Driving device special for aircraft engine fuel oil

Abstract

The utility model discloses a driving device special for aircraft engine fuel oil, and belongs to the technical field of aircraft engine testing equipment, hydraulic oil supply systems and control thereof. The driving device comprises an electric cabinet, an electric heating oil tank is fixedly installed in the electric cabinet, the top of the electric heating oil tank is fixedly connected with an oil inlet pipe, and the top of the oil inlet pipe penetrates through the top end of the electric heating oil tank; a motor pump set is fixedly installed in the electric control box, the extraction end of the motor pump set is connected with an internal pipeline of the electric heating oil tank, an oil conveying straight pipe is fixedly installed at the oil discharging end of the motor pump set, a tee joint is fixedly installed at the end, away from the motor pump set, of the oil conveying straight pipe, and an electric control valve is fixedly installed in the tee joint. Oil conveying hoses are fixedly installed at the two ends of the tee joint, and penetrating grooves matched with the two sets of oil conveying hoses are formed in the side wall of the electric control box. According to the invention, the supply pressure, flow and direction of the fuel can be quickly and accurately adjusted, so that the efficiency and accuracy of aircraft engine testing work are improved.

Description

Technical Field

[0001] This application relates to the fields of aircraft engine testing equipment, hydraulic oil supply systems and their control technologies, and in particular to a dedicated fuel drive device for aircraft engines. Background Technology

[0002] In the production and testing of aircraft engines, in order to ensure the performance and safety of the engines in actual use, it is necessary to simulate the fuel supply process of various fuels in actual use through an external fuel supply device.

[0003] Traditional aircraft engine fuel supply systems primarily adjust fuel supply parameters manually or through basic automated systems. However, the adjustment speed is slow and precise control is difficult to achieve, which affects testing efficiency and accuracy, hindering the improvement of efficiency and accuracy in aircraft engine testing. Utility Model Content

[0004] To address the shortcomings of existing technologies, this application provides a dedicated fuel drive device for aircraft engines, which overcomes the deficiencies of existing technologies. It aims to solve the problem that traditional dedicated fuel supply devices for aircraft engines mainly adjust fuel supply parameters manually or through basic automated systems, but the adjustment speed is slow and it is difficult to achieve precise control, which affects testing efficiency and accuracy and is not conducive to improving the efficiency and accuracy of aircraft engine testing.

[0005] To achieve the above objectives, this application provides the following technical solution: a dedicated fuel drive device for aircraft engines, comprising an electrical control box, an electric heating oil tank fixedly installed inside the electrical control box, an oil inlet pipe fixedly connected to the top of the electric heating oil tank, the top of the oil inlet pipe passing through the top of the electric heating oil tank, a motor pump assembly fixedly installed inside the electrical control box, the extraction end of the motor pump assembly connected to the internal pipe of the electric heating oil tank, a straight oil delivery pipe fixedly installed at the oil discharge end of the motor pump assembly, a tee head fixedly installed at the end of the straight oil delivery pipe away from the motor pump assembly, an electrically controlled valve fixedly installed inside the tee head, and oil delivery hoses fixedly installed at both ends of the tee head, a through groove matching the two sets of oil delivery hoses opened on the side wall of the electrical control box, a pressure sensor fixedly installed on the outer wall of the straight oil delivery pipe, a controller fixedly installed on the top of the electrical control box, the electrically controlled valve and the pressure sensor being signal-connected to the controller, and control buttons provided on the top of the controller.

[0006] By adopting the above technical solution, the electrical control box is moved to a suitable position next to the aircraft, and the two sets of fuel delivery hoses of the fuel pump truck are pulled out to a suitable length and connected to the two sets of fuel delivery hoses with a connecting joint. Fuel is added to the electric heating fuel tank through the fuel inlet pipe, and the fuel in the electric heating fuel tank is drawn out into the fuel delivery straight pipe by the motor pump unit. A pressure sensor is used to monitor the fuel supply pressure and flow rate in real time and transmit the data to the controller. The pressure sensor is a JN-JLZCYZL type flow and pressure monitoring device. According to the preset instructions of the controller, the opening of the electronic control valve is controlled, thereby controlling the fuel flow rate and the direction of the flow to the appropriate fuel delivery hose. This device can quickly and accurately adjust the fuel supply pressure, flow rate and direction, thereby improving the efficiency and accuracy of aircraft engine testing.

