A static pressure device for aircraft engines

Abstract

The utility model relates to aircraft engine detection, and discloses an aircraft engine static pressure device, including an equipment frame, an oil tank, a manual reversing valve, a manual pressure pump, an oil filter, a relief valve, two pressure gauges and a differential pressure gauge. On the basis of meeting the requirements of "the maximum oil supply pressure in the oil supply and return oil pipelines is not greater than 13MPa, the oil supply and return oil flow rates are not less than 2L / min; the oil supply and return oil pressure difference is not less than 3.6Mpa and is adjustable", the design is optimized, and the components are structurally optimized and arranged. Beneficial effects: compact structure, small footprint; long-term stable operation at an ambient temperature of ‑40℃~+40℃ and an ambient pressure of normal pressure; high adjustment accuracy.

Description

Technical Field

[0001] The utility model relates to aircraft engine detection, in particular to an aircraft engine static pressure device. Background Art

[0002] At present, my country has strengthened its attention to aviation safety, among which the quality of aviation engine assembly is an important part of aviation safety. In the assembly of aircraft engines, there are many devices involved, the technical requirements are relatively high, and the process is relatively complicated. Because of these factors, the process control of aircraft engine assembly is more difficult, and there are many uncertainties and complexities. Starting from the assembly of aircraft engines, we conducted a simple analysis of its quality control and put forward the existing problems. We also explored the supporting measures and requirements of quality control from the aspects of pre-assembly quality control, supervision during the assembly process, and control of key points.

[0003] Through the pressure test during the assembly stage, the leakage data such as leakage position and leakage flow rate under the static pressure state of the engine can be obtained, which can be used to evaluate the impact of leakage on engine performance.

[0004] The static pressure device is used to provide a stable high-pressure oil source and corresponding oil return pipeline for the TBV, VBV, VSV, HPTACC, and LPTACC actuating parts, forming a certain pressure difference, so as to complete the static pressure inspection and calibration of the actuating parts of the fuel control system. The existing equipment uses manual pressure testing, the cart structure is not compact enough, and the pump flow and pressure are not enough to meet the test. Utility Model Content

[0005] The present application provides an aircraft engine static pressure device, which can solve the problems raised in the background technology.

[0006] In the present application, a static pressure device for an aircraft engine is provided, comprising:

[0007] The equipment rack comprises: a horizontal part and a vertical part; the bottom surface of the horizontal part is provided with casters; the vertical part is provided with a first interface and a second interface, and the first interface and the second interface are respectively connected with a first oil pipe and a second oil pipe;

[0008] An oil tank, fixed to the horizontal part of the equipment frame, connected with an oil supply pipe and an oil return pipe;

[0009] A manual reversing valve, wherein the four oil ports are respectively connected to the first oil pipe, the second oil pipe, the oil supply pipe and the oil return pipe; at least a first station: the oil supply pipe and the first oil pipe form an oil supply pipeline, and the oil return pipe and the second oil pipe form an oil return pipeline; a second station: the oil supply pipe and the second oil pipe form an oil supply pipeline, and the oil return pipe and the first oil pipe form an oil return pipeline;

[0010] A manual pressure pump is connected to the oil supply pipe to pump the oil in the oil tank into the oil supply pipe;

[0011] The oil filter is connected to the oil supply pipe to filter the oil pumped into the oil supply pipe;

[0012] The overflow valve is connected between the oil supply pipe and the oil return pipe to allow the oil pumped into the oil supply pipe to overflow into the oil return pipe;

[0013] two pressure gauges, connected to the first oil pipe and the second oil pipe respectively;

[0014] The differential pressure gauge is connected between the first oil pipe and the second oil pipe.

[0015] Furthermore, it also includes a ball valve connected to the first oil pipe;.

[0016] Furthermore, the horizontal portion of the equipment rack is also provided with an oil collecting trough structure; each connection point on the first oil pipe, the second oil pipe, the oil supply pipe and the oil return pipe is covered by the oil collecting trough structure.

