A gravity-type oil suction mechanism for an aircraft engine oil tank

Abstract

This invention provides a gravity-type oil suction mechanism for an aircraft engine oil tank, comprising an oil tank; an oil supply pipe is provided inside the oil tank, with an upper T-shaped pipe and a lower T-shaped pipe connected to its upper and lower ends respectively; one side of the oil supply pipe is connected to the oil tank through an oil bushing, and the other end of the oil supply pipe is connected to the inner wall of the oil tank through the lower T-shaped pipe. This invention features a simpler and more compact structure, is easy to install, and can be adapted to oil tanks of various engine models; the movement of two steel balls ensures that the oil suction port, located below the oil surface, is always open, guaranteeing normal oil intake for the engine; the T-shaped pipe passage adopts a petal-shaped structure to ensure smooth movement of the steel balls and unobstructed oil flow; an oil filter is installed at the oil suction port to prevent metal impurities from entering the T-shaped pipe and the oil pump; the oil suction pipes are symmetrically arranged to ensure that an oil suction port is always below the oil surface in all flight attitudes.

Description

Technical Field

[0001] This invention relates to a gravity-type oil suction mechanism for an aircraft engine oil tank, belonging to the technical field of aircraft engine lubrication systems. Background Technology

[0002] As a key component of the aircraft engine lubrication system, the oil tank's primary function is to store a specified amount of lubricating oil circulating within the system and to replenish it based on oil consumption. The oil suction mechanism, an important component of the oil tank, is installed inside. Its main function is to ensure that the oil suction port is always positioned at the bottom of the oil tank, guaranteeing that the engine's oil tank can continuously draw oil through the suction pipe during level flight, pitching up, diving, and inverted flight, thus preventing prolonged periods of interrupted lubrication.

[0003] Currently, there are three main types of oil suction mechanisms for aero-engine oil tanks: bottom suction port, flexible suction head, and rotary suction mechanism. Among them, the bottom suction port can only suck oil from the bottom of the oil tank, and the suction range is relatively narrow, which cannot fully guarantee uninterrupted oil suction for the engine in various attitudes. The flexible suction head is a hose counterweight suction head, which has high requirements for the internal space of the oil tank and a complex movement trajectory. The rotary suction mechanism has a complex structure and a high probability of jamming. Summary of the Invention

[0004] To solve the above-mentioned technical problems, the present invention provides a gravity-type oil suction mechanism for an aircraft engine oil tank.

[0005] The present invention is achieved through the following technical solutions.

[0006] This invention provides a gravity-type oil suction mechanism for an aircraft engine oil tank, comprising an oil tank; an oil supply pipe is provided inside the oil tank, with an upper T-shaped pipe and a lower T-shaped pipe respectively connected to its upper and lower ends; one side of the oil supply pipe is connected to the oil tank through an oil-passing bushing, and one end of the oil supply pipe is connected to the inner wall of the oil tank through the lower T-shaped pipe; an upper steel ball and a lower steel ball are respectively placed inside the upper T-shaped pipe and the lower T-shaped pipe, and the diameters of the upper steel ball and the lower steel ball are larger than the diameter of the oil supply pipe; the vertical section of the upper T-shaped pipe is the upper oil suction pipe, and an upper oil filter is provided inside the upper oil suction pipe; the vertical section of the lower T-shaped pipe is the lower oil suction pipe, and a lower oil filter is provided inside the lower oil suction pipe.

[0007] The T-shaped openings of the upper and lower T-shaped tubes are not in the same direction.

[0008] The oil supply pipe has a T-shaped structure.

[0009] The contact surface between the oil-passing bushing and the oil supply pipe is provided with a first sealing ring, and the contact surface between the oil-passing bushing and the lubricating oil tank is provided with a second sealing ring.

[0010] The lower T-tube is provided with a sealing ring groove at its end, and the inner wall of the oil supply pipe is provided with a mounting seat.