[0007] As a preferred technical solution of this application, the bottom of the electrical control box is rotatably connected to four sets of omnidirectional casters, the four sets of omnidirectional casters are respectively located at the four corners of the electrical control box, and a push handle is fixedly installed on one side of the electrical control box.

[0008] By adopting the above technical solution, the electrical control box can be moved by swivel casters, and the push handle provides a hand point of action when pushing the electrical control box, thus making it easier to move the electrical control box with less effort.

[0009] As a preferred technical solution of this application, a manual pump is provided on one side of the electric heating oil tank, the extraction end of the manual pump is connected to the internal pipe of the electric heating oil tank, a connecting branch pipe is fixedly connected to one side of the oil delivery straight pipe, and the oil discharge end of the manual pump is fixedly installed to the connecting branch pipe.

[0010] By adopting the above technical solution, when the motor pump unit fails, fuel can be manually extracted by a manual pump. The manual pump and the fuel delivery line are connected by a connecting branch pipe, which meets the testing requirements and helps to ensure the continuity of the test.

[0011] As a preferred technical solution of this application, four sets of hoisting earrings are fixedly installed on the top of the electrical control box.

[0012] By adopting the above technical solution, the electrical control box can be easily moved and installed using hoisting equipment through four sets of hoisting lugs.

[0013] As a preferred technical solution of this application, a backup power supply is fixedly installed inside the electrical control box, and the backup power supply is a 115V / 400Hz power supply.

[0014] By adopting the above technical solution, a backup power supply is provided for the electrical control box and other components that require power, ensuring that testing can be carried out even in the event of a power outage.

[0015] As a preferred technical solution of this application, a filter frame is threadedly connected to the top of the oil inlet pipe, a coarse filter screen is fixedly installed inside the filter frame, a fine filter screen is fixedly installed inside the filter frame below the coarse filter screen, and an oil pipe cap is threadedly connected to the top of the filter frame.

[0016] By adopting the above technical solution, a coarse filter screen is used to filter coarse impurities in the fuel, and a fine filter screen is used to filter fine impurities in the fuel, which helps to improve the purity of the fuel. At the same time, the filter frame is connected to the fuel inlet pipe by threads, which facilitates the disassembly and cleaning of the filter frame. The fuel pipe cap prevents impurities from falling into the electric heating fuel tank from the fuel inlet pipe, further ensuring the purity of the fuel.

[0017] As a preferred technical solution of this application, a liquid level sensor is fixedly installed inside the electric heating oil tank, and a temperature monitor is fixedly installed inside the electric heating oil tank above the liquid level sensor. Both the liquid level sensor and the temperature monitor are connected to the controller signal.

[0018] By adopting the above technical solution, the liquid level in the fuel tank is monitored in real time by a liquid level sensor, the temperature in the fuel tank is monitored in real time by a temperature monitor, and the temperature of the electric heating fuel tank is adjusted by a controller, which helps to ensure the safe use of fuel.

[0019] As a preferred embodiment of this application, a warning light is fixedly installed on the top of the controller, and the warning light is electrically connected to the controller.

[0020] By adopting the above technical solution, when the controller receives abnormal conditions detected by each component, it will issue a warning signal through the warning light, which helps to promptly remind the operator to pay attention.

[0021] The beneficial effects of this application are:

[0022] 1. Move the electrical control box to a suitable location next to the aircraft. Extend the two sets of fuel hoses on the fuel pump truck to a suitable length and connect them to the two sets of fuel hoses using the coupling connectors. Add fuel to the electric heating fuel tank through the fuel inlet pipe. The electric pump unit draws the fuel from the electric heating fuel tank into the fuel straight pipe. A pressure sensor is used to monitor the fuel supply pressure and flow rate in real time and transmits the data to the controller. The pressure sensor is a JN-JLZCYZL type flow and pressure monitoring device. According to the preset instructions of the controller, the opening of the electronic control valve is controlled, thereby controlling the fuel flow rate and the direction of the flow to the appropriate fuel hose. This device can quickly and accurately adjust the fuel supply pressure, flow rate and direction, thereby improving the efficiency and accuracy of aircraft engine testing.

