Aviation piston type high-pressure common rail system testing device
By designing an aviation piston-type high-pressure common rail system testing device that includes components such as a workbench, a drive oil pump motor, and a fuel filter, the problems of exhaust pollution and high cost were solved, and efficient fuel pressurization and recycling were achieved, reducing test costs.
Patent Information
- Application Number
- CN202423245707.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-27
- Publication Date
- 2025-10-31
- Estimated Expiration
- 2034-12-27
AI Technical Summary
Existing testing equipment for aviation piston-type high-pressure common rail systems suffers from problems such as exhaust pollution and high testing costs.
A testing device was designed, comprising a workbench, a drive oil pump motor, an aviation kerosene cooler, a fuel tank, a low-pressure fuel pump, a fuel filter, a pressure transmitter, and a fuel damper. The device delivers fuel from the low-pressure fuel pump to the high-pressure fuel pump and uses the fuel damper to provide resistance, thereby achieving fuel pressurization and recycling.
It reduced exhaust emissions, improved fuel efficiency, lowered testing costs, and enabled efficient fuel delivery and recycling.
Smart Images
Figure CN223498028U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aviation high-pressure fuel pump testing technology, specifically to a testing device for an aviation piston-type high-pressure common rail system. Background Technology
[0002] The high-pressure common rail fuel system mainly consists of a high-pressure fuel pump, fuel rail, and injectors. The high-pressure fuel pump outputs high-pressure fuel, which is then supplied to the injectors via high-pressure fuel lines. The electronic control system precisely controls the injectors to accurately inject fuel into the cylinders. Its core working principle lies in the precise pumping process, achieving efficient fuel delivery through three key stages.
[0003] However, existing testing equipment for aviation piston-type high-pressure common rail systems has the following problems during use: the exhaust gas emitted by traditional engine combustion pollutes the atmosphere and cannot be recycled, and the testing cost is high. Utility Model Content
[0004] The purpose of this invention is to provide a testing device for an aviation piston-type high-pressure common rail system to solve the related problems mentioned in the background art.
[0005] To achieve the above objectives, this utility model provides the following technical solution: a testing device for an aviation piston-type high-pressure common rail system, comprising a workbench, a drive oil pump motor, and an aviation kerosene cooler. A fuel tank and an aviation kerosene cooler are disposed on the rear wall of the workbench. A drive oil pump motor is disposed on the top of the workbench. A high-pressure fuel pump mounting bracket is installed on the top of the workbench, and a high-pressure fuel pump body is disposed inside the high-pressure fuel pump mounting bracket. A low-pressure fuel pump is installed on the side wall of the workbench, and the input end of the low-pressure fuel pump is connected to one side of the fuel tank via a connecting pipe. The low-pressure fuel pump output end is equipped with a low-pressure fuel pipe connected to one end of the high-pressure fuel pump body. A fuel filter and a pressure transmitter are installed on the side of the low-pressure fuel pipe near the low-pressure fuel pump. A fuel damper body is installed on the side of the low-pressure fuel pipe near the high-pressure fuel pump body. A fuel damper bracket connected to a workbench is installed below the fuel damper body. A fuel rail fixing bracket is installed at the top of the workbench, and a fuel rail body is installed on the inner wall of the fuel rail fixing bracket. Fuel rail return pipes penetrating the high-pressure fuel pump body and the inside of the fuel tank are respectively installed at both ends of the fuel rail return pipe.
[0006] This technical solution provides a test device for an aviation piston-type high-pressure common rail system, wherein a coupling is installed at the output end of the drive oil pump motor, and one end of the coupling is connected to the high-pressure fuel pump body.
[0007] This technical solution provides a test device for an aviation piston-type high-pressure common rail system. A speed sensor bracket is provided on one side of the high-pressure fuel pump mounting bracket, and a speed sensor body for detecting the speed of the coupling is provided inside the speed sensor bracket.
[0008] This technical solution provides a test device for an aviation piston-type high-pressure common rail system. The top of the high-pressure fuel pump body is provided with a high-pressure oil pipe, and one side of the high-pressure oil pipe is connected to the fuel rail body. A flow meter is installed between the high-pressure oil pipes.
[0009] Compared with the prior art, this utility model provides a testing device for an aviation piston-type high-pressure common rail system, which has the following advantages:
[0010] 1. This utility model uses a low-pressure fuel pump to deliver fuel through a low-pressure fuel line and fuel filter to the high-pressure fuel pump body. A pressure transmitter is installed at the outlet of the low-pressure fuel pump to monitor the outlet pressure in real time. The high-pressure fuel pump body is installed on the high-pressure fuel pump mounting bracket. Fuel passes through the fuel damper body to the high-pressure fuel pump body. The main function of the fuel damper body is to provide resistance to motion, reduce motion energy, improve the atomization state of fuel during injection, improve fuel utilization, and reduce exhaust emissions.
