Straight-through integrated high-altitude valve device of aero-engine lubricating system

Abstract

The invention discloses a straight-through integrated high-altitude valve device of an aero-engine lubricating system. Two oil pipes which are coaxially distributed are correspondingly communicated with an air inlet end and an air outlet end at the two ends of a diaphragm capsule mounting shell in an inserted mode. The two oil pipes can be coaxially connected to an air inlet end and an air outlet end at the two ends of the diaphragm capsule mounting shell; through the components such as a spring valve spring, a spring valve, a diaphragm capsule assembly, a diaphragm capsule valve, a diaphragm capsule valve spring and the like which are coaxially distributed in a diaphragm capsule mounting shell and a valve outer shell, the pressure of a lubricating oil cavity communicated with the air inlet end of the diaphragm capsule mounting shell is controlled, is not reduced along with the increase of the height, and is maintained within a certain range; the problem that coaxial oil pipes need to be bent and butted due to the fact that a valve control assembly and an air inlet end are vertically distributed is solved.

Description

TECHNICAL FIELD

[0001] The application relates to an aviation engine lubricating system straight-through integrated high-altitude valve device and belongs to the technical field of aviation engines. BACKGROUND

[0002] The high-altitude valve is one of main components of the aviation engine lubricating system, and mainly functions to ensure normal operation of the aviation engine lubricating system in the whole flight envelope, and the lubricating oil cavity pressure needs to be kept within a certain range. Therefore, the high-altitude valve is arranged at the end where the engine accessory case is communicated with the atmosphere, and the high-altitude valve senses the local and current atmospheric pressure with the change of the engine flight height, changes the flow area of the high-altitude valve by changing the opening degree of the high-altitude valve, thereby changing the flow resistance of the high-altitude valve, so as to adjust the lubricating oil cavity pressure. Therefore, reasonable design of the high-altitude valve can keep the engine lubricating oil cavity pressure within a certain range in the whole flight envelope, and is crucial to the safety and reliability of the engine and the aircraft.

[0003] The existing high-altitude valve (see Chinese patent publication No. CN115949510A) has a vertical distribution of the valve control assembly and the air inlet end, so that the coaxial oil pipe needs to be bent and connected. SUMMARY

[0004] To solve the above technical problems, the application provides an aviation engine lubricating system straight-through integrated high-altitude valve device.

[0005] The application is achieved by the following technical scheme.

[0006] The application provides an aviation engine lubricating system straight-through integrated high-altitude valve device, which comprises: A diaphragm box mounting shell with coaxially distributed air inlet ends and air outlet ends at two ends is arranged; A valve outer shell is arranged in the diaphragm box mounting shell.

[0007] The valve outer shell and the diaphragm box mounting shell are fixedly connected through sealing ring sealing.

[0008] The diaphragm box mounting shell end portion with the sealing ring is provided with flow-through holes, and the flow-through holes are annularly and intervally distributed; the valve outer shell away from the sealing ring is provided with inner flow channel openings and outer flow channel openings, and the plurality of circumferentially and intervally distributed inner flow channel openings are arranged in the plurality of circumferentially and intervally distributed outer flow channel openings.

[0009] The diaphragm box mounting shell and the valve outer shell are coaxially distributed with spring valve springs, spring valves, diaphragm box assemblies, diaphragm valves and diaphragm valve springs inside.

[0010] The valve outer shell is slidably sleeved with spring valves.

[0011] The spring valve is pressed against the outer flow channel opening by adjusting pad A and the spring valve spring abutting against the inner step of the diaphragm box mounting shell.

[0012] The valve outer shell inner step is slidably sleeved with a diaphragm valve, the diaphragm valve can be pressed against the inner flow channel opening for sealing, the diaphragm valve is abutted against the inner mounting groove of the diaphragm box mounting shell through a diaphragm box assembly, the diaphragm box assembly is normally internally vacuumized and axially expanded with the increase of height.