[0023] 2. The control box is moved by using swivel casters, and the push handle provides a hand point of action when pushing the control box, thus making it easier to move the control box with less effort. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall structure of this application;

[0025] Figure 2 This is a schematic diagram of the oil delivery structure of an electric heating oil tank;

[0026] Figure 3 for Figure 2 Enlarged front view of the structure at point A in the middle;

[0027] Figure 4 This is a side view structural diagram of this application.

[0028] In the diagram: 1. Electrical control box; 2. Electric heating oil tank; 3. Oil inlet pipe; 4. Oil pipe cap; 5. Motor pump set; 6. Oil delivery straight pipe; 7. T-joint; 8. Electrically controlled valve; 9. Oil delivery hose; 10. Through groove; 11. Controller; 12. Control buttons; 14. Pressure sensor; 15. Manual pump; 16. Connecting branch pipe; 17. Universal casters; 18. Push handle; 19. Reserve power supply; 20. Lifting lugs; 21. Filter rack; 22. Coarse filter screen; 23. Fine filter screen; 24. Liquid level sensor; 25. Temperature monitor; 26. Warning light. Detailed Implementation

[0029] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0030] Reference Figure 1-4A dedicated fuel drive device for aircraft engines includes an electrical control box 1. An electric heating oil tank 2 is fixedly installed inside the electrical control box 1. An oil inlet pipe 3 is fixedly connected to the top of the electric heating oil tank 2, with the top of the oil inlet pipe 3 passing through the top of the electric heating oil tank 2. A motor pump assembly 5 is fixedly installed inside the electrical control box 1. The extraction end of the motor pump assembly 5 is connected to an internal pipe in the electric heating oil tank 2. A straight oil delivery pipe 6 is fixedly installed at the oil discharge end of the motor pump assembly 5. A T-joint 7 is fixedly installed at the end of the straight oil delivery pipe 6 furthest from the motor pump assembly 5. An electrically controlled valve 8 is fixedly installed inside the T-joint 7. Both ends of the T-joint 7 are fixedly equipped with... The oil delivery hose 9 and the side wall of the electrical control box 1 are provided with through grooves 10 that match the two sets of oil delivery hoses 9. The outer wall of the oil delivery straight pipe 6 is fixedly installed with a pressure sensor 14. The top of the electrical control box 1 is fixedly installed with a controller 11. The electric control valve 8 and the pressure sensor 14 are both connected to the controller 11. The top of the controller 11 is provided with control buttons 12. A manual pump 15 is provided on one side of the electric heating oil tank 2. The extraction end of the manual pump 15 is connected to the internal pipe of the electric heating oil tank 2. A connecting branch pipe 16 is fixedly connected to one side of the oil delivery straight pipe 6. The oil discharge end of the manual pump 15 is fixedly installed with the connecting branch pipe 16.

[0031] Move the electrical control box 1 to a suitable position next to the aircraft, extend the two sets of fuel hoses 9 of the fuel pump truck to a suitable length, connect them with the coupling connectors, add fuel to the electric heating fuel tank 2 through the fuel inlet pipe 3, and use the electric motor pump 5 to draw fuel from the electric heating fuel tank 2 into the fuel delivery straight pipe 6. The pressure sensor 14 is used to monitor the fuel supply pressure and flow rate in real time and transmit the data to the controller 11. The pressure sensor 14 is a JN-JLZCYZL type flow and pressure monitoring device. According to the preset instructions of the controller 11, the opening of the electronic control valve 8 is controlled, thereby controlling the fuel flow rate and the direction of the flow to the appropriate fuel delivery hose 9. This device can quickly and accurately adjust the fuel supply pressure, flow rate and direction, thereby improving the efficiency and accuracy of aircraft engine testing. In case of failure of the electric motor pump 5, fuel can be manually drawn by the manual pump 15. The manual pump 15 and the fuel delivery straight pipe 6 are connected by the connecting branch pipe 16 to meet the testing requirements and help ensure the continuity of the test.

