a gas supply pipeline, a fuel inlet pipeline, a pressure relief pipeline, an electric pressure regulating pipeline, a manual pressure regulating pipeline, and a tank gas pressure input pipeline. The present invention can effectively ensure the safety and stability of the fuel supply of the test bench, the accurate and timely monitoring and alarm of the fuel leakage of the system, the precise fuel flow test, and provides two fuel pressure supply modes that can be automatically controlled and switched, and can realize manual and remote adjustment of the fuel output pressure, thereby improving the applicability of the fuel system in different scenarios.

Description

Technical Field

[0001] The invention relates to the field of aviation engines, and in particular to a fuel system of an aviation engine test bench. Background Art

[0002] The fuel system is an important part of the aircraft engine test bench, and its function is to provide fuel to the engine to ensure the normal operation of the engine. The working medium of the current general aircraft engine fuel system is aviation kerosene, which is flammable and explosive. There are few methods to monitor fuel leakage in the existing fuel system fuel tank. If leakage occurs, it may cause a safety accident; at the same time, the fuel system generally uses a fuel pump or compressed air to supply fuel. If a fuel pump or compressed air fails during use, the fuel system will be unable to supply fuel; due to the large number of components in the fuel system, the current general fuel system lacks a pressure stabilizing device, which is prone to unstable output fuel pressure and flow, affecting the operation of the engine. Summary of the invention

[0003] The purpose of the present invention is to provide an aircraft engine test bench fuel system which can stably output fuel and has two fuel supply modes.

[0004] In order to achieve the above tasks, the present invention adopts the following technical solutions:

[0005] A fuel system of an aircraft engine test bench includes a fuel tank, a fuel supply pipeline, an air supply pipeline, an oil inlet pipeline, a pressure relief pipeline, an electric pressure regulating pipeline, a manual pressure regulating pipeline and a fuel tank air pressure input pipeline, wherein:

[0006] The upper part of the fuel tank is connected to the oil inlet pipeline, the pressure relief pipeline, the electric pressure regulating pipeline, the manual pressure regulating pipeline, and is provided with a tank air release valve and an electronic liquid level sensor; the fuel tank is a double-layer structure, and the calcium chloride solution is filled between the two layers; the inner tank and the outer tank are respectively provided with a flap-type liquid level sensor and a flap-type liquid level sensor; the outer wall of the fuel tank is provided with a tank interlayer air release valve connected to the interlayer between the inner and outer tanks; the lower parts of the inner tank and the outer tank are respectively provided with a tank inner layer oil release valve and a tank outer layer oil release valve;

[0007] The fuel supply pipeline is connected to the lower part of the fuel tank, and a ball valve, a fuel pump, an oil tank air pressure fuel supply electric valve, a fuel filter, a fuel supply pipeline bleed valve, a fuel filter, a pressure gauge, a pneumatic ball valve, a fuel supply pipeline pressure relief valve, a pressure gauge, a fuel supply pipeline bleed valve, a volume flow meter, an accumulator, a mass flow meter, a temperature sensor, a turbine flow meter, a temperature sensor, a fuel supply pipeline bleed valve, a drain valve, a fuel filter, a drain valve, a pressure sensor, a pressure gauge, a drain valve and a pneumatic ball valve are sequentially arranged on the fuel supply pipeline;

[0008] The end of the manual pressure regulating pipeline is connected to the oil supply pipeline between the pressure gauge and the pneumatic ball valve, and a manual back pressure regulating valve is arranged on the manual pressure regulating pipeline;

[0009] The ends of the electric pressure regulating pipeline and the pressure relief pipeline are connected to the oil supply pipeline between the pressure relief valve and the pressure gauge of the oil supply pipeline in sequence. An electric back pressure regulating valve is arranged on the electric pressure regulating pipeline, and a safety valve is arranged on the pressure relief pipeline. A fuel filter is also arranged on the oil supply pipeline between the ends of the electric pressure regulating pipeline and the pressure relief pipeline.