[0011] The diameter of the middle section of the oil supply pipe is smaller than the diameter of the upper and lower steel balls, while the diameter of the end section of the oil supply pipe is larger than the diameter of the upper and lower steel balls.

[0012] The diameters of the upper T-tube and the lower T-tube are larger than the diameters of the upper steel ball and the lower steel ball.

[0013] The upper T-tube and the lower T-tube are equipped with petal-shaped structures.

[0014] Both the upper and lower oil filters are made of metal woven mesh.

[0015] One end of the lower T-tube is connected to the mounting base, and a third sealing ring is provided between the lower T-tube and the mounting base.

[0016] The advantages of this invention are as follows: the structure is simpler and more compact, easy to install, and adaptable to various engine oil tank models; the movement of the double steel balls ensures that the oil suction port, located below the liquid surface, is always open, ensuring normal oil intake by the engine; the T-tube passage adopts a petal-shaped structure to ensure smooth movement of the steel balls and unobstructed flow of lubricating oil; an oil filter is installed at the oil suction port to prevent metal impurities from entering the T-tube and the lubricating oil pump; the oil suction pipe is symmetrically arranged to ensure that there is always an oil suction port below the lubricating oil surface in all flight attitudes. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of the present invention;

[0018] Figure 2 This is a schematic diagram of the petal structure of the T-shaped tube in this invention;

[0019] Figure 3 This is a schematic diagram of the petal structure of the T-shaped tube of the present invention;

[0020] Figure 4 This is a schematic diagram of the position of the steel ball and the oil suction path during level flight;

[0021] Figure 5 This is a schematic diagram showing the position of the steel ball and the oil suction path during the upward flight process;

[0022] Figure 6 This is a schematic diagram of the position of the steel ball and the oil suction path during flight at a maximum elevation angle of 105°;

[0023] Figure 7 This is a schematic diagram of the position of the steel ball and the oil suction path during the downward flight.

[0024] Figure 8This is a schematic diagram of the position of the steel ball and the oil suction path during a vertical dive flight.

[0025] Figure 9 This is a schematic diagram showing the position of the steel ball and the oil suction path during inverted flight;

[0026] In the diagram: 1-oil supply pipe, 2-upper T-pipe, 3-lower T-pipe, 4-upper steel ball, 5-lower steel ball, 6-upper suction pipe, 7-lower suction pipe, 8-upper oil filter, 9-lower oil filter, 10-oil passing bushing, 11-first sealing ring, 12-second sealing ring, 13-third sealing ring, 14-lubricating oil tank. Detailed Implementation

[0027] The technical solution of the present invention is further described below, but the scope of protection is not limited to what is described.

[0028] Example 1

[0029] like Figure 1 As shown, a gravity-type oil suction mechanism for an aircraft engine oil tank includes an oil tank 14; an oil supply pipe 1 is provided inside the oil tank 14, with an upper T-shaped pipe 2 and a lower T-shaped pipe 3 connected to its upper and lower ends respectively; one side of the oil supply pipe 1 is connected to the oil tank 14 through an oil-passing bushing 10, and one end of the oil supply pipe 1 is connected to the inner wall of the oil tank 14 through the lower T-shaped pipe 3; an upper steel ball 4 and a lower steel ball 5 are respectively placed inside the upper T-shaped pipe 2 and the lower T-shaped pipe 3, and the diameters of the upper steel ball 4 and the lower steel ball 5 are larger than the diameter of the oil supply pipe 1; the vertical section of the upper T-shaped pipe 2 is an upper oil suction pipe 6, and an upper oil filter 8 is provided inside the upper oil suction pipe 6; the vertical section of the lower T-shaped pipe 3 is a lower oil suction pipe 7, and a lower oil filter 9 is provided inside the lower oil suction pipe 7.

[0030] The T-shaped openings of the upper T-tube 2 and the lower T-tube 3 are not in the same direction.

