Aero-engine fuel nozzle spray angle testing device

Abstract

The utility model relates to the technical field of aero-engine fuel nozzle spraying angle testing, and discloses an aero-engine fuel nozzle spraying angle testing device which comprises a base, an air cylinder is fixedly installed on the right side of the upper surface of the base, a fixing box is arranged at the output end of the air cylinder, and a displayer is fixedly connected to the upper surface of the fixing box. A micro-processor is arranged in the display, the left side of the upper surface of the base is fixedly connected with an oil tank, and the upper surface of the oil tank fixedly communicates with an oil inlet hopper; the aero-engine fuel oil can be sprayed to the test plate through the nozzle, the pressure sensor is used for measuring a pressure field formed in the spraying area so as to obtain the spatial distribution condition of the spraying angle, and the microprocessor can feed back data collected by the pressure sensor to the displayer so as to deduce the spraying angle and distribution condition of the nozzle. A user can record and analyze data on the display.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft engine fuel nozzle spray angle testing, and in particular to an aircraft engine fuel nozzle spray angle testing device. Background Art

[0002] In the development and production of aircraft engines, the spray angle of aircraft engine fuel nozzles refers to the expansion angle of the fuel spray cone ejected from the fuel nozzle. This angle has an important impact on the performance and efficiency of fuel injection, because the spray angle directly affects the mixing effect of fuel and air and the uniformity of the combustion process.

[0003] At present, the main test method for the spray angle of the fuel nozzle of the aircraft engine is to test the spray angle based on the photographic method. Specifically, when the nozzle sprays, a camera is used to capture the spray image, and then a special image processing software is used to process it to obtain the nozzle spray angle. However, when a camera is used to capture the spray image, the image processing process is relatively complicated and easily consumes a lot of time, which is inconvenient for the staff to use.

[0004] The above information disclosed in the background technology is only used to increase the understanding of the background technology of the present application, and therefore, it may include information that does not constitute the prior art known to ordinary technicians in the field. Utility Model Content

[0005] In order to solve the problem that the image processing process is relatively complicated and time-consuming when using a camera to capture spray images, the present application provides an aircraft engine fuel nozzle spray angle test device.

[0006] The aircraft engine fuel nozzle spray angle test device provided in this application adopts the following technical solution:

[0007] An aircraft engine fuel nozzle spray angle test device comprises a base, a cylinder is fixedly installed on the right side of the upper surface of the base, a fixed box is provided at the output end of the cylinder, a display is fixedly connected to the upper surface of the fixed box, a microprocessor is provided in the display, a fuel tank is fixedly connected to the left side of the upper surface of the base, an oil inlet hopper is fixedly connected to the upper surface of the fuel tank, an electric telescopic rod is fixedly installed on one side of the fuel tank through a support plate, a connecting seat is hinged at the output end of the electric telescopic rod, a connecting pipe is provided on the connecting seat, a nozzle is fixedly connected to one end of the connecting pipe, the fuel tank is connected to the connecting pipe through an oil delivery mechanism, a groove is provided on the side of the fixed box close to the fuel tank, a pressure sensor is provided in the groove, a test board located in the groove is provided on the pressure sensor, and the microprocessor is electrically connected to the pressure sensor.

[0008] Preferably, the upper surface of the base is symmetrically fixedly connected with guide rails, and both side edges of the fixed box are fixedly connected with fixed plates, and the fixed plates are slidably arranged on the guide rails.

[0009] Preferably, the oil delivery mechanism includes an oil pump, which is fixedly connected to the upper surface of the oil tank, the input end of the oil pump is fixedly connected to the oil tank through an oil inlet pipe, the output end of the oil pump is fixedly connected to an oil outlet pipe, and one end of the oil outlet pipe is fixedly connected to the connecting pipe through a corrugated hose.

[0010] Preferably, a filter is provided inside the oil inlet hopper.

[0011] Preferably, a through groove is provided on the upper surface of the base.

[0012] In summary, this application includes the following beneficial technical effects:

[0013] The aviation engine fuel in the fuel tank can be pumped out through the oil pump, and then the fuel enters the connecting pipe and is finally sprayed to the test board through the nozzle. The test board can feed back to the pressure sensor, and the pressure sensor can feed back to the microprocessor. The microprocessor can display the test results to the user through the display. Compared with the existing technology, the aviation engine fuel can be sprayed to the test board through the nozzle, and the pressure sensor is used to measure the pressure field formed in the injection area to obtain the spatial distribution of the spray angle. The microprocessor can feed back the data collected by the pressure sensor to the display to infer the angle and distribution of the nozzle spray, and the user can record and analyze the data on the display. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the three-dimensional structure of an embodiment of the application;

[0015] Figure 2 is a schematic diagram of a three-dimensional cross-sectional structure of a fixed box of an embodiment of the application;

[0016] Figure 3 is a three-dimensional structural schematic diagram of an oil delivery mechanism of an embodiment of the application;

[0017] Figure 4 It is a three-dimensional structural schematic diagram of the oil inlet hopper and filter screen of the application embodiment.