[0010] A pneumatic ball valve is provided on the oil inlet pipeline;

[0011] A ball valve and an air supply pressure reducing valve are arranged on the air supply pipeline in sequence; the air supply pipeline is connected to the pneumatic ball valve, and the air supply pipeline is connected to the upper part of the inner oil tank of the fuel tank through the oil tank air pressure input pipeline, and a pneumatic ball valve is installed on the oil tank air pressure input pipeline; the air supply pipeline is also connected to the pneumatic ball valve and the pneumatic ball valve.

[0012] Furthermore, ball valves are provided between the oil tank air pressure supply electric valve and the fuel filter, between the fuel filter and the fuel supply line air bleed valve, between the fuel filter and the pressure gauge, between the fuel supply line pressure relief valve and the pressure gauge, between the pressure gauge and the fuel supply line air bleed valve, between the temperature sensor and the fuel supply line air bleed valve, between the fuel filter and the oil drain valve, and between the pressure sensor and the pressure gauge.

[0013] Further, a fuel filter pressure difference sensor and a pressure difference sensor calibration three-way valve, a fuel filter pressure difference sensor and a pressure difference sensor calibration three-way valve, and a fuel filter pressure difference sensor and a pressure difference sensor calibration three-way valve are respectively arranged on the fuel filter, the fuel filter, and the fuel filter;

[0014] Furthermore, an oil receiving pan is arranged below the pressure gauge, oil supply pipeline air bleed valve, volume flow meter, accumulator, mass flow meter, temperature sensor, turbine flow meter, temperature sensor, oil supply pipeline air bleed valve, oil drain valve, fuel filter, oil drain valve, pressure sensor, pressure gauge, oil drain valve and pneumatic ball valve, an oil receiving pan liquid level alarm is arranged in the oil receiving pan, and an oil drain valve is arranged at the bottom of the oil receiving pan.

[0015] Furthermore, the outer layer of the fuel tank is equipped with an openable vertical manhole cover to facilitate daily inspection of the inner layer of the fuel tank.

[0016] Furthermore, the fuel system has two fuel supply methods, one of which is to provide fuel pressure through compressed air: an air supply reducing valve is arranged on the air supply pipeline, and the air pressure of the oil tank air pressure input pipeline can be controlled by adjusting the opening of the air supply reducing valve; a pneumatic ball valve is arranged on the oil tank air pressure input pipeline and is connected to the fuel tank, and the bottom of the fuel tank is connected to the oil supply pipeline and is equipped with an oil tank air pressure supply electric valve; when using air pressure supply, first close the ball valve, open the pneumatic ball valve to fill the fuel tank with oil, and close the pneumatic ball valve after it is filled; further, open the pneumatic ball valve and the oil tank air pressure supply valve.

[0017] Furthermore, another method of the fuel system is to provide fuel pressure through a fuel pump: the bottom of the fuel tank is connected to the fuel supply pipeline, and the fuel supply pipeline is equipped with a ball valve and a fuel pump. When the pump is used to supply fuel, the oil tank air pressure fuel supply electric valve is closed, the ball valve is opened, and the fuel pump is turned on.

[0018] Furthermore, the system generally operates in a fuel pump mode. When the fuel pump fails during operation, the compressed air fuel supply mode is immediately turned on through the control system to ensure that the engine continues to operate normally.

[0019] Furthermore, the fuel pressure output by the system can be adjusted by adjusting the opening of the manual back-pressure regulating valve according to the actual use of the fuel system; the electric pressure regulating pipeline is equipped with an electric back-pressure regulating valve, and during the test run or when it is inconvenient to manually adjust the pressure, the fuel pressure output by the system can be adjusted by remotely adjusting the opening of the electric back-pressure regulating valve through the control system.

[0020] Furthermore, the accumulator is filled with nitrogen. When the fuel pressure in the fuel supply pipeline is unstable, the accumulator absorbs and releases an appropriate amount of pressure, thereby stabilizing the pressure fluctuation of the fuel supply pipeline.