[0031] The oil supply pipe 1 has a T-shaped structure. The diameter of the middle part of the oil supply pipe 1 is smaller than the diameter of the upper steel ball 4 and the lower steel ball 5, which can fix the position of the steel ball and prevent the steel ball from falling. The diameter of the end of the oil supply pipe 1 is larger than the diameter of the upper steel ball 4 and the lower steel ball 5, which facilitates the installation and movement of the steel ball.

[0032] The contact surface between the oil-passing bushing 10 and the oil supply pipe 1 is provided with a first sealing ring 11, and the contact surface between the oil-passing bushing 10 and the lubricating oil tank 14 is provided with a second sealing ring 12.

[0033] Preferably, the oil bushing 10 has a double sealing ring structure at both ends to ensure installation and sealing.

[0034] Furthermore, the oil bushing 10 is connected to the lubricating oil pump through an external pipeline to ensure a secure seal and installation.

[0035] The end of the lower T-tube 3 is provided with a sealing ring groove, and the inner wall of the oil supply pipe 1 is provided with a mounting seat.

[0036] The diameters of the upper T-tube 2 and the lower T-tube 3 are larger than the diameters of the upper steel ball 4 and the lower steel ball 5, which facilitates the movement of the steel balls.

[0037] The upper T-tube 2 and lower T-tube 3 are provided with petal-shaped structures, such as Figure 2 and 3 As shown, this design prevents the steel ball from falling into the lubricating oil tank 14, ensures smooth movement of the steel ball, and guarantees unobstructed flow of lubricating oil, enabling normal oil absorption.

[0038] Both the upper oil filter 8 and the lower oil filter 9 are made of metal woven mesh, which serves to filter impurities inside the lubricating oil tank 14, ensuring that metal impurities do not enter the oil supply pipe 1, the upper and lower T-pipes and the lubricating oil pump, thus affecting the movement of the steel ball and the operation of the lubricating oil pump.

[0039] One end of the lower T-tube 3 is connected to the mounting base, and a third sealing ring 13 is provided between the lower T-tube 3 and the mounting base.

[0040] Example 2

[0041] like Figure 4 As shown, during the aircraft's level flight, under the influence of gravity, the upper steel ball 4 blocks the upper end of the oil supply pipe 1, and the lower steel ball 5 is placed at the bottom of the lower T-shaped pipe 3. Under the action of the lubricating oil pump, lubricating oil is drawn in through the lower suction pipe 7.

[0042] Example 3

[0043] like Figure 5 As shown, during the aircraft's pitch-up flight, under the influence of gravity, the upper steel ball 4 blocks the upper end of the oil supply pipe 1, and the lower steel ball 5 is placed at the bottom of the lower T-shaped pipe 3. Under the action of the lubricating oil pump, lubricating oil is drawn in through the lower suction pipe 7.

[0044] Example 4

[0045] like Figure 6 As shown, during the flight at the maximum pitch angle (105°), under the action of gravity, the upper steel ball 4 moves to one end of the upper T-tube 2, and the lower steel ball 5 moves to one side of the middle of the oil supply pipe 1, releasing the lubricating oil passage. Under the action of the lubricating oil pump, lubricating oil is drawn in through the lower suction pipe 7 and flows into the oil supply pipe 1 along the gap between the lower steel ball 5 and the oil supply pipe 1.

[0046] Example 5

[0047] like Figure 7 As shown, during the aircraft's downward flight, under the influence of gravity, the upper steel ball 4 blocks the upper end of the oil supply pipe 1, and the lower steel ball 5 is placed at the bottom of the lower T-shaped pipe 3. Under the action of the lubricating oil pump, lubricating oil is drawn in through the lower suction pipe 7.

[0048] Example 6

[0049] like Figure 8 As shown, during the vertical dive of the aircraft, the upper steel ball 4 and the lower steel ball 5 release the passage, and under the action of the lubricating oil pump, the lubricating oil is drawn in through the lower oil suction pipe 7 and enters the oil supply pipe 1 through the gap between the upper steel ball 4 and the oil supply pipe 1 or the upper T-shaped pipe 2.