[0018] Explanation of the accompanying drawings: 1. Base; 2. Cylinder; 3. Fixed box; 4. Display; 5. Nozzle; 6. Oil pump; 7. Oil inlet hopper; 8. Oil tank; 9. Through groove; 10. Fixed plate; 11. Guide rail; 12. Test plate; 13. Pressure sensor; 14. Oil inlet pipe; 15. Oil outlet pipe; 16. Connecting pipe; 17. Connecting seat; 18. Electric telescopic rod; 19. Support plate; 20. Corrugated hose; 21. Filter. DETAILED DESCRIPTION

[0019] The following is combined with Figure 1-4 This application is described in further detail.

[0020] The present application embodiment discloses an aircraft engine fuel nozzle spray angle test device. Figure 1-4 The aircraft engine fuel nozzle spray angle test device comprises a base 1, a cylinder 2 is fixedly installed on the right side of the upper surface of the base 1, a fixed box 3 is arranged at the output end of the cylinder 2, a display 4 is fixedly connected to the upper surface of the fixed box 3, a microprocessor (not shown in the figure) is arranged in the display 4, a fuel tank 8 is fixedly connected to the left side of the upper surface of the base 1, an oil inlet hopper 7 is fixedly connected to the upper surface of the fuel tank 8, an electric telescopic rod 18 is fixedly installed on one side of the fuel tank 8 through a support plate 19, a connecting seat 17 is hinged at the output end of the electric telescopic rod 18, and a connecting pipe 16 is arranged on the connecting seat 17, One end of the connecting pipe 16 is fixedly connected with the nozzle 5, the oil tank 8 is connected to the connecting pipe 16 through the oil delivery mechanism, a groove is provided on one side of the fixed box 3, a pressure sensor 13 is arranged in the groove, a test board 12 located in the groove is arranged on the pressure sensor 13, a microprocessor is electrically connected to the pressure sensor 13, the model of the pressure sensor 13 can be PT124Y-623, the model of the microprocessor can be PIC16F877, the model of the cylinder 2 can be SC32-25-S, and the model of the electric telescopic rod 18 can be ROB32-16-50 FA; When in use, the user can add aviation engine fuel into the fuel tank 8 through the oil inlet hopper 7, the fuel in the fuel tank 8 can be pumped out through the oil delivery mechanism, and then the fuel enters the connecting pipe 16, and finally sprayed to the test plate 12 through the nozzle 5. The test plate 12 can feedback to the pressure sensor 13, and the pressure sensor 13 can feedback to the microprocessor. The microprocessor can display the test results to the user through the display 4. By starting the electric telescopic rod 18, the connecting seat 17 can be driven to move, and the connecting seat 17 can drive the nozzle 5 to rotate through the connecting pipe 16. By starting the cylinder 2, the fixed box 3 can be driven to move, thereby driving the test plate 12 to move, so as to change the distance between the test plate 12 and the nozzle 5, and both can increase the test range of the test plate 12 for fuel. In this process, the aviation engine fuel can be sprayed to the test plate 12 through the nozzle 5, and the pressure sensor 13 is used to measure the pressure field formed in the injection area to obtain the spatial distribution of the spray angle. The microprocessor can feedback the data collected by the pressure sensor 13 to the display 4 to infer the angle and distribution of the nozzle 5 spray. The user can record and analyze the data on the display 4.

[0021] Reference Figure 1The upper surface of the base 1 is symmetrically fixedly connected with a guide rail 11, and both sides of the fixed box 3 are fixedly connected with a fixed plate 10, and the fixed plate 10 is slidably set on the guide rail 11; by sliding the fixed plate 10 on the guide rail 11, the fixed box 3 is more stable when moving.

[0022] Reference Figure 1 and Figure 3 The oil delivery mechanism includes an oil pump 6, which is fixedly connected to the upper surface of the fuel tank 8. The input end of the oil pump 6 is fixedly connected to the fuel tank 8 through an oil inlet pipe 14, and the output end of the oil pump 6 is fixedly connected to an oil outlet pipe 15. One end of the oil outlet pipe 15 is fixedly connected to a connecting pipe 16 through a corrugated hose 20. The model of the water pump can be selected as IS65-50-125; by starting the oil pump 6, the oil pump 6 can extract the aircraft engine fuel in the fuel tank 8 through the oil inlet pipe 14, and then the aircraft engine fuel can enter the connecting pipe 16 through the oil outlet pipe 15 and the corrugated hose 20, and the rotation of the connecting pipe 16 can be ensured by the corrugated hose 20.

