Civil aircraft airborne fuel oil accessory test system and test board applying civil aircraft airborne fuel oil accessory test system

Abstract

The utility model discloses a civil aircraft airborne fuel accessory test system and a testboard applying the same, comprising a nitrogen source, an air outlet of the nitrogen source is connected with an air inlet of a pressure cylinder, an air outlet of the pressure cylinder is connected with an air inlet of an oil storage tank, an oil outlet of the oil storage tank is connected with two first test ports, and an air outlet of the oil storage tank is connected with two second test ports. According to the utility model, the nitrogen source is used for supplying pressure, and the pressure in the oil storage tank is increased to the test pressure through the pressure cylinder, so that the investment of a fuel pump station is reduced, the pressure in the oil storage tank is increased to the test pressure through the pressure cylinder, the test efficiency is improved, and the test cost is reduced. The possibility that fuel oil burns and is on fire when the pump station motor works is avoided, and the safety and the reliability of the test system are effectively improved.

Description

Technical Field

[0001] The utility model relates to the technical field of fuel accessory testing, in particular to a fuel accessory testing system onboard a civil aircraft. Background Art

[0002] The function of the aircraft fuel system is to store fuel and ensure that it can continuously supply fuel to the engine at the pressure and flow rate required by the engine under any specified conditions (such as various flight altitudes and flight attitudes). In addition, the fuel system can also complete additional functions such as cooling other systems on the aircraft, balancing the aircraft, and keeping the center of gravity of the aircraft within the specified range. Due to the importance of the fuel system to the aircraft, the fuel system is required to be reliable, long-lasting, fire-safe, simple in structure, easy to maintain and repair, and precisely controlled.

[0003] Most modern civil aircraft fuel accessory test systems are imported from foreign fuel accessory manufacturers, with a single test function (one test system can only test one part number or one category of components from the manufacturer), resulting in a large waste of duplicate investment; the test system requires a fuel pump station to work, which, in addition to the high investment price, is not very safe because the fuel has an extremely low ignition point and the pump station requires an electric pump to drive the pressurization; in addition, for flow testing, foreign imported equipment mostly uses flow meter readings, which have large reading errors and cannot achieve flow integration, making the test operation extremely inconvenient. Utility Model Content

[0004] In order to solve the above technical problems, the utility model provides a civil aircraft onboard fuel accessory testing system, including a nitrogen source, wherein an outlet of the nitrogen source is connected to an air inlet of a booster cylinder, an outlet of the booster cylinder is connected to an air inlet of an oil storage tank, an oil outlet of the oil storage tank is connected to two first test ports, and another oil outlet of the oil storage tank is connected to two second test ports.

[0005] Preferably, a pressure reducing valve and a one-way valve are provided on a pipeline connecting the gas outlet of the nitrogen source and a gas inlet of the booster cylinder.

[0006] Preferably, an air release valve is provided on the pipeline connecting the air outlet of the boosting cylinder and the air inlet of the oil storage tank.

[0007] Preferably, a flow meter is provided on a pipeline connecting an oil outlet of the oil storage tank and the two first test ports.

[0008] Preferably, a first pressure gauge and a second pressure gauge are provided on a pipeline connecting the other oil outlet of the oil storage tank and the two second test ports.

[0009] Preferably: a second isolation valve is provided on the pipeline connected to the first pressure gauge.

[0010] Preferably: a third isolation valve is provided on the pipeline connected to the second pressure gauge.

[0011] Preferably, a first isolation valve is provided on each pipeline connected to the first test port.

[0012] Preferably: a fourth isolation valve is provided on the pipeline connected to the second test port.

[0013] A test bench comprises a test bench body, the test system is installed on the test bench body, and the fuel accessories are tested through the test bench body.

[0014] Technical effects and advantages of the utility model:

[0015] In the utility model, the pressure in the oil storage tank is increased to the test pressure by the nitrogen source through the booster cylinder, which reduces the investment in the fuel pump station, avoids the possibility of fuel combustion and fire when the pump station motor is working, and effectively improves the safety and reliability of the test system. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the structure of a civil aircraft onboard fuel accessories testing system provided in an embodiment of the present application;

[0017] Figure 2 It is a structural schematic diagram of a test bench applied to a civil aircraft onboard fuel accessories test system provided in an embodiment of the present application.