[0017] Furthermore, a support frame is fixedly provided on the horizontal part of the equipment frame, and the oil tank is fixed on the top of the support frame; and the oil inlet of the oil supply pipe is connected to the bottom surface of the oil tank.

[0018] Furthermore, the two pressure gauges and the differential pressure gauge are both fixedly mounted on the horizontal top surface of the vertical portion of the equipment rack.

[0019] Furthermore, on the oil supply pipe, the overflow valve is located after the oil filter.

[0020] Furthermore, the oil tank also has at least one of the following settings: Setting 1: a liquid level gauge is provided on the oil tank; Setting 2: an air filter is provided on the oil tank; Setting 3: a first oil discharge port with a valve is provided on the oil tank.

[0021] Furthermore, it also includes a force rod; the force rod is detachably fixed to the equipment frame, and in a disassembled state, one end of the force rod can be inserted into the handle of a manual pressure pump.

[0022] In summary, in the present application, a static pressure device for an aircraft engine includes an equipment rack, an oil tank, a manual reversing valve, a manual pressure pump, an oil filter, a relief valve, two pressure gauges and a differential pressure gauge. On the basis of meeting the requirements of "the maximum oil supply pressure in the oil supply and return oil pipelines is not greater than 13MPa, the oil supply and return oil flow rates are not less than 2L / min; the oil supply and return oil pressure difference is not less than 3.6Mpa and is adjustable", the design is optimized and the components are arranged in an optimized structure. Beneficial effects: compact structure, small footprint; long-term stable operation at an ambient temperature of -40℃ to +40℃ and an ambient pressure of normal pressure; high adjustment accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the background technology, the drawings required for use in the embodiments of the present application or the background technology will be described below.

[0024] Figure 1 A schematic diagram of this application;

[0025] Figure 2 A schematic diagram of another perspective of this application;

[0026] Figure 3 This is a schematic diagram of the settings on the fuel tank;

[0027] Figure 4 It is a schematic diagram of the setting on the vertical part of the equipment rack;

[0028] Figure 5 Schematic diagram for the application.

[0029] In the figure,

[0030] 1. Equipment frame; 1a. Horizontal part; 1a1. Casters; 1a2. Support frame; 1a3. Oil collecting tank structure; 1b. Vertical part; 1b1. Handle; 1c. Connecting block; 1c1. First interface; 1c2. Second interface; 1c3. First oil pipe; 1c4. Second oil pipe;

[0031] 2. Fuel tank; 2a. Fuel filling port; 2b. Fuel supply pipe; 2c. Fuel return pipe; 2e. Liquid level gauge; 2f. Air filter; 2g. First oil outlet;

[0032] 3. Manual reversing valve;

[0033] 4. Manual pressure pump;

[0034] 5. Oil filter;

[0035] 6. Overflow valve;

[0036] 7. Pressure gauge;

[0037] 8. Differential pressure gauge;

[0038] 9. Afterburner rod; 9a. Clip;

[0039] 10. Ball valve;

[0040] 11. Oil circuit block. DETAILED DESCRIPTION

[0041] The following is further explained in conjunction with the accompanying drawings. Unless otherwise defined, the technical terms or scientific terms used in the present disclosure should be understood by people with ordinary skills in the field to which the present disclosure belongs. The "first", "second" and similar words used in the present disclosure do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprise" and similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0042] See also Figure 1 and Figure 2 , an aircraft engine static pressure device, including an equipment frame 1, an oil tank 2, a manual reversing valve 3, a manual pressure pump 4, an oil filter 5, a relief valve 6, two pressure gauges 7 and a differential pressure gauge 8.

[0043] The equipment rack 1 includes a horizontal portion 1a and a vertical portion 1b. Specifically, the equipment rack 1 can be formed by processing the horizontal portion 1a and the vertical portion 1b through sheet metal, and then the two portions are welded or connected and assembled together using fasteners.

