Oil way cut-off device, lubricating oil system and aero-engine

Abstract

The utility model relates to the technical field of aerospace, in particular to an oil way cut-off device, a lubricating oil system and an aero-engine. The oil way cut-off device comprises a first shell, a second shell and a plugging ejector pin, the first shell is provided with an oil inlet, an oil outlet, an oil cavity and a communicating hole, the oil inlet is communicated with the oil cavity through the communicating hole, and the oil cavity is communicated with the oil outlet; the second shell at least partially extends into the oil cavity and is hermetically connected with the first shell; and the plugging ejector pin is arranged in the oil cavity and can slide relative to the first shell, the plugging ejector pin and the communicating hole are oppositely arranged, and the plugging ejector pin can stretch into or be separated from the communicating hole under the action of gravity so that the communicating hole and the oil cavity can be disconnected or communicated. When the airplane flies reversely, the blocking ejector pin and the valve body descend and move under the action of gravity to block the communicating hole, at the moment, the amount of oil flowing into the oil cavity from the oil inlet is reduced, the amount of oil entering the bearing seat is reduced to zero, and due to the fact that the bearing cavity does not supply oil any more, leakage of lubricating oil in the bearing cavity can be avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation and aerospace, and in particular to an oil circuit cut-off device, a lubricating oil system and an aviation engine. Background Art

[0002] The oil supply circuit is an important component in the engine's lubricating oil system. The main function of the lubricating oil system is to provide lubricating oil of a certain temperature and pressure to the system to lubricate and cool the engine's bearings, gear systems, etc.

[0003] Since the aircraft has inverted flight attitude and flight time requirements during flight, for components with large heat dissipation power, it is required that both oil supply and oil return can be normal during inverted flight, but for components with small heat dissipation power, the lubricating oil system supply can be cut off during inverted flight. In the prior art, a relatively complex oil return system is usually used to lubricate and cool components with different heat dissipation powers. After the lubricating oil enters the bearing cavity, the bearing is lubricated and cooled. However, the lubricating oil is easy to leak from the bearing cavity during inverted flight.

[0004] Therefore, there is an urgent need for an oil circuit cutting device to solve the above technical problems. Utility Model Content

[0005] The utility model aims to provide an oil circuit cut-off device, a lubricating oil system and an aircraft engine, which can prevent the lubricating oil from leaking when the aircraft flies backwards.

[0006] To achieve this purpose, the utility model adopts the following technical solutions:

[0007] In a first aspect, an oil circuit cut-off device is provided, comprising:

[0008] A first housing, wherein the first housing has an oil inlet, an oil outlet, an oil chamber and a communicating hole, wherein the oil inlet is communicated with the oil chamber through the communicating hole, and the oil chamber is communicated with the oil outlet;

[0009] a second housing, the second housing at least partially extending into the oil chamber and being sealedly connected to the first housing;

[0010] a blocking ejector pin, which is disposed in the oil chamber and can slide relative to the first housing, the blocking ejector pin being disposed opposite to the communicating hole, and the blocking ejector pin can extend into or out of the communicating hole under the action of gravity to disconnect or connect the communicating hole with the oil chamber;

[0011] The valve body, the second shell has a receiving groove arranged opposite to the connecting hole, the valve body is arranged in the receiving groove and can approach or move away from the connecting hole under the action of gravity, the side of the valve body facing the connecting hole can fit with the bottom of the oil chamber, and the blocking ejector pin is installed at the end of the valve body facing the connecting hole.

[0012] As a preferred technical solution of the above-mentioned oil circuit cutting off device, a mounting groove is provided at one end of the valve body facing the connecting hole, the blocking ejector pin is installed in the mounting groove and protrudes from the mounting groove, and the distance between the valve body and the bottom of the oil chamber is greater than the protruding length of the blocking ejector pin.

[0013] As a preferred technical solution of the above-mentioned oil circuit cutting device, the valve body is arranged to protrude from the accommodating groove.

[0014] As a preferred technical solution of the above-mentioned oil circuit cutting device, it also includes a guide rod, the first shell is fixedly mounted with the guide rod, the valve body is provided with a guide hole, the guide rod extends into the guide hole and the valve body can move relative to the guide rod.

