Performance test bench for aircraft fuel pump

Abstract

The utility model discloses a performance test bench for an aircraft fuel pump, which belongs to the technical field of aircraft fuel pumps and comprises a test oil tank, the top of the test oil tank is fixedly connected with a plurality of mounting boxes, and one end of each mounting box is provided with an oil outlet pipe. According to the utility model, when oil liquid is added into the inner cavity of the test oil tank, impurities in the oil liquid are directly filtered through the filter screen, the cleanliness of the oil liquid at the bottom of the inner cavity of the test oil tank is ensured, and in addition, when the aircraft fuel pump is tested, the oil liquid flowing back into the inner cavity of the test oil tank from the oil return pipe is also filtered by the filter screen; the device is simple in structure and convenient to operate, preparation is made for subsequent aircraft fuel pump testing, flowing fluency of oil in the oil outlet pipe, the aircraft fuel pump and the oil return pipe is guaranteed, meanwhile, the oil detection accuracy of the pressure sensor and the flow meter is guaranteed, and the performance testing accuracy of the aircraft fuel pump is guaranteed.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft fuel pump, more particularly to a performance test test bench of aircraft fuel pump. BACKGROUND

[0002] The main role of the aircraft fuel pump is to suck fuel from the tank and deliver it to the fuel supply pipe after pressurization, cooperate with the fuel pressure regulator to establish a certain fuel pressure, and ensure continuous supply of fuel to the fuel nozzle. The specific working principle of the fuel pump includes two processes of oil suction and pumping: in the oil suction process, the movement of the pump piston provides power, the oil inlet valve is opened, and the fuel is sucked in; in the pumping process, the oil inlet valve is closed, the pump piston moves to generate pressure, and when the pressure exceeds the oil rail pressure, the oil outlet valve is opened, and the fuel is pumped into the oil rail.

[0003] After retrieval, the utility model with publication number CN221547264U discloses a performance test test bench of aircraft fuel pump, which comprises a test platform, an installation shell, a parameter acquisition assembly and a control assembly installed on the test platform; the inside of the installation shell is hollow, and the fuel pump is installed in the installation shell; an inlet and an outlet are formed in the side wall of the installation shell, and the inlet and the outlet are in communication with the inside of the installation shell; the oil inlet of the fuel pump is connected with a first oil pipe, the other end of the first oil pipe penetrates the inlet and is in communication with the oil outlet of the oil tank arranged in the test platform; the oil outlet of the fuel pump is connected with a second oil pipe, and the other end of the second oil pipe penetrates the outlet and is in communication with the oil inlet of the oil tank; the parameter acquisition assembly comprises a pressure sensor and a flowmeter, the pressure sensor is arranged on the first oil pipe, and the flowmeter is arranged on the second oil pipe; the control assembly is electrically connected with the fuel pump, the pressure sensor and the flowmeter; the patent has improved the accuracy of performance test of the aircraft fuel pump. But the above-mentioned patent still has the following shortcomings: although the filter can filter the residues in the oil, the filter will affect the flow resistance of the oil, and affect the accuracy of the performance test of the aircraft fuel pump, therefore, we propose a performance test test bench of aircraft fuel pump. UTILITY MODEL CONTENTS

[0004] In view of the problems in the prior art, the utility model aims to provide a performance test test bench of aircraft fuel pump.

[0005] To solve the above problems, the utility model adopts the following technical scheme:

[0006] A kind of performance test test bench of aircraft fuel pump, including test tank, the top of the test tank is fixedly connected with multiple installation boxes, one end of multiple installation boxes is provided with oil outlet pipe, one end of oil outlet pipe is fixedly sleeved to the bottom of test tank inner cavity, one end of multiple installation boxes is provided with oil return pipe, one end of oil return pipe is fixedly sleeved to the top of test tank inner cavity, pressure sensor is fixedly installed on the oil outlet pipe, flowmeter is fixedly installed on the oil return pipe, the side of the test tank is provided with pull-out slot, the inner cavity of pull-out slot is sleeved with oil filter frame, the bottom of the inner cavity of oil filter frame is fixedly sleeved with filter screen.

[0007] As a preferred scheme of the utility model, the front of the test tank is fixedly installed with control panel, and the side of the test tank is provided with power module.

[0008] As a preferred scheme of the utility model, the side of the test tank is fixedly installed with oil discharge valve, and the end of the oil discharge valve extends to the bottom of the inner cavity of the test tank.