[0021] Compared with the prior art, the present invention has the following technical features:

[0022] The present invention can effectively ensure the safe and stable fuel supply of the test bench, the accurate and timely system fuel leakage monitoring and alarm, the precise fuel flow test, and provide two fuel pressure supply modes that can be automatically controlled and switched, and can realize manual and remote adjustment of the fuel output pressure, thereby improving the applicability of the fuel system in different scenarios. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0024] Explanation of the numbers in the figure: 1 air supply pressure reducing valve, 2 pneumatic ball valve, 3 flap type liquid level sensor, 4 oil tank vent valve, 5 electronic liquid level sensor, 6 oil tank interlayer vent valve, 7 flap type liquid level sensor, 8 pneumatic ball valve, 9 pressure relief pipeline, 10 electric pressure regulating pipeline, 11 manual pressure regulating pipeline, 12 oil tank air pressure input pipeline, 13 oil tank inner layer oil drain valve, 14 oil tank outer layer oil drain valve, 15 oil tank air pressure supply electric valve, 16 fuel pump, 17 fuel filter, 18 fuel filter pressure difference sensor, 19 pressure difference sensor calibration three-way valve, 20 fuel supply pipeline vent valve, 21 fuel filter pressure difference sensor, 22 pressure difference sensor calibration three-way valve, 23 fuel filter, 24 pressure gauge, 25 manual back pressure adjustment throttle valve, 26 pneumatic ball valve, 27 oil supply pipeline drain valve, 28 electric back pressure regulating valve, 29 pressure gauge, 30 oil supply pipeline bleed valve, 31 accumulator, 32 volume flow meter, 33 mass flow meter, 34 turbine flow meter, 35 temperature sensor, 36 temperature sensor, 37 oil supply pipeline bleed valve, 38 fuel filter pressure difference sensor, 39 safety valve, 40 oil drain valve, 41 fuel filter, 42 pressure difference sensor calibration three-way valve, 43 oil drain valve, 44 pressure sensor, 45 pressure gauge, 46 pneumatic ball valve, 47 oil drain valve, 48 oil receiving pan level alarm, 49 oil receiving pan, 50 oil drain valve, 51 oil supply pipeline, 52 air supply pipeline, 53 oil inlet pipeline, 54 fuel tank, 55 ball valve. DETAILED DESCRIPTION

[0025] like Figure 1 As shown, the present invention provides an aircraft engine test bench fuel system, including a fuel tank 54, a fuel supply pipeline 51, an air supply pipeline 52, an oil inlet pipeline 53, a pressure relief pipeline 9, an electric pressure regulating pipeline 10, a manual pressure regulating pipeline 11 and a tank air pressure input pipeline 12, wherein:

[0026] The upper part of the fuel tank 54 is connected to the fuel inlet pipeline 53, the pressure relief pipeline 9, the electric pressure regulating pipeline 10, and the manual pressure regulating pipeline 11, and is provided with an oil tank air release valve 4 and an electronic liquid level sensor 5; the fuel tank 54 is a double-layer structure, and the calcium chloride solution is filled between the two layers; the inner oil tank and the outer oil tank are respectively provided with a flap type liquid level sensor 7 and a flap type liquid level sensor 3; the outer wall of the fuel tank 54 is provided with an oil tank interlayer air release valve 6 connected with the interlayer between the inner and outer oil tanks; the lower parts of the inner oil tank and the outer oil tank are respectively provided with an oil tank inner layer oil release valve 13 and an oil tank outer layer oil release valve 14;

[0027] The oil supply pipeline 51 is connected to the lower part of the fuel tank 54, and the ball valve 55, the fuel pump 16, the oil tank gas pressure oil supply electric valve 15, the fuel filter 17, the oil supply pipeline bleed valve 20, the fuel filter 23, the pressure gauge 24, the pneumatic ball valve 26, the oil supply pipeline pressure relief valve 27, the pressure gauge 29, the oil supply pipeline bleed valve 30, the volume flow meter 32, the accumulator 31, the mass flow meter 33, the temperature sensor 35, the turbine flow meter 34, the temperature sensor 36, the oil supply pipeline bleed valve 37, the oil drain valve 40, the fuel filter 41, the oil drain valve 43, the pressure sensor 44, the pressure gauge 45, the oil drain valve 47 and the pneumatic ball valve 46 are arranged on the oil supply pipeline 51 in sequence; Ball valves are arranged between the fuel filter 17, between the fuel filter 17 and the fuel supply line air release valve 20, between the fuel filter 23 and the pressure gauge 24, between the fuel supply line pressure relief valve 27 and the pressure gauge 29, between the pressure gauge 29 and the fuel supply line air release valve 30, between the temperature sensor 36 and the fuel supply line air release valve 37, between the fuel filter 41 and the oil release valve 43, and between the pressure sensor 44 and the pressure gauge 45; a fuel filter pressure difference sensor 18 and a pressure difference sensor calibration three-way valve 19, a fuel filter pressure difference sensor 21 and a pressure difference sensor calibration three-way valve 22, and a fuel filter pressure difference sensor 38 and a pressure difference sensor calibration three-way valve 42 are arranged on the fuel filter 17, the fuel filter 23, and the fuel filter 41 respectively;

