Aero-engine oil return device and aero-engine
By designing an aircraft engine oil return device with moving shielding members and communication rods, the problems of complex structure and high manufacturing cost of the oil return device in the prior art are solved, and the oil return function that can effectively absorb lubricant during forward flight and reverse flight is realized, and the structural complexity and manufacturing cost are reduced.
Patent Information
- Application Number
- CN202422354495.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-26
- Publication Date
- 2025-06-10
- Estimated Expiration
- 2034-09-26
AI Technical Summary
The existing aircraft engine oil return device has a complex structure, which leads to high manufacturing costs and is difficult to continuously absorb engine oil in a reverse flight posture.
An aircraft engine oil return device including a housing, a communication rod and a moving shield is designed. The communication rod is provided with a first opening and a second opening, and the moving shield member moves under the action of gravity to selectively block the opening to realize the oil return function during forward flight and reverse flight.
It realizes the oil return function of continuously absorbing engine lubricant when the aircraft is flying in a forward or reverse flight. It has a simple structure, which reduces the demand for complex runners and pipelines and reduces manufacturing costs.
Smart Images
Figure CN222962955U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of aviation technology, in particular to an aviation engine oil return device and an aviation engine. Background Art
[0002] 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. During flight, the aircraft has inverted flight attitude and flight time requirements, so the oil return circuit design should be able to continuously absorb engine lubricating oil from the oil return chamber in the inverted flight attitude. However, the oil return circuit of the existing technology is relatively complex, resulting in a complex internal structure of the oil return device and high manufacturing cost.
[0003] Therefore, there is an urgent need for an aircraft engine oil return device to solve the above technical problems. Utility Model Content
[0004] The utility model aims to provide an aircraft engine oil return device, which has a simple oil return oil path and can continuously absorb engine lubricating oil from an oil return chamber.
[0005] To achieve this purpose, the utility model adopts the following technical solutions:
[0006] In a first aspect, an aircraft engine oil return device is provided, comprising:
[0007] The housing has an oil containing cavity, a first oil inlet, a second oil inlet and an oil return port, wherein the first oil inlet, the second oil inlet and the oil return port are respectively connected to the oil containing cavity;
[0008] A connecting rod, comprising a rod body and a partition plate, wherein the circumferential side wall of the rod body is provided with a first opening and a second opening, the rod body has an axially through chamber, the partition plate is provided in the chamber to separate the chamber into a first sub-chamber and a second sub-chamber, the first sub-chamber has a first opening, the second sub-chamber has a second opening, the first opening can connect the first oil inlet, the oil containing chamber, the first sub-chamber and the oil return port, and the second opening can connect the second oil inlet, the oil containing chamber, the second sub-chamber and the oil return port;
[0009] The movable shielding member is sleeved on the outer circumference of the connecting rod and is located in the oil containing cavity. The movable shielding member can move under the action of gravity to selectively shield the first opening or the second opening.
[0010] As a preferred technical solution of the above-mentioned aircraft engine oil return device, the number of the first openings is multiple, and the multiple first openings are arranged along the circumference of the connecting rod; and / or,
[0011] The number of the second openings is multiple, and the multiple second openings are arranged along the circumferential direction of the connecting rod.
[0012] As a preferred technical solution of the above oil return device for an aero-engine, the first oil inlet, the second oil inlet and the oil return port are located on the same side of the housing.
[0013] As a preferred technical solution of the above oil return device for an aero-engine, the housing includes a first housing and a second housing. The first oil inlet is arranged on the first housing, the oil return port and the second oil inlet are arranged on the second housing. The second housing is provided with the oil storage cavity. The first housing and the second housing are hermetically connected to close the opening of the oil storage cavity. One end of the connecting rod is fixedly connected to the first housing, and the other end of the connecting rod is fixedly connected to the second housing.
[0014] As a preferred technical solution of the above oil return device for an aero-engine, both ends of the connecting rod are in interference connection with the housing, and sealing rings are arranged between both ends of the connecting rod and the housing.
[0015] As a preferred technical solution of the above oil return device for an aero-engine, the connecting rod is provided with a first limiting structure, and the second housing is provided with a second limiting structure. The first limiting structure and the second limiting structure cooperate to limit the connecting rod.
[0016] As a preferred technical solution of the above oil return device for an aero-engine, the first limiting structure includes a limiting ring extending outward along the outer periphery of the connecting rod, and the second limiting structure includes the bottom wall of the oil storage cavity. The limiting ring abuts against the bottom wall, and the limiting ring is located on the side of the second opening facing the bottom wall of the oil storage cavity.