[0018] In the figure: 1. nitrogen source; 2. booster cylinder; 21. temperature sensor; 3. oil storage tank; 31. air filter; 4. first test port; 5. second test port; 6. pressure reducing valve; 7. one-way valve; 8. vent valve; 9. refueling valve; 10. flow meter; 11. first isolation valve; 12. second isolation valve; 13. first pressure gauge; 14. third isolation valve; 15. second pressure gauge; 16. fourth isolation valve; 17. test bench body. DETAILED DESCRIPTION

[0019] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments of the present invention are provided for the purpose of illustration and description, and are not intended to be exhaustive or to limit the present invention to the disclosed forms. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are selected and described in order to better illustrate the principles and practical applications of the present invention, and to enable those of ordinary skill in the art to understand the present invention and thereby design various embodiments with various modifications suitable for specific purposes.

[0020] See also Figures 1-2In this embodiment, a civil aircraft onboard fuel accessory test system is provided, including a nitrogen source 1, wherein an outlet of the nitrogen source 1 is connected to an inlet of a boosting cylinder 2, an outlet of the boosting cylinder 2 is connected to an inlet of an oil storage tank 3, an outlet of the oil storage tank 3 is connected to at least one first test port 4, and another outlet of the oil storage tank 3 is connected to at least one second test port 5. The test bench does not require a fuel pump station to supply oil and boost pressure. The pressure is supplied by the nitrogen source 1, and the pressure in the oil storage tank 3 is boosted to the test pressure through the boosting cylinder 2, thereby reducing the investment in the fuel pump station, avoiding the possibility of fuel combustion and fire when the pump station motor is working, and effectively improving the safety and reliability of the test system.

[0021] Specifically, a nitrogen gas bottle is used as the nitrogen gas source 1, and the nitrogen gas bottle supplies pressure.

[0022] The following is a specific description using two first test ports 4 and two second test ports 5 as an example:

[0023] In this embodiment, a pressure reducing valve 6 and a one-way valve 7 are provided on the pipeline connecting the air outlet of the nitrogen source 1 and an air inlet of the boosting cylinder 2, a venting valve 8 is provided on the pipeline connecting the air outlet of the boosting cylinder 2 and the air inlet of the oil storage tank 3, a flow meter 10 is provided on the pipeline connecting an oil outlet of the oil storage tank 3 and two first test ports 4, the flow meter 10 is connected to a flow integrator, and the fuel flow is monitored by the flow meter 10 and the flow integrator, and a first isolation valve 11 is provided on the pipeline connected to each first test port 4, and each first isolation valve 11 controls the opening and closing of the first test port 4 connected thereto.

[0024] Specifically, the pressure adjustment range of the pressure reducing valve is generally between 0 MPa and 10 MPa.

[0025] Specifically, the flow test is performed by the flow meter 10 and the flow integrator to monitor the real-time flow and the total flow value. The flow meter 10 monitors the flow rate of 0.6 to 60 L / Min, which covers the test capability requirements of most civil aviation aircraft fuel accessories. The data recording is reliable and convenient, and the error in reading is avoided.

[0026] In this embodiment, a first pressure gauge 13 and a second pressure gauge 15 are provided on a pipeline connecting the other oil outlet of the oil storage tank 3 and the two second test ports 5, and a second isolation valve 12 is provided on the pipeline connected to the first pressure gauge 13, a third isolation valve 14 is provided on the pipeline connected to the second pressure gauge 15, and a fourth isolation valve 16 is provided on the pipeline connected to each second test port 5. Each fourth isolation valve 16 controls the opening and closing of the second test port 5 connected thereto, and is used to monitor the fuel pressure of the second test port 5 through the first pressure gauge 13 and the second pressure gauge 15.

[0027] Specifically, the measuring range of the first pressure gauge 13 is 0-230 PSI, and the measuring range of the second pressure gauge 15 is 0-1450 PSI.

[0028] In this embodiment, the oil inlet of the oil storage tank 3 passes through the oil outlet of the booster cylinder 2 through a pipeline, and a refueling valve 9 is provided on the pipeline connecting the oil inlet of the oil storage tank 3 and the oil outlet of the booster cylinder 2 .