[0044] The bottom surface of the horizontal part 1a is provided with casters 1a1, which is convenient for moving the entire aircraft engine static pressure device. Specifically, two of the casters 1a1 can also be provided with foot brakes, and the vertical part 1b can be provided with a handle 1b1, which is convenient for holding by hand to push.

[0045] The vertical part 1b has a first interface 1c1 and a second interface 1c2, and the first interface 1c1 and the second interface 1c2 are respectively connected to the first oil pipe 1c3 and the second oil pipe 1c4. Specifically, the first interface 1c1 and the second interface 1c2 can be set on a connecting block 1c, the connecting block 1c is fixedly connected to the vertical part 1b, and the first oil pipe 1c3 and the second oil pipe 1c4 are connected to the connecting block 1c.

[0046] When performing a pressure test, the first interface 1c1 and the second interface 1c2 are used to connect to the test object through an oil pipe, providing the test object with a stable high-pressure oil pressure source and a corresponding oil return pipe 2c. Preferably, the first interface 1c1 and the second interface 1c2 can be arranged on the vertical side of the vertical part 1b to facilitate the connection and removal of the oil pipe.

[0047] The oil tank 2 is fixedly connected to the horizontal part 1a of the equipment frame 1, and is connected with an oil supply pipe 2b and an oil return pipe 2c. The oil filling port 2a of the oil tank 2 can be arranged on the top surface of the oil tank 2, and the oil filling port 2a can also be threadedly connected with a cover body.

[0048] The manual pressure pump 4 is connected to the oil supply pipe 2b, and is used to pump the oil in the oil tank 2 into the oil supply pipe 2b. Specifically, the manual pressure pump 4 can be fixedly connected to the oil tank 2.

[0049] The oil filter 5 is also connected to the oil supply pipe 2b to filter the oil in the oil supply pipe 2b.

[0050] The overflow valve 6 is connected between the oil supply pipe 2b and the oil return pipe 2c so that the oil pumped into the oil supply pipe 2b can overflow to the oil return pipe 2c.

[0051] See also Figure 5 In some embodiments, on the oil supply pipe 2b, the overflow valve 6 is after the oil filter 5. That is, the oil in the oil supply pipe 2b is first filtered by the oil filter 5, and then provides a high-pressure oil source for the test object. When it is too high, the overflow valve 6 overflows and enters the return pipe 2c and returns to the oil tank 2.

[0052] In this way, the oil overflowing back into the oil tank 2 is also filtered by the oil filter 5 first, which is more conducive to keeping the oil in the oil tank 2 clean.

[0053] The manual reversing valve 3 has four oil ports, which are respectively connected to the first oil pipe 1c3, the second oil pipe 1c4, the oil supply pipe 2b and the oil return pipe 2c. The manual reversing valve 3 has at least a first position and a second position. The first position: the oil supply pipe 2b and the first oil pipe 1c3 form the oil supply pipe 2b, and the oil return pipe 2c and the second oil pipe 1c4 form the oil return pipe 2c. The second position: the oil supply pipe 2b and the second oil pipe 1c4 form the oil supply pipe 2b, and the oil return pipe 2c and the first oil pipe 1c3 form the oil return pipe 2c. That is, the manual reversing valve 3 can be a two-position four-way, and of course the manual reversing valve 3 can also be a three-position four-way, and then add a third position. In the third position, the ends of the first oil pipe 1c3, the second oil pipe 1c4, the oil supply pipe 2b and the oil return pipe 2c on the manual reversing valve 3 are blocked and not connected.

[0054] See also Figure 3 and Figure 5 , the relief valve 6 and the manual reversing valve 3 can be connected to the oil circuit block 11. The detailed oil circuit in the oil circuit block 11 is based on Figure 5The oil supply pipe 2b includes the oil pipe between the oil tank 2 and the manual pressure pump 4, the oil pipe between the manual pressure pump 4 and the oil filter 5, and the oil circuit block 11. The oil supply pipe 2b includes the oil pipe between the oil tank 2 and the manual pressure pump 4, the oil pipe between the manual pressure pump 4 and the oil filter 5, and part of the oil circuit on the oil circuit block 11, and the oil return pipe 2c is directly provided on the part of the oil circuit on the oil circuit block 11.