[0009] As a preferred scheme of the utility model, the side of the test tank is screwed to threaded plug, and the end of the threaded plug extends to the inner cavity of the test tank.

[0010] As a preferred scheme of the utility model, the side of the oil filter frame extends to the outside of the test tank and is fixedly connected with handle, and the side of the oil filter frame and the inner wall of the pull-out slot are attached.

[0011] As a preferred scheme of the utility model, the top of the installation box is hinged with installation cover.

[0012] Compared with the prior art, the utility model has the advantages that:

[0013] In the utility model, when oil is added to the inner cavity of the test tank, impurities in the oil are directly filtered through the filter screen, ensuring the cleanliness of the oil at the bottom of the inner cavity of the test tank; when the aircraft fuel pump is tested, the oil flowing back into the inner cavity of the test tank through the oil return pipe is also filtered by the filter screen, preparing for subsequent testing of the aircraft fuel pump, ensuring the smoothness of the oil flowing through the oil outlet pipe, the aircraft fuel pump and the oil return pipe, and the accuracy of the pressure sensor and the flowmeter in detecting the oil, ensuring the accuracy of the performance test of the aircraft fuel pump, and good practicability. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 It is the overall structure schematic view of the utility model;

[0015] Figure 2 It is the overall structure explosion drawing of the utility model;

[0016] Figure 3 is a structural schematic view of the test oil tank of the utility model;

[0017] Figure 4 is a structural schematic view of the installation box of the utility model.

[0018] Explanation of reference numerals in the drawing:

[0019] 1, test oil tank; 2, pull-out groove; 3, oil filter frame; 4, filter screen; 5, installation box; 6, oil outlet pipe; 7, oil return pipe; 8, pressure sensor; 9, flow meter; 10, installation cover; 11, control panel; 12, threaded plug; 13, oil drain valve; 14, power module; 15, handle. DETAILED DESCRIPTION

[0020] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0021] In the description of the utility model, it should be noted that the terms "upper", "lower", "inner", "outer", "top / bottom end" and the like indicate the orientation or positional relationship shown in the drawing, and are only for the convenience of describing the utility model and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the utility model. In addition, the terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0022] In the description of the utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "mounting", "provided with", "sleeved / connected", "connected" and the like should be understood broadly, for example, "connected" can be fixedly connected, or can be detachably connected, or integrally connected; can be mechanically connected, or can be electrically connected; can be directly connected, or can be indirectly connected through an intermediate medium; can be the communication inside two elements. For those skilled in the art, the specific meanings of the above terms in the utility model can be understood according to the specific circumstances.

[0023] Embodiment:

[0024] Please refer to Figures 1-4The utility model provides an aircraft fuel pump performance test test bench, including test oil tank 1, the top of test oil tank 1 is fixedly connected with a plurality of installation box 5, and one end of a plurality of installation box 5 is provided with oil outlet pipe 6, and one end of oil outlet pipe 6 is fixedly sleeved to the bottom of the inner chamber of test oil tank 1, and the other end of a plurality of installation box 5 is provided with oil return pipe 7, and one end of oil return pipe 7 is fixedly sleeved to the top of the inner chamber of test oil tank 1, and pressure sensor 8 is fixedly installed on oil outlet pipe 6, and flowmeter 9 is fixedly installed on oil return pipe 7, and the side of test oil tank 1 is provided with pullout slot 2, and the inner chamber of pullout slot 2 is sleeved with oil filter frame 3, and the bottom of the inner chamber of oil filter frame 3 is fixedly sleeved with filter screen 4.

[0025] In the embodiment, the end of the oil return pipe 7 and the oil outlet pipe 6 in the inner chamber of the installation box 5 is provided with a structure connected with the aircraft fuel pump, which is a prior art.

[0026] Specifically, please refer to Figure 2 The front of the test oil tank 1 is fixedly installed with a control panel 11, and the side of the test oil tank 1 is provided with a power module 14.

[0027] In the embodiment, the device is controlled by the control panel 11, and the data detected by the pressure sensor 8 and the flowmeter 9 are displayed. In addition, the pressure sensor 8, the flowmeter 9, the control panel 11 and the aircraft fuel pump are powered by the power module 14.

[0028] Specifically, please refer to Figure 2 The side of the test oil tank 1 is fixedly installed with an oil drain valve 13, and the end of the oil drain valve 13 extends to the bottom of the inner chamber of the test oil tank 1.

[0029] In the embodiment, the oil in the test oil tank 1 is discharged by opening the oil drain valve 13.