[0029] In this embodiment, a temperature sensor 21 is provided on the boost cylinder 2 , and the temperature of the fuel in the boost cylinder 2 is detected by the temperature sensor 21 .

[0030] In this embodiment, the oil storage tank 3 is also connected to an air filter 31 through a pipeline, and the fuel volatile gas in the oil storage tank 3 is discharged into the air after passing through the air filter 31.

[0031] In this embodiment, a test bench body 17 is further included, and the above-mentioned test system is installed on the test bench body 17, and the fuel accessories are tested through the test bench body 17.

[0032] The working principle of the utility model is:

[0033] After connecting both ends of the fuel accessory to the first test port 4, open the vent valve 8 and a first isolation valve 11, close the refueling valve 9, the second isolation valve 12, the third isolation valve 14 and each fourth isolation valve 16, and adjust the pressure reducing valve 6 through the pressure reducing valve 6, the check valve 7 and the booster cylinder 2 to increase the pressure in the fuel storage tank 3 to the test pressure. The flow rate is monitored by the flow meter 10 to test the fuel accessory. After the test is completed, close all valves;

[0034] After connecting both ends of the fuel accessory to the second test port 5, open the vent valve 8, a fourth isolation valve 16 and the second isolation valve 12, close the refueling valve 9, each of the first isolation valves 11 and the third isolation valve 14, adjust the pressure reducing valve 6, increase the pressure in the fuel storage tank 3 to the test pressure, and monitor the pressure through the first pressure gauge 13 to test the fuel accessory. Monitoring the fuel accessory under low pressure can improve the test accuracy. After the test is completed, close all valves;

[0035] After connecting both ends of the fuel accessory to the second test port 5, open the vent valve 8, a fourth isolation valve 16 and the third isolation valve 14, close the refueling valve 9, each of the first isolation valve 11 and the second isolation valve 12, adjust the pressure reducing valve 6, increase the pressure in the fuel storage tank 3 to the test pressure, and monitor the pressure through the second pressure gauge 15 to test the fuel accessory and monitor the fuel accessory under high pressure.

[0036] Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field and related fields without creative work should fall within the scope of protection of the present invention. Structures, devices and operating methods not specifically described and explained in the present invention shall be implemented according to conventional means in the field unless otherwise specified and limited.

Claims

1. A civil aircraft fuel accessory test system, characterized in that: The invention comprises a nitrogen source (1), wherein the gas outlet of the nitrogen source (1) is connected to an gas inlet of a boosting cylinder (2), the gas outlet of the boosting cylinder (2) is connected to an gas inlet of an oil storage tank (3), an oil outlet of the oil storage tank (3) is connected to two first test ports (4), and another oil outlet of the oil storage tank (3) is connected to two second test ports (5).

2. The test system according to claim 1, characterized in that: A pressure reducing valve (6) and a one-way valve (7) are provided on a pipeline connecting the gas outlet of the nitrogen source (1) and a gas inlet of the booster cylinder (2).

3. The test system according to claim 2, characterized in that: An air release valve (8) is provided on a pipeline connecting the air outlet of the boosting cylinder (2) and the air inlet of the oil storage tank (3).

4. The test system according to claim 3, characterized in that: A flow meter (10) is provided on a pipeline connecting an oil outlet of the oil storage tank (3) and two first test ports (4).

5. The test system according to claim 4, characterized in that: A first pressure gauge (13) and a second pressure gauge (15) are provided on a pipeline connecting the other oil outlet of the oil storage tank (3) and the two second test ports (5).

6. The test system according to claim 5, characterized in that: A first isolation valve (11) is provided on the pipeline connected to the first test port (4).

7. The test system according to claim 6, characterized in that: A second isolation valve (12) is provided on the pipeline connected to the first pressure gauge (13).

8. The test system according to claim 7, characterized in that: A third isolation valve (14) is provided on the pipeline connected to the second pressure gauge (15).

9. The test system according to claim 8, characterized in that: A fourth isolation valve (16) is provided on the pipeline connected to the second test port (5).

10. A test bench, characterized in that: It comprises a test bench body (17), on which the test system according to any one of claims 1 to 9 is installed, and the fuel accessories are tested through the test bench body (17).

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