[0011] 2. This utility model pressurizes the fuel through the high-pressure fuel pump body and then sends it to the fuel rail body through the high-pressure fuel pipe. The fuel on the fuel rail body returns to the aviation kerosene cooler through the fuel rail return pipe, which facilitates recycling.
[0012] 3. This utility model drives a low-pressure fuel pump to deliver fuel from the fuel tank to the high-pressure fuel pump body through a low-pressure fuel pipe. The high-pressure fuel pump body can then deliver fuel to the fuel rail body through the fuel rail return pipe. This structure requires less testing equipment and can provide a high-pressure, high-flow-rate fuel testing device, achieving the advantages of low cost and high efficiency. Attached Figure Description
[0013] Figure 1 This is a three-dimensional structural diagram of the present invention;
[0014] Figure 2 For the present utility model Figure 1 A magnified structural diagram at point A;
[0015] Figure 3 This is a top view of the structure of this utility model;
[0016] Figure 4 This is a schematic diagram of the right-side structure of this utility model.
[0017] In the diagram: 1. Workbench; 2. Drive oil pump motor; 3. Aviation kerosene cooler; 4. Oil rail bracket; 5. Fuel tank; 6. Pressure transmitter; 7. Fuel damper bracket; 8. Fuel filter; 9. Low-pressure fuel pump; 10. High-pressure fuel pump bracket; 11. High-pressure fuel pump body; 12. Oil rail return pipe; 13. Low-pressure oil pipe; 14. Fuel damper body; 15. Speed sensor bracket; 16. Coupling; 17. Speed sensor body; 18. Flow meter; 19. High-pressure oil pipe; 20. Oil rail body. Detailed Implementation
[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.
[0019] Example 1, as Figure 1-2As shown, this utility model provides a technical solution: a test device for an aviation piston-type high-pressure common rail system, including a workbench 1, a drive oil pump motor 2, and an aviation kerosene cooler 3. A fuel tank 5 and an aviation kerosene cooler 3 are installed on the rear wall of the workbench 1. The drive oil pump motor 2 is installed on the top of the workbench 1. A high-pressure fuel pump mounting bracket 10 is installed on the top of the workbench 1, and a high-pressure fuel pump body 11 is installed inside the high-pressure fuel pump mounting bracket 10. A low-pressure fuel pump 9 is installed on the side wall of the workbench 1, and the input end of the low-pressure fuel pump 9 is connected to the fuel tank via a connecting pipe. Connected to one side of 5, the low-pressure fuel pump 9 has a low-pressure fuel pipe 13 connected to one end of the high-pressure fuel pump body 11. A fuel filter 8 and a pressure transmitter 6 are installed on the side of the low-pressure fuel pipe 13 closest to the low-pressure fuel pump 9. A coupling 16 is installed at the output end of the fuel pump motor 2, and one end of the coupling 16 is connected to the high-pressure fuel pump body 11. A speed sensor bracket 15 is installed on one side of the high-pressure fuel pump mounting bracket 10, and a speed sensor body 17 for detecting the speed of the coupling 16 is installed inside the speed sensor bracket 15. A fuel damper body 14 is installed on the side of the fuel pipe 13 near the high-pressure fuel pump body 11, and a fuel damper bracket 7 connected to the workbench 1 is installed below the fuel damper body 14. The real-time speed at the high-pressure fuel pump body 11 can be monitored by the speed sensor body 17. The fuel tank 5 can exchange heat through the aviation kerosene cooler 3 to provide the temperature required for the test. The low-pressure fuel pump 9 draws fuel from the fuel tank 5 through the low-pressure fuel pipe 13, and the fuel is then transferred from the low-pressure fuel pump 9 to the high-pressure fuel pump body through the fuel filter element 8. 11. A pressure transmitter 6 is installed at the outlet of the low-pressure fuel pump 9. The pressure transmitter 6 monitors the outlet pressure of the low-pressure fuel pump 9 in real time. The high-pressure fuel pump body 11 is installed on the high-pressure fuel pump mounting bracket 10. Fuel passes through the fuel damper body 14 to the high-pressure fuel pump body 11. The main function of the fuel damper body 14 is to provide resistance to motion and reduce motion energy. After the high-pressure fuel pump body 11 pressurizes the fuel, it passes through the high-pressure fuel pipe 19 to the fuel rail body 20. The fuel on the fuel rail body 20 returns to the aviation kerosene cooler 3 through the fuel rail return pipe 12 for easy recycling.