[0017] As a preferred technical solution of the above oil return device for an aero-engine, the partition plate and the rod body are of an integrally formed structure.
[0018] As a preferred technical solution of the above oil return device for an aero-engine, the end faces at both ends of the movable shielding member and the circumferential side wall are smoothly connected through a flow guiding wall.
[0019] In a second aspect, the present invention further provides an aero-engine, including the oil return device for an aero-engine according to any one of the above solutions.
[0020] The present invention has at least the following beneficial effects:
[0021] The oil return device for an aeroengine and the aeroengine provided by the present utility model are such that the connecting rod is provided with a first opening and a second opening. Whether the aircraft is flying forward or backward, the movable shielding member is sleeved on the connecting rod and can move relative to the connecting rod. When the aircraft is flying forward, under the action of gravity, the movable shielding member blocks the second opening, so that the oil fluid enters the first subchamber through the first oil inlet and the first opening, then flows out through the first opening into the oil storage chamber and flows out through the oil return port. When the aircraft is flying backward, under the action of gravity, the movable shielding member blocks the first opening, so that the oil fluid enters the second subchamber through the second oil inlet and the second opening, then flows out through the second opening into the oil storage chamber and flows out through the oil return port. In this way, whether the aircraft is flying forward or backward, the purpose of oil return can be achieved. In addition, the structures of the connecting rod and the movable shielding member are relatively simple, and the oil return can be realized without setting up complex flow channels and pipelines. Compared with the prior art, the structure is simple and the manufacturing cost is low. Description of the Drawings
[0022] In order 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 according to the content of the embodiments of the present utility model and these drawings.
[0023] Figure 1 It is a cross-sectional view of the oil return device for an aeroengine provided by the embodiment of the present utility model;
[0024] Figure 2 It is a cross-sectional view of the connecting rod provided by the embodiment of the present utility model.
[0025] In the figure:
[0026] 1. Outer shell; 11. First shell; 111. First oil inlet; 12. Second shell; 121. Oil return port; 122. Second oil inlet; 123. Oil storage chamber; 2. Connecting rod; 201. Rod main body; 202. Partition plate; 21. First opening; 22. First subchamber; 23. First opening; 24. Second opening; 25. Second subchamber; 26. Second opening; 27. Limiting ring; 3. Movable shielding member; 31. Flow guiding wall. Detailed 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 are shown in the drawings, rather than all the structures.
[0028] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0029] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level 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 embodiment of the utility model provides an aircraft engine oil return device, which can return oil when the aircraft is flying in reverse or forward, has a simple oil return oil circuit structure and low manufacturing cost.
[0032] like Figure 1 and Figure 2As shown in the figure, the oil return device of the aero-engine includes a housing 1, a connecting rod 2, and a movable baffle 3. The housing 1 has an oil storage chamber 123, a first oil inlet 111, a second oil inlet 122, and an oil return port 121. The first oil inlet 111, the second oil inlet 122, and the oil return port 121 are respectively communicated with the oil storage chamber 123. The connecting rod 2 includes a rod main body 201 and a partition plate 202. The circumferential side wall of the rod main body 201 is provided with a first opening 23 and a second opening 26. The rod main body 201 has an axially penetrating chamber. The partition plate 202 is arranged in the chamber to divide the chamber into a first sub-chamber 22 and a second sub-chamber 25. The first sub-chamber 22 has a first opening 21, and the second sub-chamber 25 has a second opening 24. The first opening 23 can communicate the first oil inlet 111, the oil storage chamber 123, the first sub-chamber 22, and the oil return port 121. The second opening 26 can communicate the second oil inlet 122, the oil storage chamber 123, the second sub-chamber 25, and the oil return port 121. The movable baffle 3 is sleeved on the outer periphery of the connecting rod 2 and is located in the oil storage chamber 123. The movable baffle 3 can move under the action of gravity to selectively block the first opening 23 or the second opening 26.