[0030] Specifically, please refer to Figure 2 The side of the test oil tank 1 is screwed to a threaded plug 12, and the end of the threaded plug 12 extends to the inner chamber of the test oil tank 1.

[0031] In the embodiment, the oil is put into the inner chamber of the test oil tank 1 by removing the threaded plug 12. In addition, the oil put into the inner chamber of the test oil tank 1 is also filtered by the filter screen 4.

[0032] Specifically, please refer to Figure 2 The side of the oil filter frame 3 extends to the outside of the test oil tank 1 and is fixedly connected with a handle 15, and the side of the oil filter frame 3 is in close contact with the inner wall of the pullout slot 2.

[0033] In the embodiment, the oil filter frame 3 is taken by the handle 15, and the close contact between the side of the oil filter frame 3 and the inner wall of the pullout slot 2 ensures the stability of the oil filter frame 3 in the inner chamber of the pullout slot 2.

[0034] Specifically, please refer to Figure 1 The top of the installation box 5 is hinged with an installation cover 10.

[0035] In this embodiment, the aircraft fuel pump to be tested is installed in the inner cavity of the installation box 5 by opening the installation cover 10.

[0036] Working principle: in use, first, open the installation cover 10 to install the aircraft fuel pump in the inner cavity of the installation box 5, so that the input end of the aircraft fuel pump is connected with the end of the oil outlet pipe 6, and the output end of the aircraft fuel pump is connected with the end of the oil return pipe 7, then remove the threaded plug 12 to pour the oil into the inner cavity of the test tank 1, filter the impurities in the oil through the filter screen 4, and then start the aircraft fuel pump to generate suction in the oil outlet pipe 6, use the suction of the oil outlet pipe 6 to pump the oil at the bottom of the inner cavity of the test tank 1 into the fuel pump, at the same time, use the pressure sensor 8 to detect the pressure of the oil flow, in addition, guide the oil in the fuel pump back to the inner cavity of the test tank 1 through the oil return pipe 7, and at the same time, use the flow meter 9 to detect the flow of the oil, finally, the oil flowing back into the inner cavity of the test tank 1 is filtered again by the filter screen 4, so that the residues in the oil are filtered out, so as to facilitate the subsequent use of the oil, avoid the residues in the oil affecting the performance test of the aircraft fuel pump, and the like.

[0037] The above is only a preferred specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any skilled person in the art can make equivalent replacement or change according to the technical scheme and improvement concept of the present application within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. A test bench for testing the performance of an aircraft fuel pump, comprising a test tank (1), characterized in that: The top of the test oil tank (1) is fixedly connected with a plurality of installation boxes (5), one end of the plurality of installation boxes (5) is provided with an oil outlet pipe (6), one end of the oil outlet pipe (6) is fixedly sleeved to the bottom of the inner cavity of the test oil tank (1), the other end of the plurality of installation boxes (5) is provided with an oil return pipe (7), one end of the oil return pipe (7) is fixedly sleeved to the top of the inner cavity of the test oil tank (1), the oil outlet pipe (6) is fixedly installed with a pressure sensor (8), the oil return pipe (7) is fixedly installed with a flowmeter (9), the side of the test oil tank (1) is provided with a pull slot (2), the pull slot (2) is sleeved with an oil filter frame (3), the bottom of the inner cavity of the oil filter frame (3) is fixedly sleeved with a filter screen (4).

2. A performance test bench for an aircraft fuel pump according to claim 1, characterized in that: The front of the test oil tank (1) is fixedly installed with a control panel (11), the side of the test oil tank (1) is provided with a power module (14).

3. A performance test bench for an aircraft fuel pump according to claim 1, characterized in that: The side of the test oil tank (1) is fixedly installed with an oil discharge valve (13), the end of the oil discharge valve (13) extends to the bottom of the inner cavity of the test oil tank (1).

4. A performance test bench for an aircraft fuel pump according to claim 1, characterized in that: The side of the test oil tank (1) is screwed to a threaded plug (12), the end of the threaded plug (12) extends to the inner cavity of the test oil tank (1).

5. A performance test bench for an aircraft fuel pump according to claim 1, characterized in that: The side of the oil filter frame (3) extends to the outside of the test oil tank (1) and is fixedly connected with a handle (15), the side of the oil filter frame (3) and the inner wall of the pull slot (2) are fitted.

6. A performance test bench for an aircraft fuel pump according to claim 1, characterized in that: The top of the installation box (5) is hinged with an installation cover (10).

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