[0055] See also Figure 1 and Figure 2 In some embodiments, the horizontal portion 1a of the equipment frame 1 is further fixed with a support frame 1a2, the oil tank 2 is fixed on the top of the support frame 1a2, and the oil inlet of the oil supply pipe 2b (i.e., the connection port of the oil pipe between the oil tank 2 and the manual pressure pump 4 on the oil tank 2) is connected to the bottom surface of the oil tank 2. That is, the oil tank 2 is lifted up through the support frame 1a2, so that the bottom surface of the oil tank 2 is vacant, so that the oil inlet of the oil supply pipe 2b can be connected to the bottom surface of the oil tank 2.

[0056] In this way, the manual pressure pump 4 can be used more conveniently and labor-savingly to pump the oil in the oil tank 2 into the oil supply pipe 2b.

[0057] See also Figure 1 and Figure 2 In some embodiments, the aircraft engine static pressure relief device further includes a booster rod 9. The booster rod 9 is detachably fixed to the equipment frame 1. Specifically, two clips 9a for mounting the booster rod 9 may be fixedly provided on the equipment frame 1. In the disassembled state, one end of the booster rod 9 may also be inserted into the handle of the manual pressure relief pump 4. Furthermore, the two clips 9a may be fixedly provided on the support frame 1a2, and the position is relatively close to the manual pressure relief pump 4, which is also relatively quick and convenient to use.

[0058] In this way, the handle of the manual pressure pump 4 is extended by the force-adding rod 9, and the force arm of the manual force acting on the handle is extended, which saves more effort.

[0059] See also Figure 2 and Figure 5 In some embodiments, the oil tank 2 further has at least one of the following configurations. Configuration 1: a liquid level gauge 2e is provided on the oil tank 2. Configuration 2: an air filter 2f is provided on the oil tank 2. Configuration 3: a first oil outlet 2g with a valve is provided on the oil tank 2.

[0060] A level meter 2e is provided to intuitively know the amount of oil remaining in the oil tank 2. An air filter 2f is provided, and a manual pressure pump 4 draws oil from the oil tank 2. The air entering the oil tank 2 will be filtered by the air filter 2f to ensure the cleanliness of the oil in the oil tank 2. A first oil discharge port 2g is provided, and the oil in the oil tank 2 can be discharged by opening the valve.

[0061] See also Figure 4 and Figure 5 The two pressure gauges 7 are connected to the first oil pipe 1c3 and the second oil pipe 1c4 respectively to measure the pressure of the oil in the first oil pipe 1c3 and the second oil pipe 1c4 respectively. Specifically, the two pressure gauges 7 can be connected to the connection block 1c.

[0062] The pressure differential gauge 8 is connected between the first oil pipe 1c3 and the second oil pipe 1c4 to measure the pressure difference of the oil in the first oil pipe 1c3 and the second oil pipe 1c4. Specifically, the pressure differential gauge 8 can also be connected to the connection block 1c.

[0063] In some implementations, the two pressure gauges 7 and the differential pressure gauge 8 are both installed on the horizontal top surface of the vertical portion 1 b of the equipment rack 1 .

[0064] In this way, it is convenient and intuitive to see the data on the two pressure gauges 7 and the pressure differential gauge 8 together.

[0065] In some embodiments, the horizontal portion 1a of the equipment rack 1 is also provided with an oil collecting tank structure 1a3. Specifically, the horizontal portion 1a is in a box shape, and a second oil discharge port is provided on a side wall of one side. Each connection point on the first oil pipe 1c3, the second oil pipe 1c4, the oil supply pipe 2b and the oil return pipe 2c is covered by the oil collecting tank structure 1a3.

[0066] In this way, the oil collecting tank structure 1a3 is used to collect possible pipeline seepage and oil leakage, which is convenient for recycling and can also keep the use environment clean.