[0033] For the oil return device of the aero-engine provided by the present utility model, the connecting rod 2 is provided with a first opening 23 and a second opening 26. Whether the aircraft is flying forward or backward, the movable baffle 3 sleeved on the connecting rod 2 can move relative to the connecting rod 2. When the aircraft is flying forward, under the action of gravity, the movable baffle 3 blocks the second opening 26, so that the oil fluid enters the first sub-chamber 22 through the first oil inlet 111 and the first opening 21, and then flows out from the first opening 23 into the oil storage chamber 123 and flows out through the oil return port 121. When the aircraft is flying backward, under the action of gravity, the movable baffle 3 blocks the first opening 23, so that the oil fluid enters the second sub-chamber 25 through the second oil inlet 122 and the second opening 24, and then flows out from the second opening 26 into the oil storage chamber 123 and flows out through the oil return port 121. In this way, it can be ensured that whether the aircraft is flying forward or backward, the engine lubricating oil can be absorbed from the oil return chamber. In addition, the structures of the connecting rod 2 and the movable baffle 3 are relatively simple, and the oil return can be realized without setting complex flow channels and pipelines. Compared with the prior art, the structure is simple and the manufacturing cost is low.
[0034] In some embodiments, in order to ensure the lubricating oil flow rate, the number of the first openings 23 is multiple, and the multiple first openings 23 are arranged along the circumferential direction of the connecting rod 2. More specifically, the multiple first openings 23 are evenly arranged along the circumferential direction of the connecting rod 2. Such an arrangement ensures the flow balance of the oil fluid everywhere.
[0035] In some embodiments, in order to ensure the oil flow rate during inverted flight, the number of second openings 26 is multiple, and the multiple second openings 26 are arranged along the circumference of the connecting rod 2. More specifically, the multiple second openings 26 are evenly arranged along the circumference of the connecting rod 2, and such an arrangement ensures that the oil flow rate is balanced everywhere.
[0036] In some embodiments, in order to facilitate the arrangement of pipeline connections and make the pipeline arrangement neater, the first oil inlet 111, the second oil inlet 122 and the oil return port 121 are located on the same side of the housing 1. When the aircraft is in a positive flight attitude, the first oil inlet 111, the oil return port 121 and the second oil inlet 122 are arranged in sequence from top to bottom, and the oil return port 121 is located between the first oil inlet 111 and the second oil inlet 122, which can facilitate the distinction during assembly. In some other embodiments, the arrangement of the first oil inlet 111, the second oil inlet 122 and the oil return port 121 can be set according to actual needs, and no special limitation is made here.
[0037] In some embodiments, Figure 1 As shown, the housing 1 includes a first shell 11 and a second shell 12, a first oil inlet 111 is arranged on the first shell 11, an oil return port 121 and a second oil inlet 122 are arranged on the second shell 12, an oil containing chamber 123 is opened in the second shell 12, the first shell 11 and the second shell 12 are sealed and connected to close the opening of the oil containing chamber 123, the first oil inlet 111 is communicated with the oil containing chamber 123, one end of the connecting rod 2 is fixedly connected with the first shell 11, at this time, the first opening 21 is communicated with the first oil inlet 111, the other end of the connecting rod 2 is fixedly connected with the second shell 12, and the second opening 26 is blocked by the movable shielding member 3.
[0038] In some embodiments, in order to enable the connecting rod 2 to be fixedly connected to the outer shell 1 and reduce the use of parts, the two ends of the connecting rod 2 are respectively interference-connected with the outer shell 1, that is, the two ends of the connecting rod 2 are respectively interference-fitted with the first shell 11 and the second shell 12, so that the connecting rod 2 is fixed relative to the outer shell 1, and sealing rings are provided between the two ends of the connecting rod 2 and the outer shell 1 to ensure that no lubricating oil leaks between the connecting rod 2 and the outer shell 1, thereby ensuring sealing.
[0039] In some embodiments, the aircraft is in a normal flight state for a long time. Under the action of gravity, the connecting rod 2 will sink downward. In order to prevent the connecting rod 2 from being separated from the first housing 11 due to the sinking of the connecting rod 2, the connecting rod 2 is provided with a first limiting structure, and the second housing 12 is provided with a second limiting structure. The first limiting structure and the second limiting structure cooperate to limit the connecting rod 2. The provision of the first limiting structure and the second limiting structure can prevent the connecting rod 2 from moving toward the second housing 12, thereby ensuring that the position of the connecting rod 2 is fixed and always maintained in communication with the first oil inlet 111 and the second oil inlet 122.
[0040] Specifically, combinedFigure 1 and Figure 2 The first limiting structure includes a limiting ring 27 extending outward along the outer periphery of the communicating rod 2, and the second limiting structure includes the bottom wall of the oil storage cavity 123. The limiting ring 27 abuts against the bottom wall, and the limiting ring 27 is located on the side of the second opening 26 facing the bottom wall of the oil storage cavity 123. The abutment of the limiting ring 27 against the bottom wall can prevent the communicating rod 2 from moving towards the second housing 12. The structures of the limiting ring 27 and the bottom wall are relatively simple and will not increase the manufacturing cost.