[0013] The diaphragm valve is below the valve outer shell inner step through the diaphragm valve spring and adjusting pad B.

[0014] The beneficial effects of the present application are that two oil pipes distributed on the same axis correspond to the air inlet end and the exhaust end of the diaphragm box mounting shell and are connected in communication; the two oil pipes can be connected to the air inlet end and the exhaust end of the diaphragm box mounting shell in a coaxial state; through the components such as the spring valve spring, the spring valve, the diaphragm box assembly, the diaphragm valve, and the diaphragm valve spring distributed coaxially inside the diaphragm box mounting shell and the valve outer shell, the pressure of the oil chamber connected with the air inlet end of the diaphragm box mounting shell is controlled and is not reduced with the increase of the height, and is maintained within a certain range, thereby solving the problem that the valve control components and the air inlet end are vertically distributed, and the oil pipes on the same axis need to be bent and connected. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 is the front view of the present application; Figure 2 is the front view of the present application when the inner flow channel is opened in the ground and low altitude state; Figure 3 is the front view of the present application when the inner and outer flow channels are closed in the high altitude state; Figure 4 is the front view of the present application when the outer flow channel is opened in the high altitude state; In the figure: 1-diaphragm box mounting shell; 11-flowing hole; 2-sealing ring; 3-valve outer shell; 31-inner flow channel opening; 32-outer flow channel opening; 4-diaphragm box assembly; 5-diaphragm valve; 6-diaphragm valve spring; 7-adjusting pad A; 8-adjusting pad B; 9-spring valve; 10-spring valve spring. DETAILED DESCRIPTION

[0016] The technical solutions of the present application are further described below, but the scope of protection is not limited to the description.

[0017] As Figures 1 to 4 shown.

[0018] The present application is an aviation engine lubrication system straight-through integrated high altitude valve device, which comprises: The membrane box mounting shell 1 is provided with a communication port at the horizontal two ends, the horizontal left and right ends of the membrane box mounting shell 1 correspond to form an air inlet end and an air outlet end, a valve outer shell 3 is mounted in the membrane box mounting shell 1, and the valve outer shell 3 is sealed and packaged with the membrane box mounting shell 1 through a sealing ring 2. The outer diameter circle of the valve outer shell 3 and the membrane box mounting shell 1 is fixed by screwing through a bolt and a nut.

[0019] The membrane box mounting shell 1 is provided with a communication port at the horizontal two ends, the horizontal left and right ends of the membrane box mounting shell 1 correspond to form an air inlet end and an air outlet end, a valve outer shell 3 is mounted in the membrane box mounting shell 1, and the valve outer shell 3 is sealed and packaged with the membrane box mounting shell 1 through a sealing ring 2. The outer diameter circle of the valve outer shell 3 and the membrane box mounting shell 1 is fixed by screwing through a bolt and a nut.

[0020] The membrane box mounting shell 1 is provided with a communication port at the horizontal two ends, the horizontal left and right ends of the membrane box mounting shell 1 correspond to form an air inlet end and an air outlet end, a valve outer shell 3 is mounted in the membrane box mounting shell 1, and the valve outer shell 3 is sealed and packaged with the membrane box mounting shell 1 through a sealing ring 2. The outer diameter circle of the valve outer shell 3 and the membrane box mounting shell 1 is fixed by screwing through a bolt and a nut.

[0021] The membrane box mounting shell 1 is provided with a communication port at the horizontal two ends, the horizontal left and right ends of the membrane box mounting shell 1 correspond to form an air inlet end and an air outlet end, a valve outer shell 3 is mounted in the membrane box mounting shell 1, and the valve outer shell 3 is sealed and packaged with the membrane box mounting shell 1 through a sealing ring 2. The outer diameter circle of the valve outer shell 3 and the membrane box mounting shell 1 is fixed by screwing through a bolt and a nut.