[0028] An oil receiving pan 49 is provided below the pressure gauge 29, the oil supply pipeline bleed valve 30, the volume flow meter 32, the accumulator 31, the mass flow meter 33, the temperature sensor 35, the turbine flow meter 34, the temperature sensor 36, the oil supply pipeline bleed valve 37, the oil drain valve 40, the fuel filter 41, the oil drain valve 43, the pressure sensor 44, the pressure gauge 45, the oil drain valve 47 and the pneumatic ball valve 46. An oil receiving pan 49 is provided with an oil receiving pan liquid level alarm 48, and an oil drain valve 50 is provided at the bottom of the oil receiving pan 49;

[0029] The end of the manual pressure regulating pipeline 11 is connected to the oil supply pipeline 51 between the pressure gauge 24 and the pneumatic ball valve 26, and a manual back pressure regulating valve 25 is provided on the manual pressure regulating pipeline 11;

[0030] The ends of the electric pressure regulating pipeline 10 and the pressure relief pipeline 9 are connected to the oil supply pipeline 51 between the oil supply pipeline pressure relief valve 27 and the pressure gauge 29 in sequence. The electric back pressure regulating valve 28 is arranged on the electric pressure regulating pipeline 10, and the safety valve 39 is arranged on the pressure relief pipeline 9. A fuel filter is also arranged on the oil supply pipeline 51 between the ends of the electric pressure regulating pipeline 10 and the pressure relief pipeline 9.

[0031] A pneumatic ball valve 2 is provided on the oil inlet pipeline 53;

[0032] A ball valve and an air supply pressure reducing valve 1 are arranged on the air supply pipeline 52 in sequence; the air supply pipeline 53 is connected to the pneumatic ball valve 2, and the air supply pipeline 53 is connected to the upper part of the inner oil tank of the fuel tank 54 through the oil tank air pressure input pipeline 12, and a pneumatic ball valve 8 is installed on the oil tank air pressure input pipeline 12; the air supply pipeline 52 is also connected to the pneumatic ball valve 26 and the pneumatic ball valve 46.

[0033] The system is equipped with pneumatic ball valves 2, 26, and 46 to improve the valve switching response speed and working stability. The upper part of the fuel tank 54 is connected to the oil inlet pipeline 53 to fill the fuel tank 54 with oil. The fuel tank 54 is a double-layer oil tank design, and calcium chloride solution is filled between the two layers. It is monitored by the liquid level sensor 3. If the liquid level rises above the warning value, an alarm is issued to realize the oil tank leakage alarm function. The inner layer of the oil tank is equipped with a liquid level sensor 7 to monitor the fuel storage volume in the fuel tank 54. The outer layer of the fuel tank is equipped with a vent valve 6 and an oil drain valve 14, and the inner layer is equipped with a vent valve 4 and an oil drain valve 13, which are used for decompression, degassing and oil discharge during the operation of the fuel tank 54. The outer layer of the fuel tank 54 is equipped with an openable vertical manhole cover to facilitate daily inspection of the inner layer of the fuel tank 54. The top of the fuel tank 54 is connected to the oil tank air pressure input pipeline 12, and the bottom is connected to the oil supply pipeline 51. One end of the fuel pump 16 is connected to the fuel tank 54, and the other end is connected to the fuel supply pipeline 51. The system can provide fuel pressure to the fuel supply pipeline 51 by compressed air and pump.