[0015] As a preferred technical solution of the above oil circuit cutting device, it also includes a lubricating oil pressure sensor, and the lubricating oil pressure sensor is arranged on the first housing to detect the lubricating oil pressure of the oil inlet.

[0016] As a preferred technical solution of the above-mentioned oil circuit cutting device, the first housing is threadedly connected to the second housing.

[0017] As a preferred technical solution of the above oil circuit cutting device, the first housing and the second housing are interference connected.

[0018] As a preferred technical solution of the above-mentioned oil circuit cutting device, the oil inlet and the oil outlet are arranged on the same side.

[0019] In a second aspect, a lubricating oil system is provided, comprising the oil circuit cutting device described in any one of the above schemes.

[0020] In a third aspect, an aircraft engine is provided, comprising the lubricating oil system described in the above scheme.

[0021] The utility model has at least the following beneficial effects:

[0022] The oil circuit cut-off device, lubricating oil system and aircraft engine provided by the embodiments of the utility model are in an inverted state when the aircraft is flying inverted, and the blocking ejector pin and the valve body both move downward under the action of gravity to block the connecting hole. At this time, the amount of oil flowing into the oil chamber through the oil inlet is reduced, and the amount of oil passing through the oil outlet is also greatly reduced, so that the amount of oil entering the bearing seat is reduced to 0. Since the bearing chamber is no longer supplied with oil, there is no need to design a complex oil return system for oil return. The bearing lubrication relies on the residual oil in the bearing seat to be splashed and cooled under the action of the oil throwing plate, which can not only ensure the lubricating oil cooling function for inverted flight in a short time, but also avoid lubricating oil leakage in the bearing chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] To more clearly illustrate the technical solutions in the embodiments of the present utility model, the following will briefly introduce the drawings required for description in the embodiments of the present utility model. Obviously, the drawings described below are only some embodiments of the present utility model. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on the content of the embodiments of the present utility model and these drawings.

[0024] Figure 1 It is a cross-sectional view of the oil circuit cut-off device provided by the embodiment of the present utility model.

[0025] In the figure:

[0026] 1. First housing; 11. Oil inlet; 12. Oil outlet; 13. Oil chamber; 14. Communication hole; 2. Second housing; 21. Accommodating groove; 3. Plugging thimble; 4. Valve body; 41. Installation groove; 5. Guide rod; 6. Lubricating oil pressure sensor. Specific embodiments

[0027] The following will further elaborate on the present utility model in conjunction with the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the present utility model, rather than limiting the present utility model. Additionally, it should be noted that for the sake of description, only the parts related to the present utility model rather than all the structures are shown in the drawings.

[0028] In the description of the present utility model, unless otherwise clearly defined and limited, the terms "connected", "connected to", and "fixed" shall be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0029] In the present utility model, unless otherwise clearly defined and limited, the first feature being "above" or "below" the second feature may include the direct contact between the first and second features, or may include the situation where the first and second features are not in direct contact but in contact through other features between them. Moreover, the first feature being "above", "above the top", and "on the top" of the second feature includes the first feature being directly above and obliquely above the second feature, or merely indicating that the first feature has a higher horizontal height than the second feature. The first feature being "below", "below the bottom", and "under the bottom" of the second feature includes the first feature being directly below and obliquely below the second feature, or merely indicating that the first feature has a lower horizontal height than the second feature.

[0030] In the description of this embodiment, the terms "upper", "lower", "right", etc., are based on the directions or positions shown in the drawings, and are only for the convenience of description and simplified operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0031] The utility model provides an oil circuit cutting device, which can prevent lubricating oil from leaking from a bearing cavity when an aircraft flies backwards.