[0023] Reference Figure 4 A filter screen 21 is provided inside the oil inlet hopper 7; the filter screen 21 can prevent dust and other impurities in the air from entering the oil inlet hopper 7.

[0024] Reference Figure 1 A through groove 9 is provided on the upper surface of the base 1; the aviation engine fuel on the test plate 12 can slide down through the through groove 9, and the user can place a collection box at the bottom of the through groove 9 to collect the fuel.

[0025] The implementation principle of the aircraft engine fuel nozzle spray angle test device of the embodiment of the present application is as follows: the electrical components appearing in the present application are all externally connected to a power supply and a control switch when in use. When in use, the user can add aircraft engine fuel into the fuel tank 8 through the oil inlet hopper 7, the fuel in the fuel tank 8 can be drawn out through the oil delivery mechanism, and then the fuel enters the connecting pipe 16, and finally sprayed to the test plate 12 through the nozzle 5. The test plate 12 can feed back to the pressure sensor 13, and the pressure sensor 13 can feed back to the microprocessor. The microprocessor can display the test results to the user through the display 4, and the connecting seat 17 can be driven to move by starting the electric telescopic rod 18, and the connecting seat 17 can be connected. The socket 17 can drive the nozzle 5 to rotate through the connecting pipe 16, and can drive the fixed box 3 to move by starting the cylinder 2, thereby driving the test plate 12 to move, so as to change the distance between the test plate 12 and the nozzle 5, and both can increase the test range of the test plate 12 for the fuel. During this process, the aviation engine fuel can be sprayed to the test plate 12 through the nozzle 5, and the pressure sensor 13 is used to measure the pressure field formed in the injection area to obtain the spatial distribution of the spray angle. The microprocessor can feed back the data collected by the pressure sensor 13 to the display 4 to infer the angle and distribution of the nozzle 5 spray, and the user can record and analyze the data on the display 4.

[0026] Finally, a few points should be explained: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, which may refer to mechanical connection or electrical connection, or internal communication between two components, or direct connection. "upper", "lower", "left", "right", etc. are only used to indicate relative positional relationships. When the absolute position of the object being described changes, the relative positional relationship may change;

[0027] Secondly: In the drawings of the embodiments disclosed in the present utility model, only the structures related to the embodiments disclosed in the present utility model are involved, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present utility model can be combined with each other;

[0028] Finally: The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present utility model should be included in the protection scope of the present utility model.

[0029] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. An aircraft engine fuel nozzle spray angle test device, comprising a base (1), characterized in that: A cylinder (2) is fixedly mounted on the right side of the upper surface of the base (1); a fixed box (3) is provided at the output end of the cylinder (2); a display (4) is fixedly connected to the upper surface of the fixed box (3); a microprocessor is provided in the display (4); an oil tank (8) is fixedly connected to the left side of the upper surface of the base (1); an oil inlet hopper (7) is fixedly connected to the upper surface of the oil tank (8); an electric telescopic rod (18) is fixedly mounted on one side of the oil tank (8) via a support plate (19); The output end is hingedly connected with a connection seat (17), a connection pipe (16) is arranged on the connection seat (17), one end of the connection pipe (16) is fixedly connected with a nozzle (5), the oil tank (8) is connected to the connection pipe (16) through an oil delivery mechanism, a groove is provided on a side of the fixed box (3) close to the oil tank (8), a pressure sensor (13) is arranged in the groove, a test plate (12) located in the groove is arranged on the pressure sensor (13), and the microprocessor is electrically connected to the pressure sensor (13).

2. The aircraft engine fuel nozzle spray angle test device according to claim 1, characterized in that: The upper surface of the base (1) is symmetrically fixedly connected with guide rails (11), and both side edges of the fixed box (3) are fixedly connected with fixed plates (10), and the fixed plates (10) are slidably arranged on the guide rails (11).

3. The aircraft engine fuel nozzle spray angle test device according to claim 1, characterized in that: The oil delivery mechanism comprises an oil pump (6), the oil pump (6) is fixedly connected to the upper surface of the oil tank (8), the input end of the oil pump (6) is fixedly connected to the oil tank (8) through an oil inlet pipe (14), the output end of the oil pump (6) is fixedly connected to an oil outlet pipe (15), and one end of the oil outlet pipe (15) is fixedly connected to the connecting pipe (16) through a corrugated hose (20).

4. The aircraft engine fuel nozzle spray angle test device according to claim 1, characterized in that: A filter screen (21) is arranged inside the oil inlet hopper (7).

5. The aircraft engine fuel nozzle spray angle test device according to claim 1, characterized in that: A through groove (9) is provided on the upper surface of the base (1).

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