[0034] The fuel system has two fuel supply modes. One mode is to provide fuel pressure through compressed air. The specific implementation method is as follows: the air supply pressure reducing valve 1 is arranged on the air supply pipeline 52, and the air pressure of the oil tank air pressure input pipeline 12 can be controlled by adjusting the opening of the air supply pressure reducing valve 1. The oil tank air pressure input pipeline 12 is equipped with a pneumatic ball valve 8 and connected to the fuel tank 54. The lower part of the fuel tank 54 is connected to the oil supply pipeline 51 and equipped with an oil tank air pressure oil supply electric valve 15. When using air pressure oil supply, first close the ball valve 55, open the pneumatic ball valve 2 to fill the fuel tank 54 with oil, and close the pneumatic ball valve 2 after filling. Further, open the pneumatic ball valve 8 and the oil tank air pressure oil supply valve 15. Another way is to provide fuel pressure through a fuel pump, and the specific implementation method is as follows: the bottom of the fuel tank 54 is connected to the fuel supply pipeline 51, and the fuel supply pipeline 51 is equipped with a ball valve 55 and a fuel pump 16. When the pump is used to supply fuel, the oil tank air pressure fuel supply electric valve 15 is closed, the ball valve 55 is opened, and the fuel pump 16 is turned on. The system generally works in the fuel pump mode. When the fuel pump fails during operation, the compressed air supply is immediately turned on through the control system to ensure that the engine continues to operate normally.

[0035] The manual pressure regulating pipeline 11 is connected to the fuel supply pipeline 51 at one end and to the fuel tank 54 at the other end. It is equipped with a manual back pressure regulating valve 25. The fuel pressure outputted by the system can be regulated by adjusting the opening of the manual back pressure regulating valve 25 according to the actual use of the fuel system. The electric pressure regulating pipeline 10 is connected to the fuel supply pipeline 51 at one end and to the fuel tank 54 at the other end. It is equipped with an electric back pressure regulating valve 28. During the test run or when it is inconvenient to manually adjust the pressure, the opening of the electric back pressure regulating valve 28 can be remotely adjusted by the control system to adjust the fuel pressure outputted by the system. The pressure relief pipeline 9 is connected to the fuel supply pipeline 51 at one end and to the fuel tank 54 at the other end. It is equipped with a safety valve 39 to realize the over-pressure oil relief function. When the fuel supply pipeline 51 is blocked and the fuel pressure exceeds the standard, the safety valve 39 opens immediately after exceeding the threshold value, and the fuel in the fuel supply pipeline 51 returns to the fuel tank 54. After the fuel pressure returns to the normal working value, the safety valve 39 closes and the system operates normally.

[0036] The oil supply pipeline 51 is provided with fuel filters 17, 23, 41, and the fuel filter inlet and outlet are provided with differential pressure sensors 18, 21, 38 to monitor the oil filter blockage. If the oil filter is blocked, an alarm is immediately given. The rear end of the differential pressure sensor is provided with a three-way ball valve 19, 22, 42 for online calibration of the differential pressure sensor.

[0037] A volume flow meter 32, a mass flow meter 33, and a turbine flow meter 34 are provided on the oil supply pipeline 51 to measure and record the fuel flow. The volume flow meter 32 is used to record the cumulative fuel flow of the fuel system, and the mass flow meter 33 and the turbine flow meter 34 are used to measure the fuel flow of the system and compare the measurement parameters to ensure the accuracy of the flow measurement data.

[0038] An accumulator 31 is provided between the mass flowmeter 33 and the turbine flowmeter 34 . The accumulator 31 is filled with nitrogen. When the fuel pressure in the fuel supply pipeline 51 is unstable, the accumulator absorbs and releases an appropriate amount of pressure to stabilize the pressure fluctuation of the fuel supply pipeline 51 .

[0039] The fuel supply pipeline 51 is equipped with three pressure gauges 24, 29, 45, one pressure sensor 44, and two temperature sensors 35, 36 for accurate measurement of fuel pressure and temperature. The front end of the pressure sensor 44 is equipped with a three-way ball valve for online calibration of the pressure sensor. Valves are separately provided in front of the three pressure gauges 24, 29, 45, one pressure sensor 44, and two temperature sensors 35, 36 to facilitate disassembly and inspection of the instruments.

[0040] The oil supply pipeline 51 is equipped with air release valves 20, 30, 37 and oil drain valves 27, 40, 43, 47, which are used to release air and oil from different parts of the system. When a part of the system pipeline needs to be disassembled or replaced, it can be released through the air release valve and oil drain valve, and disassembled and assembled after the pipeline is emptied.