[0050] Example 7

[0051] like Figure 9 As shown, during the inverted flight of the aircraft, under the action of gravity, the lower steel ball 5 blocks one end of the oil supply pipe 1, and the upper steel ball moves to one end of the upper T-shaped pipe 2, opening the passage. Under the action of the lubricating oil pump, lubricating oil is sucked in through the upper suction pipe 6.

[0052] Example 8

[0053] The working principle of this invention is as follows: This invention is installed on the mounting base at the bottom of the engine oil tank. As the aircraft's flight attitude changes, the upper steel ball 4 and the lower steel ball 5 can move freely in the upper T-tube 2 and the lower T-tube 3 respectively under the action of gravity, ensuring that the oil suction port located below the liquid surface is always in the open state. This ensures that the engine oil tank can normally draw oil through the oil supply pipe of the oil suction mechanism during level flight, pitching up, diving, and inverted flight, ensuring that the engine will not be in a situation where lubrication is interrupted for a long time.

Claims

1. A gravity-type oil suction mechanism for an aircraft engine oil tank, comprising an oil tank (14), characterized in that: The oil tank (14) is provided with an oil supply pipe (1), and the upper and lower ends of the oil supply pipe (1) are respectively connected to an upper T-shaped pipe (2) and a lower T-shaped pipe (3); one side of the oil supply pipe (1) is connected to the oil tank (14) through an oil bushing (10), and one end of the oil supply pipe (1) is connected to the inner wall of the oil tank (14) through the lower T-shaped pipe (3); an upper steel ball (4) and a lower steel ball (5) are respectively placed in the upper T-shaped pipe (2) and the lower T-shaped pipe (3), and the diameter of the upper steel ball (4) and the lower steel ball (5) is larger than the diameter of the oil supply pipe (1); the horizontal section of the upper T-shaped pipe (2) is an upper oil suction pipe (6), and an upper oil filter (8) is provided in the upper oil suction pipe (6); the horizontal section of the lower T-shaped pipe (3) is a lower oil suction pipe (7), and a lower oil filter (9) is provided in the lower oil suction pipe (7); The T-shaped openings of the upper T-shaped tube (2) and the lower T-shaped tube (3) are not in the same direction; the oil bushing (10) and the oil supply pipe (1) are provided with a first sealing ring (11), and the oil bushing (10) and the lubricating oil tank (14) are provided with a second sealing ring (12).

2. The gravity-type oil suction mechanism for an aircraft engine oil tank as described in claim 1, characterized in that: The oil supply pipe (1) has a T-shaped structure.

3. The gravity-type oil suction mechanism for an aircraft engine oil tank as described in claim 1, characterized in that: The lower T-tube (3) is provided with a sealing ring groove at its end, and the inner wall of the oil supply pipe (1) is provided with a mounting seat.

4. The gravity-type oil suction mechanism for an aircraft engine oil tank as described in claim 2, characterized in that: The diameter of the middle part of the oil supply pipe (1) is smaller than the diameter of the upper steel ball (4) and the lower steel ball (5), and the diameter of the end of the oil supply pipe (1) is larger than the diameter of the upper steel ball (4) and the lower steel ball (5).

5. The gravity-type oil suction mechanism for an aircraft engine oil tank as described in claim 1, characterized in that: The diameters of the upper T-tube (2) and the lower T-tube (3) are greater than the diameters of the upper steel ball (4) and the lower steel ball (5).

6. The gravity-type oil suction mechanism for an aircraft engine oil tank as described in claim 1, characterized in that: The upper T-tube (2) and lower T-tube (3) are provided with petal-shaped structures.

7. The gravity-type oil suction mechanism for an aircraft engine oil tank as described in claim 1, characterized in that: Both the upper oil filter (8) and the lower oil filter (9) are made of metal woven mesh.

8. The gravity-type oil suction mechanism for an aircraft engine oil tank as described in claim 3, characterized in that: One end of the lower T-tube (3) is connected to the mounting base, and a third sealing ring (13) is provided between the lower T-tube (3) and the mounting base.

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