[0032] Reference Figure 2-4 The bottom of the electrical control box 1 is rotatably connected to four sets of universal casters 17, which are located at the four corners of the electrical control box 1. A push handle 18 is fixedly installed on one side of the electrical control box 1. Four sets of lifting lugs 20 are fixedly installed on the top of the electrical control box 1. A filter frame 21 is threadedly connected to the top of the oil inlet pipe 3. A coarse filter screen 22 is fixedly installed inside the filter frame 21. A fine filter screen 23 is fixedly installed inside the filter frame 21 below the coarse filter screen 22. An oil pipe cap 4 is threadedly connected to the top of the filter frame 21.

[0033] The control box 1 is moved by the swivel casters 17, and the push handle 18 provides a handhold for pushing the control box 1, thus facilitating its movement with minimal effort. Four sets of lifting lugs 20 facilitate the handling and installation of the control box 1 using lifting equipment. The coarse filter 22 filters coarse impurities in the fuel, and the fine filter 23 filters fine impurities, which helps improve the purity of the fuel. At the same time, the filter frame 21 is threadedly connected to the fuel inlet pipe 3, which facilitates the disassembly and cleaning of the filter frame 21. The fuel pipe cap 4 prevents impurities from falling into the electric heating oil tank 2 from the fuel inlet pipe 3, further ensuring the purity of the fuel.

[0034] Reference Figure 1-3 The electrical control box 1 has a fixedly installed backup power supply 19, which is a 115V / 400Hz power supply. The electric heating oil tank 2 has a fixedly installed liquid level sensor 24, and a temperature monitor 25 is fixedly installed above the liquid level sensor 24 inside the electric heating oil tank 2. Both the liquid level sensor 24 and the temperature monitor 25 are connected to the controller 11. The backup power supply 19 provides backup power for the electrical control box 1 and other components that require power, ensuring that testing can be carried out even in the event of a power outage. The liquid level sensor 24 monitors the liquid level in the oil tank in real time, the temperature monitor 25 monitors the temperature in the oil tank in real time, and the controller 11 adjusts the temperature of the electric heating oil tank 2, which helps to ensure the safe use of fuel.

[0035] Reference Figure 1-3 A warning light 26 is fixedly installed on the top of the controller 11 and is electrically connected to the controller 11. When the controller 11 receives abnormal conditions detected by various components, it issues a warning signal through the warning light 26, which helps to promptly remind the operator to pay attention.

[0036] Working principle: Move the electrical control box 1 to a suitable position next to the aircraft, pull out the two sets of fuel hoses 9 of the fuel pump truck to a suitable length, connect them with the two sets of fuel hoses 9 using the coupling connector, add fuel to the electric heating fuel tank 2 through the fuel inlet pipe 3, and draw the fuel from the electric heating fuel tank 2 into the fuel straight pipe 6 through the motor pump unit 5. The pressure sensor 14 is used to monitor the fuel supply pressure and flow rate in real time and transmit the data to the controller 11. The pressure sensor 14 is a JN-JLZCYZL type flow and pressure monitoring device. According to the preset instructions of the controller 11, the opening of the electronic control valve 8 is controlled, thereby controlling the fuel flow rate and the direction of the flow to the appropriate fuel hose 9. This device can quickly and accurately adjust the fuel supply pressure, flow rate and direction, thereby improving the efficiency and accuracy of aircraft engine testing. The electrical control box 1 is moved by the universal casters 17, and the push handle 18 provides a hand action point when pushing the electrical control box 1, which is conducive to moving the electrical control box 1 with less effort.

[0037] When the motor pump set 5 fails, fuel is manually extracted by the manual pump 15. The manual pump 15 and the fuel straight pipe 6 are connected by the connecting branch pipe 16 to meet the testing requirements and ensure the continuity of the test. The four sets of lifting lugs 20 facilitate the use of lifting equipment to move and install the electrical control box 1.