[0041] The bottom of the fuel system is equipped with an oil receiving pan 49, and the oil receiving pan is equipped with a liquid level sensor 48 for monitoring leaked fuel. At the same time, the oil receiving pan 49 is equipped with an oil drain valve 50 to discharge the remaining oil in the oil receiving pan 49.

[0042] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, a person skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the protection scope of the present application.

Claims

1. An aircraft engine test bench fuel system, characterized in that: It comprises a fuel tank (54), a fuel supply pipeline (51), a gas supply pipeline (52), a fuel inlet pipeline (53), a pressure relief pipeline (9), an electric pressure regulating pipeline (10), a manual pressure regulating pipeline (11) and a fuel tank gas pressure input pipeline (12), wherein: The upper part of the fuel tank (54) is connected to an oil inlet pipeline (53), a pressure relief pipeline (9), an electric pressure regulating pipeline (10), and a manual pressure regulating pipeline (11), and is provided with an oil tank air release valve (4) and an electronic liquid level sensor (5); the fuel tank (54) is a double-layer structure, and a calcium chloride solution is filled between the two layers; a second flap type liquid level sensor (7) and a first flap type liquid level sensor (3) are respectively provided on the inner layer oil tank and the outer layer oil tank; an oil tank interlayer air release valve (6) communicating with the interlayer between the inner layer oil tank and the outer layer oil tank is provided on the outer wall of the fuel tank (54); an oil tank inner layer oil release valve (13) and an oil tank outer layer oil release valve (14) are respectively provided at the lower parts of the inner layer oil tank and the outer layer oil tank; The oil supply pipeline (51) is connected to the lower part of the fuel tank (54), and a ball valve (55), a fuel pump (16), an oil tank air pressure oil supply electric valve (15), a first fuel filter (17), a first oil supply pipeline air release valve (20), a second fuel filter (23), a first pressure gauge (24), a third pneumatic ball valve (26), an oil supply pipeline pressure relief valve (27), a second pressure gauge (29), a second oil supply pipeline air release valve (30), a volume flow meter (32), an accumulator (31), a mass flow meter (33), a first temperature sensor (35), a turbine flow meter (34), a second temperature sensor (36), a third oil supply pipeline air release valve (37), a first oil drain valve (40), a third fuel filter (41), a second oil drain valve (43), a pressure sensor (44), a third pressure gauge (45), a third oil drain valve (47) and a fourth pneumatic ball valve (46) are sequentially arranged on the oil supply pipeline (51); The end of the manual pressure regulating pipeline (11) is connected to the oil supply pipeline (51) between the first pressure gauge (24) and the third pneumatic ball valve (26), and a manual back pressure regulating valve (25) is provided on the manual pressure regulating pipeline (11); The ends of the electric pressure regulating pipeline (10) and the ends of the pressure relief pipeline (9) are sequentially connected to the oil supply pipeline (51) between the oil supply pipeline pressure relief valve (27) and the second pressure gauge (29); an electric back pressure regulating valve (28) is arranged on the electric pressure regulating pipeline (10), and a safety valve (39) is arranged on the pressure relief pipeline (9); a fuel filter is also arranged on the oil supply pipeline (51) between the ends of the electric pressure regulating pipeline (10) and the ends of the pressure relief pipeline (9); A first pneumatic ball valve (2) is provided on the oil inlet pipeline (53); A ball valve and an air supply pressure reducing valve (1) are sequentially arranged on the air supply pipeline (52); the air supply pipeline (52) is connected to a first pneumatic ball valve (2); the air supply pipeline (52) is connected to the upper part of the inner oil tank of the fuel tank (54) through an oil tank air pressure input pipeline (12); a second pneumatic ball valve (8) is installed on the oil tank air pressure input pipeline (12); the air supply pipeline (52) is also connected to a third pneumatic ball valve (26) and a fourth pneumatic ball valve (46); The fuel system has two fuel supply modes. One mode is to provide fuel pressure through compressed air: an air supply pressure reducing valve (1) is arranged on the air supply pipeline (52), and the air pressure of the oil tank air pressure input pipeline (12) can be controlled by adjusting the opening of the air supply pressure reducing valve (1); a second pneumatic ball valve (8) is arranged on the oil tank air pressure input pipeline (12) and is connected to the fuel tank (54); the lower part of the fuel tank (54) is connected to the oil supply pipeline (51) and is equipped with an oil tank air pressure oil supply electric valve (15); when using air pressure oil supply, first close the ball valve (55), open the first pneumatic ball valve (2) to fill the fuel tank (54), and close the first pneumatic ball valve (2) after filling; further, open the second pneumatic ball valve (8) and the oil tank air pressure oil supply electric valve (15); Another method of the fuel system is to provide fuel pressure through a fuel pump: the bottom of the fuel tank (54) is connected to the fuel supply pipeline (51), and the fuel supply pipeline (51) is equipped with a ball valve (55) and a fuel pump (16). When the pump is used to supply fuel, the oil tank air pressure fuel supply electric valve (15) is closed, the ball valve (55) is opened, and the fuel pump (16) is turned on.