[0032] like Figure 1 As shown, the oil circuit cutting device includes a first housing 1, a second housing 2, a valve body 4 and a blocking ejector pin 3, wherein the first housing 1 has an oil inlet 11, an oil outlet 12, an oil chamber 13 and a connecting hole 14, the oil inlet 11 is connected to the oil chamber 13 through the connecting hole 14, and the oil chamber 13 is connected to the oil outlet 12; the second housing 2 at least partially extends into the oil chamber 13 and is sealed and connected to the first housing 1; the blocking ejector pin 3 is arranged in the oil chamber 13 and can slide relative to the first housing 1, the blocking ejector pin 3 and the connecting hole 14 are arranged opposite to each other, and the blocking ejector pin 3 can extend into or out of the connecting hole 14 under the action of gravity to disconnect or connect the connecting hole 14 with the oil chamber 13. The second housing 2 has a receiving groove 21 arranged opposite to the communicating hole 14. The valve body 4 is arranged in the receiving groove 21 and can approach or move away from the communicating hole 14 under the action of gravity. The side of the valve body 4 facing the communicating hole 14 can fit with the bottom of the oil chamber 13. The blocking ejector pin 3 is installed at the end of the valve body 4 facing the communicating hole 14. In this way, the communicating hole 14 is blocked by the side of the valve body 4 facing the communicating hole 14 and the blocking ejector pin 3, which can prevent the oil from flowing out of the oil outlet 12 after the blocking ejector pin 3 is flushed open, and further improve the blocking and cutting effect.

[0033] The oil circuit cutting device provided by the embodiment of the utility model is in an inverted state when the aircraft is flying inverted. The blocking ejector pin 3 and the valve body 4 both move downward under the action of gravity to block the connecting hole 14. At this time, the amount of oil flowing into the oil chamber 13 from the oil inlet 11 is reduced, and the amount of oil passing through the oil outlet 12 is also greatly reduced, so that the amount of oil entering the bearing seat is reduced to 0. Since the bearing chamber is no longer supplied with oil, there is no need to design a complex oil return system for oil return. The bearing lubrication relies on the residual oil in the bearing seat to be splashed and cooled under the action of the oil throwing plate, which can not only ensure the oil cooling function in the inverted flight in a short time, but also avoid the oil leakage of the bearing chamber.

[0034] In some embodiments, a mounting groove 41 is provided at one end of the valve body 4 facing the connecting hole 14, and the blocking ejector pin 3 is installed in the mounting groove 41 and protrudes from the mounting groove 41, so that the valve body 4 provides support for the blocking ejector pin 3, and the distance between the valve body 4 and the bottom of the oil chamber 13 is greater than the protruding length of the blocking ejector pin 3. Such a setting can ensure that the lubricating oil of the oil circuit cut-off device enters the oil chamber 13 through the connecting hole 14 from the inlet during the normal flight of the aircraft and flows out through the oil outlet 12, and the connecting hole 14 is blocked when the aircraft is flying inverted to prevent the lubricating oil from leaking from the bearing cavity.

[0035] In some embodiments, the valve body 4 is arranged to protrude from the receiving groove 21. Such an arrangement ensures that the valve body 4 can contact one end of the oil chamber 13 close to the connecting hole 14, the second housing 2 blocks the oil chamber 13, and the valve body 4 is arranged in the oil chamber 13 and can reciprocate in the oil chamber 13 due to position changes, so that the blocking ejector pin 3 can block or escape from the connecting hole 14 under the drive of the valve body 4.

[0036] In order to prevent the valve body 4 from being offset during movement, causing the blocking ejector pin 3 and the connecting hole 14 to be offset and unable to effectively block the connecting hole 14, in some embodiments, the oil circuit cut-off device further includes a guide rod 5, the first housing 1 is fixedly mounted with the guide rod 5, the valve body 4 is provided with a guide hole, the guide rod 5 extends into the guide hole and the valve body 4 can move relative to the guide rod 5. In this way, the guide rod 5 can provide guidance for the movement of the valve body 4 to prevent the valve body 4 from being offset during movement. The cross-sectional shape of the guide rod 5 is the same as the shape of the guide hole, and the guide rod 5 and the guide hole are interference-fitted to achieve the fixation of the guide rod 5.