[0038] Meanwhile, the backup power supply 19 provides backup power to the electrical control box 1 and other components that require power, ensuring that testing can be carried out even in the event of a power outage; the coarse filter 22 is used to filter coarse impurities in the fuel, and the fine filter 23 is used to filter fine impurities in the fuel, which helps to improve the purity of the fuel. At the same time, the filter frame 21 is threadedly connected to the fuel inlet pipe 3, which facilitates the disassembly and cleaning of the filter frame 21. The fuel pipe cap 4 prevents impurities from falling into the electric heating oil tank 2 from the fuel inlet pipe 3, further ensuring the purity of the fuel.

[0039] In addition, the liquid level sensor 24 monitors the liquid level in the fuel tank in real time, the temperature monitor 25 monitors the temperature in the fuel tank in real time, and the controller 11 adjusts the temperature of the electric heating fuel tank 2, which helps to ensure the safe use of fuel. When the controller 11 receives abnormal conditions detected by each component, it issues a warning signal through the warning light 26, which helps to promptly remind the operator to pay attention.

[0040] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A dedicated fuel drive device for aircraft engines, comprising an electrical control box (1), characterized in that, An electric heating oil tank (2) is fixedly installed inside the electrical control box (1). An oil inlet pipe (3) is fixedly connected to the top of the electric heating oil tank (2). The top of the oil inlet pipe (3) passes through the top of the electric heating oil tank (2). A motor pump set (5) is fixedly installed inside the electrical control box (1). The extraction end of the motor pump set (5) is connected to the internal pipe of the electric heating oil tank (2). An oil straight pipe (6) is fixedly installed at the oil discharge end of the motor pump set (5). A T-joint (7) is fixedly installed at the end of the oil straight pipe (6) away from the motor pump set (5). An electric control valve (8) is fixedly installed inside the three-way connector (7). Oil hoses (9) are fixedly installed at both ends of the three-way connector (7). The side wall of the electric control box (1) is provided with through grooves (10) that match the two sets of oil hoses (9). A pressure sensor (14) is fixedly installed on the outer wall of the oil straight pipe (6). A controller (11) is fixedly installed on the top of the electric control box (1). The electric control valve (8) and the pressure sensor (14) are both connected to the controller (11). The controller (11) is provided with control buttons (12) on the top.

2. The dedicated fuel drive device for aircraft engines according to claim 1, characterized in that, The bottom of the electrical control box (1) is rotatably connected to four sets of universal casters (17), and the four sets of universal casters (17) are located at the four corners of the electrical control box (1). A push handle (18) is fixedly installed on one side of the electrical control box (1).

3. The dedicated fuel drive device for aircraft engines according to claim 1, characterized in that, A manual pump (15) is provided on one side of the electric heating oil tank (2). The extraction end of the manual pump (15) is connected to the internal pipe of the electric heating oil tank (2). A connecting branch pipe (16) is fixedly connected to one side of the oil delivery straight pipe (6). The oil discharge end of the manual pump (15) is fixedly installed with the connecting branch pipe (16).

4. The dedicated fuel drive device for aircraft engines according to claim 1, characterized in that, Four sets of hoisting earrings (20) are fixedly installed on the top of the electrical control box (1).

5. A dedicated fuel drive device for aircraft engines according to claim 1, characterized in that, The electrical control box (1) is equipped with a fixed power supply (19), which is a 115V / 400Hz power supply.

6. The dedicated fuel drive device for aircraft engines according to claim 1, characterized in that, The top of the oil inlet pipe (3) is threaded with a filter frame (21), a coarse filter screen (22) is fixedly installed inside the filter frame (21), a fine filter screen (23) is fixedly installed inside the filter frame (21) below the coarse filter screen (22), and an oil pipe cap (4) is threadedly connected to the top of the filter frame (21).

7. A dedicated fuel drive device for aircraft engines according to claim 1, characterized in that, A liquid level sensor (24) is fixedly installed inside the electric heating oil tank (2), and a temperature monitor (25) is fixedly installed inside the electric heating oil tank (2) above the liquid level sensor (24). Both the liquid level sensor (24) and the temperature monitor (25) are connected to the controller (11) via signals.

8. A dedicated fuel drive device for aircraft engines according to claim 1, characterized in that, A warning light (26) is fixedly installed on the top of the controller (11), and the warning light (26) is electrically connected to the controller (11).

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