2. The aircraft engine test bench fuel system according to claim 1, characterized in that: Ball valves are provided between the oil tank gas pressure oil supply electric valve (15) and the first fuel filter (17), between the first fuel filter (17) and the first fuel supply pipeline air release valve (20), between the second fuel filter (23) and the first pressure gauge (24), between the fuel supply pipeline pressure relief valve (27) and the second pressure gauge (29), between the second pressure gauge (29) and the second fuel supply pipeline air release valve (30), between the second temperature sensor (36) and the third fuel supply pipeline air release valve (37), between the third fuel filter (41) and the second oil release valve (43), and between the pressure sensor (44) and the third pressure gauge (45).

3. The aircraft engine test bench fuel system according to claim 1, characterized in that: A first fuel filter differential pressure sensor (18) and a first differential pressure sensor calibration three-way valve (19), a second fuel filter differential pressure sensor (21) and a second differential pressure sensor calibration three-way valve (22), and a third fuel filter differential pressure sensor (38) and a third differential pressure sensor calibration three-way valve (42) are respectively arranged on the first fuel filter (17), the second fuel filter (23), and the third fuel filter (41).

4. The aircraft engine test bench fuel system according to claim 1, characterized in that: An oil receiving pan (49) is arranged below the second pressure gauge (29), the second oil supply pipeline venting valve (30), the volume flow meter (32), the accumulator (31), the mass flow meter (33), the first temperature sensor (35), the turbine flow meter (34), the second temperature sensor (36), the third oil supply pipeline venting valve (37), the first oil drain valve (40), the third fuel filter (41), the second oil drain valve (43), the pressure sensor (44), the third pressure gauge (45), the third oil drain valve (47) and the fourth pneumatic ball valve (46); an oil receiving pan liquid level alarm (48) is arranged in the oil receiving pan (49); and a fourth oil drain valve (50) is arranged at the bottom of the oil receiving pan (49).

5. The aircraft engine test bench fuel system according to claim 1, characterized in that: The outer layer of the fuel tank (54) is equipped with an openable vertical manhole cover, which facilitates daily inspection of the inner layer of the fuel tank (54).

6. The aircraft engine test bench fuel system according to claim 1, characterized in that: The system works in a fuel pump mode. When the fuel pump (16) fails during operation, the control system immediately starts the compressed air fuel supply mode to ensure that the engine continues to operate normally.

7. The aircraft engine test bench fuel system according to claim 1, characterized in that: The fuel pressure output by the system can be adjusted by adjusting the opening of a manual back pressure regulating valve (25) according to the actual use of the fuel system; the electric back pressure regulating pipeline (10) is equipped with an electric back pressure regulating valve (28), and during the test run or when it is inconvenient to manually adjust the pressure, the control system remotely adjusts the opening of the electric back pressure regulating valve (28) to adjust the fuel pressure output by the system.

8. The aircraft engine test bench fuel system according to claim 1, characterized in that: The accumulator (31) is filled with nitrogen. When the fuel pressure in the fuel supply pipeline (51) is unstable, the accumulator absorbs and releases an appropriate amount of pressure, thereby stabilizing the pressure fluctuation of the fuel supply pipeline (51).

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