[0037] In some embodiments, the oil circuit cut-off device further includes a lubricating oil pressure sensor 6, which is disposed on the first housing 1 to detect the lubricating oil pressure of the oil inlet 11. The setting of the lubricating oil pressure sensor 6 can detect the oil pressure to determine whether the oil pressure meets the impact on the valve body 4 and the blocking ejector pin 3 during inverted flight, so as to avoid the lubricating oil pressure being too high and thus breaking the valve body 4 and the blocking ejector pin 3. The lubricating oil pressure can be precisely controlled by monitoring the lubricating oil pressure through the lubricating oil pressure sensor 6. It should be noted that the lubricating oil pressure sensor 6 is connected to the control board. In this embodiment, the control board can be a centralized or distributed controller. For example, the controller can be a single single-chip microcomputer or a distributed plurality of single-chip microcomputers. The control program can be run in the single-chip microcomputer to control each component to realize its function.

[0038] In some embodiments, the first shell 1 is threadedly connected to the second shell 2 , and a sealing gasket is further disposed between the first shell 1 and the second shell 2 . The sealing gasket and the thread can seal the first shell 1 and the second shell 2 .

[0039] In some other embodiments, the first housing 1 and the second housing 2 are connected by interference fit. A gasket is provided between the first housing 1 and the second housing 2, and the gasket and the interference fit can seal and connect the first housing 1 and the second housing 2.

[0040] To facilitate the layout of the pipeline, in some embodiments, the oil inlet 11 and the oil outlet 12 are arranged on the same side. Of course, in other embodiments, the oil inlet 11 and the oil outlet 12 can be oppositely arranged on both sides of the first housing 1.

[0041] When the aircraft is flying in a normal attitude, the engine oil supply pipeline is connected to the oil inlet 11, and the lubricating oil enters the first housing 1 from the oil inlet 11, then enters the second housing 2 through the communication hole 14, and is then transported to the bearing cavity of the engine through the oil outlet 12.

[0042] When the aircraft is flying in an inverted attitude, the valve body 4 slides down along the guide rod 5, and the plugging thimble 3 presses against the communication hole 14 to close the communication hole 14. The weight of the valve body 4 needs to match the area of the communication hole 14 and the lubricating oil pressure in the first housing 1 to ensure that under the action of gravity, the valve body 4 can block the communication hole 14. At this time, the lubricating oil supply is cut off, and there is no longer lubricating oil supply to the bearing seat lubricating oil cavity. The bearing is lubricated by the remaining oil in the bearing seat under the action of the oil slinger for splash cooling. Since there is no longer lubricating oil supply to the bearing seat lubricating oil cavity, even if a complex oil return pipeline is not designed in the inverted attitude, there will be no lubricating oil leakage in the lubricating oil cavity, and the structure is simple and reliable.

[0043] The present invention also provides an oil lubrication system, including the oil circuit cutting device provided by the embodiments of the present invention. When the aircraft is flying in an inverted attitude, the oil circuit cutting device is in an inverted state, and the plugging thimble 3 and the valve body 4 move downward under the action of gravity to block the communication hole 14. At this time, the amount of oil flowing into the oil cavity 13 from the oil inlet 11 decreases, and thus the amount of oil flowing through the oil outlet 12 also decreases significantly, so that the amount of oil flowing into the bearing seat is reduced to 0. Since there is no longer oil supply to the bearing cavity, there is no need to design a complex oil return system for oil return. The bearing is lubricated by the remaining oil in the bearing seat under the action of the oil slinger for splash cooling, which can not only ensure the lubricating oil cooling function during inverted flight for a short time, but also avoid lubricating oil leakage in the bearing cavity.

[0044] Due to including the above oil circuit cutting device, the oil lubrication system of the embodiments of the present invention has all the advantages and beneficial effects of the above embodiments, which will not be elaborated here.