[0067] In some embodiments, the aircraft engine static pressure device further comprises a ball valve 10, which is connected to the first oil pipe 1c3. Specifically, a joint of the ball valve 10 can be installed on the connection block 1c, connected to the first interface 1c1, and the first oil pipe 1c3 is connected to another joint of the ball valve 10.

[0068] In this way, the ball valve 10 can be used as an on-off valve, which is convenient for control during the pressure test.

Claims

1. An aircraft engine static pressure device, characterized in that: include: The equipment rack (1) comprises: a horizontal part (1a) and a vertical part (1b); The bottom surface of the horizontal part (1a) is provided with casters (1a1); the vertical part (1b) is provided with a first interface (1c1) and a second interface (1c2), and the first interface (1c1) and the second interface (1c2) are respectively connected to a first oil pipe (1c3) and a second oil pipe (1c4); An oil tank (2) is fixed to the horizontal part (1a) of the equipment frame (1) and is connected to an oil supply pipe (2b) and an oil return pipe (2c); A manual reversing valve (3), wherein four oil ports are respectively connected to a first oil pipe (1c3), a second oil pipe (1c4), an oil supply pipe (2b) and an oil return pipe (2c); at least a first working position: the oil supply pipe (2b) and the first oil pipe (1c3) form an oil supply pipe (2b) path, and the oil return pipe (2c) and the second oil pipe (1c4) form an oil return pipe (2c) path; a second working position: the oil supply pipe (2b) and the second oil pipe (1c4) form an oil supply pipe (2b) path, and the oil return pipe (2c) and the first oil pipe (1c3) form an oil return pipe (2c) path; A manual pressure pump (4) is connected to the oil supply pipe (2b) to pump the oil in the oil tank (2) into the oil supply pipe (2b); An oil filter (5) is connected to the oil supply pipe (2b) to filter the oil pumped into the oil supply pipe (2b); An overflow valve (6) is connected between the oil supply pipe (2b) and the oil return pipe (2c) so that the oil pumped into the oil supply pipe (2b) can overflow to the oil return pipe (2c); Two pressure gauges (7), respectively connected to the first oil pipe (1c3) and the second oil pipe (1c4); The differential pressure gauge (8) is connected between the first oil pipe (1c3) and the second oil pipe (1c4).

2. The static pressure device for an aircraft engine according to claim 1, characterized in that: The horizontal portion (1a) of the equipment frame (1) is also provided with an oil collecting trough structure (1a3); each connection point on the first oil pipe (1c3), the second oil pipe (1c4), the oil supply pipe (2b) and the oil return pipe (2c) is covered by the oil collecting trough structure (1a3).

3. The static pressure device for an aircraft engine according to claim 1, characterized in that: The horizontal part (1a) of the equipment frame (1) is also fixedly provided with a support frame (1a2), and the oil tank (2) is fixed to the top of the support frame (1a2); the oil inlet of the oil supply pipe (2b) is connected to the bottom surface of the oil tank (2).

4. The static pressure device for an aircraft engine according to claim 1, characterized in that: The two pressure gauges (7) and the pressure differential gauge (8) are both fixedly mounted on the horizontal top surface of the vertical portion (1b) of the equipment frame (1).

5. The aircraft engine static pressure device according to claim 1, characterized in that: It also includes a ball valve (10) connected to the first oil pipe (1c3).

6. The aircraft engine static pressure device according to claim 1, characterized in that: On the oil supply pipe (2b), the overflow valve (6) is located after the oil filter (5).

7. The aircraft engine static pressure device according to claim 1, characterized in that: The oil tank (2) also has at least one of the following arrangements: arrangement one: a liquid level gauge (2e) is arranged on the oil tank (2); arrangement two: an air filter (2f) is arranged on the oil tank (2); arrangement three: a first oil discharge port (2g) with a valve is arranged on the oil tank (2).

8. The aircraft engine static pressure device according to claim 1, characterized in that: It also includes a force rod (9); the force rod (9) is detachably fixed to the equipment frame (1); in a detached state, one end of the force rod (9) can be inserted into the handle of a manual pressure pump (4).

Images