[0020] Example 2, as Figure 1-4As shown, this utility model provides a technical solution: a test device for an aviation piston-type high-pressure common rail system, including a fuel rail fixing frame 4 installed on the top of a workbench 1, and a fuel rail body 20 provided on the inner wall of the fuel rail fixing frame 4. The two ends of the fuel rail return pipe 12 are respectively installed with fuel rail return pipes 12 that penetrate the inner side of the high-pressure fuel pump body 11 and the fuel tank 5. The top of the high-pressure fuel pump body 11 is provided with a high-pressure oil pipe 19, and one side of the high-pressure oil pipe 19 is connected to the fuel rail body 20. A flow meter 18 is installed between the high-pressure oil pipes 19. The flow rate of fuel from the high-pressure fuel pump body 11 through the high-pressure oil pipe 19 is monitored by the flow meter 18 installed on the high-pressure oil pipe 19.
[0021] Working principle: First, the external power supply is connected, which drives the low-pressure fuel pump 9 to deliver fuel from the fuel tank 5 to the high-pressure fuel pump body 11 through the low-pressure fuel line 13. The fuel from the high-pressure fuel pump body 11 is then delivered to the fuel rail body 20 through the fuel rail return line 12. The fuel is filtered by the fuel filter element 8. The pressure transmitter 6 monitors the fuel pressure in real time. The speed sensor body 17 monitors the real-time speed of the high-pressure fuel pump body 11. The main function of the fuel damper body 14 is to provide resistance to motion, reduce motion energy, and prevent insufficient fuel supply. After the high-pressure fuel pump body 11 pressurizes the fuel, it is delivered to the fuel rail body 20 through the high-pressure fuel line 19. The fuel on the fuel rail body 20 returns to the aviation kerosene cooler 3 through the fuel rail return line 12 for recycling. The flow meter 18 installed on the high-pressure fuel line 19 monitors the fuel flow rate of the high-pressure fuel pump body 11 through the high-pressure fuel line 19.
[0022] Finally, it should be noted that the above content is only used to illustrate the technical solution of this utility model, and is not intended to limit the scope of protection of this utility model. Simple modifications or equivalent substitutions made by those skilled in the art to the technical solution of this utility model do not depart from the essence and scope of the technical solution of this utility model.
Claims
1. A testing device for an aviation piston-type high-pressure common rail system, comprising a workbench (1), a drive oil pump motor (2), and an aviation kerosene cooler (3), characterized in that: The rear wall of the workbench (1) is provided with a fuel tank (5) and an aviation kerosene cooler (3). The top of the workbench (1) is provided with a drive oil pump motor (2). The top of the workbench (1) is equipped with a high-pressure fuel pump mounting bracket (10), and the high-pressure fuel pump body (11) is provided inside the high-pressure fuel pump mounting bracket (10). The side wall of the workbench (1) is equipped with a low-pressure fuel pump (9), and the input end of the low-pressure fuel pump (9) is connected to one side of the fuel tank (5) through a connecting pipe. The output end of the low-pressure fuel pump (9) is equipped with a low-pressure oil pipe (13) connected to one end of the high-pressure fuel pump body (11), and the low-pressure oil... A fuel filter (8) and a pressure transmitter (6) are provided on the side of the pipe (13) near the low-pressure fuel pump (9). A fuel damper body (14) is provided on the side of the low-pressure fuel pipe (13) near the high-pressure fuel pump body (11). A fuel damper bracket (7) connected to the workbench (1) is installed below the fuel damper body (14). A fuel rail fixing bracket (4) is installed at the top of the workbench (1). A fuel rail body (20) is provided on the inner wall of the fuel rail fixing bracket (4). A fuel rail return pipe (12) is installed at both ends of the fuel rail return pipe (12) that penetrates the high-pressure fuel pump body (11) and the inside of the fuel tank (5).
2. The testing device for an aviation piston-type high-pressure common rail system according to claim 1, characterized in that: The output end of the drive oil pump motor (2) is equipped with a coupling (16), and one end of the coupling (16) is connected to the high-pressure fuel pump body (11).
3. The testing device for an aviation piston-type high-pressure common rail system according to claim 2, characterized in that: A speed sensor bracket (15) is provided on one side of the high-pressure fuel pump mounting bracket (10), and a speed sensor body (17) for detecting the speed of the coupling (16) is provided inside the speed sensor bracket (15).
4. The testing device for an aviation piston-type high-pressure common rail system according to claim 1, characterized in that: The high-pressure fuel pump body (11) is provided with a high-pressure oil pipe (19) at the top, and one side of the high-pressure oil pipe (19) is connected to the fuel rail body (20). A flow meter (18) is provided between the high-pressure oil pipes (19).