[0045] The present utility model also provides an aeroengine, which includes the lubricating oil system provided by the embodiments of the present utility model. When the aircraft is flying upside down, the oil circuit cutting device is in an inverted state, and both the plugging thimble 3 and the valve body 4 move downward under the action of gravity to plug the communication hole 14. At this time, the amount of oil flowing into the oil chamber 13 from the oil inlet 11 decreases, and thus the amount of oil flowing through the oil outlet 12 also decreases significantly, so that the amount of oil entering the bearing housing is reduced to 0. Since the bearing cavity is no longer supplied with oil, there is no need to design a complex oil return system for oil return. The bearing lubrication relies on the remaining oil in the bearing housing to be splashed and cooled under the action of the oil slinger, which can not only ensure the lubricating oil cooling function during flying upside down for a short time, but also avoid the lubricating oil leakage in the bearing cavity.

[0046] Due to including the above-mentioned oil circuit cutting device, the aeroengine of the embodiments of the present utility model has all the advantages and beneficial effects of the above embodiments, which will not be elaborated here.

[0047] In addition, the above is only the preferred embodiment of the present utility model and the applied technical principle. Those skilled in the art will understand that the present utility model is not limited to the specific embodiments described here, and various obvious changes, re-adjustments and substitutions can be made by those skilled in the art without departing from the protection scope of the present utility model. Therefore, although the present utility model has been described in detail through the above embodiments, the present utility model is not limited to the above embodiments only. Without departing from the concept of the present utility model, more other equivalent embodiments can be included, and the scope of the present utility model is determined by the scope of the appended claims.

Claims

1. An oil circuit cut-off device, characterized in that: include: A first housing (1), the first housing (1) having an oil inlet (11), an oil outlet (12), an oil chamber (13) and a communicating hole (14), the oil inlet (11) being in communication with the oil chamber (13) via the communicating hole (14), and the oil chamber (13) being in communication with the oil outlet (12); A second housing (2), the second housing (2) at least partially extending into the oil chamber (13) and being sealedly connected to the first housing (1); a blocking ejector pin (3) disposed in the oil chamber (13) and capable of sliding relative to the first housing (1); the blocking ejector pin (3) being disposed opposite to the communicating hole (14); and the blocking ejector pin (3) being capable of extending into or out of the communicating hole (14) under the action of gravity so as to disconnect or connect the communicating hole (14) with the oil chamber (13); The valve body (4) is provided with a receiving groove (21) arranged opposite to the communicating hole (14); the valve body (4) is arranged in the receiving groove (21) and can approach or move away from the communicating hole (14) under the action of gravity; the side of the valve body (4) facing the communicating hole (14) can fit with the bottom of the oil chamber (13); and the blocking ejector pin (3) is installed at the end of the valve body (4) facing the communicating hole (14).

2. The oil circuit cut-off device according to claim 1, characterized in that: An installation groove (41) is provided at one end of the valve body (4) facing the connecting hole (14), the blocking ejector pin (3) is installed in the installation groove (41) and protrudes from the installation groove (41), and the distance between the valve body (4) and the bottom of the oil chamber (13) is greater than the protruding length of the blocking ejector pin (3).

3. The oil circuit cut-off device according to claim 1, characterized in that: The valve body (4) is arranged to protrude from the accommodating groove (21).

4. The oil circuit cut-off device according to claim 3, characterized in that: It also comprises a guide rod (5), the first shell (1) is fixedly mounted with the guide rod (5), the valve body (4) is provided with a guide hole, the guide rod (5) extends into the guide hole and the valve body (4) can move relative to the guide rod (5).

5. The oil circuit cut-off device according to claim 1, characterized in that: It also comprises a lubricating oil pressure sensor (6), wherein the lubricating oil pressure sensor (6) is arranged on the first housing (1) and is used to detect the lubricating oil pressure of the oil inlet (11).

6. The oil circuit cut-off device according to any one of claims 1 to 5, characterized in that: The first shell (1) is threadedly connected to the second shell (2).

7. The oil circuit cut-off device according to any one of claims 1 to 5, characterized in that: The first shell (1) and the second shell (2) are interference connected.

8. The oil circuit cut-off device according to any one of claims 1 to 5, characterized in that: The oil inlet (11) and the oil outlet (12) are arranged on the same side.

9. A lubricating oil system, characterized in that: It comprises the oil circuit cutting device as described in any one of claims 1 to 8.

10. An aircraft engine, characterized in that: Comprising the lubricating oil system as claimed in claim 9.

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