[0022] As shown in the drawings, Figure 2 The membrane box mounting shell 1 is provided with a communication port at the horizontal two ends, the horizontal left and right ends of the membrane box mounting shell 1 correspond to form an air inlet end and an air outlet end, a valve outer shell 3 is mounted in the membrane box mounting shell 1, and the valve outer shell 3 is sealed and packaged with the membrane box mounting shell 1 through a sealing ring 2. The outer diameter circle of the valve outer shell 3 and the membrane box mounting shell 1 is fixed by screwing through a bolt and a nut.

[0023] As shown in the drawings, Figure 3As shown, due to the vacuum inside the bellows assembly 4, the bellows assembly 4 starts to expand axially with the increase of altitude, pushing the bellows valve 5 to move towards the closing end until the bellows valve 5 presses against the inner flow passage port 31 to completely close it, at which time the pressure of the oil chamber connected to the air inlet end no longer decreases with the increase of altitude, and is maintained within a certain range.

[0024] As shown, Figure 4 As shown, due to the large rigidity of the bellows assembly 4, after the bellows valve 5 closes the inner flow passage port 31, the pressure of the oil chamber connected to the air inlet end is higher than that of the spring valve 9, the spring valve 9 overcomes the spring valve spring 10 to move towards the air outlet end to open the outer flow passage port 32 to release the pressure, and the gas and oil mixed fluid in the oil chamber is discharged from the outer flow passage port 32 and the flow-through hole 11 of the valve outer housing 1 to the air outlet end.

Claims

1. An aircraft engine lubrication system direct-through integrated high-altitude valve device, characterized in that: include: A membrane box mounting housing (1) is provided with a coaxially distributed air inlet end and an air outlet end at both ends; A valve outer shell (3) is installed in a membrane box installation shell (1).

2. The aircraft engine lubrication system direct-through integrated high-altitude valve device according to claim 1, characterized in that: The membrane box mounting housing (1) with a sealing ring (2) is provided with a flow hole (11) at the end thereof, and the flow holes (11) are multiple and distributed in an annular manner; the valve outer housing (3) away from the sealing ring (2) is provided with an inner flow channel opening (31) and an outer flow channel opening (32), and the multiple inner flow channel openings (31) distributed in a circumferentially spaced array are located within the outer flow channel openings (32) distributed in a circumferentially spaced array.

3. The aircraft engine lubrication system direct-through integrated high-altitude valve device according to claim 1, characterized in that: The membrane box installation housing (1) and the valve outer housing (3) are coaxially distributed with a spring valve spring (10), a spring valve (9), a membrane box assembly (4), a membrane box valve (5), and a membrane box valve spring (6).

4. The aircraft engine lubrication system direct-through integrated high-altitude valve device according to claim 3, characterized in that: A spring valve (9) is slidably sleeved on the outer periphery of the valve outer shell (3).

5. The aircraft engine lubrication system direct-through integrated high-altitude valve device according to claim 4, characterized in that: The spring valve (9) is pressed against the inner step of the membrane box mounting housing (1) through the adjustment pad A (7) and the spring valve spring (10), so that the spring valve (9) presses against the outer flow channel (32) to seal it.

6. The aircraft engine lubrication system direct-through integrated high-altitude valve device according to claim 4, characterized in that: The inner platform of the valve outer shell (3) can be slidably covered with a membrane box valve (5), which can press against the inner flow channel opening (31) to seal it. The membrane box valve (5) is pressed against the internal installation groove of the membrane box installation shell (1) through the membrane box assembly (4). The membrane box assembly (4) is normally vacuumed and axial expansion occurs as the height increases.

7. The aircraft engine lubrication system direct-through integrated high-altitude valve device according to claim 6, characterized in that: The diaphragm valve (5) is lower than the inner platform of the valve outer shell (3) through the diaphragm valve spring (6) and the adjustment pad B (8).

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