[0041] In some embodiments, the partition plate 202 and the rod body 201 are integrally formed structures, which facilitates assembly and greatly reduces the assembly difficulty and assembly time.
[0042] After the oil fluid flows out from the first opening 23 or the second opening 26, a certain flow guiding structure is required to guide the oil fluid so that the oil fluid can flow into the oil return port 121 relatively quickly and prevent the oil fluid from accumulating in the oil storage cavity 123. For this purpose, the two end faces of the movable shielding member 3 and the circumferential side wall are smoothly connected by a flow guiding wall 31. The flow guiding wall 31 is inclined with respect to the communicating rod 2, and the distance of the flow guiding wall 31 from the oil return port 121 has a gradually increasing trend. Such a setting can ensure that no matter whether the aircraft is flying forward or backward, the lubricating oil can flow along the flow guiding wall 31 to the oil return port 121.
[0043] In an embodiment of the present utility model, an aero-engine is further provided, which includes the aero-engine oil return device provided by the embodiment of the present utility model. Since the aero-engine includes the aero-engine oil return device, the communicating rod 2 is provided with a first opening 23 and a second opening 26. No matter whether the aircraft is flying forward or backward, the movable shielding member 3 is sleeved on the communicating rod 2 and can move relative to the communicating rod 2. Under the action of gravity, when the aircraft is flying forward, the movable shielding member 3 blocks the second opening 26, so that the oil fluid enters the first sub-cavity 22 through the first oil inlet 111 and the first opening 21, then flows out from the first opening 23 into the oil storage cavity 123 and flows out through the oil return port 121. Under the action of gravity, when the aircraft is flying backward, the movable shielding member 3 blocks the first opening 23, so that the oil fluid enters the second sub-cavity 25 through the second oil inlet 122 and the second opening 24, then flows out from the second opening 26 into the oil storage cavity 123 and flows out through the oil return port 121. In this way, no matter whether the aircraft is flying forward or backward, the purpose of oil return can be achieved. In addition, the structures of the communicating rod 2 and the movable shielding member 3 are relatively simple, and the oil return can be realized without setting complex flow channels and pipelines. Compared with the prior art, the structure is simple and the manufacturing cost is low.
[0044] Since the aero-engine includes the above-mentioned aero-engine oil return device, the aero-engine of the embodiment of the present utility model has all the advantages and beneficial effects of the above embodiments and will not be elaborated herein.
[0045] In addition, the above are only the preferred embodiments of the present utility model and the technical principles applied. Those skilled in the art will understand that the present utility model is not limited to the specific embodiments described herein, 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 more detail through the above embodiments, the present utility model is not limited to the above embodiments. 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 aircraft engine oil return device, characterized in that: include: The housing (1) comprises an oil containing chamber (123), a first oil inlet (111), a second oil inlet (122) and an oil return port (121), wherein the first oil inlet (111), the second oil inlet (122) and the oil return port (121) are respectively connected to the oil containing chamber (123); A connecting rod (2), comprising a rod body (201) and a partition plate (202), wherein a first opening (23) and a second opening (26) are provided on a circumferential side wall of the rod body (201), wherein the rod body (201) has an axially through chamber, wherein the partition plate (202) is arranged in the chamber to separate the chamber into a first sub-chamber (22) and a second sub-chamber (25), wherein the first sub-chamber (22) has a first opening (21), and the second sub-chamber (25) has a second opening (24), wherein the first opening (23) can connect the first oil inlet (111), the oil containing chamber (123), the first sub-chamber (22) and the oil return port (121), and wherein the second opening (26) can connect the second oil inlet (122), the oil containing chamber (123), the second sub-chamber (25) and the oil return port (121); A movable shielding member (3) is sleeved on the outer circumference of the connecting rod (2) and is located in the oil containing cavity (123). The movable shielding member (3) can move under the action of gravity to selectively shield the first opening (23) or the second opening (26).
2. The aircraft engine oil return device according to claim 1, characterized in that: The number of the first openings (23) is multiple, and the multiple first openings (23) are arranged along the circumference of the connecting rod (2); and / or, The number of the second openings (26) is multiple, and the multiple second openings (26) are arranged along the circumference of the connecting rod (2).
3. The aircraft engine oil return device according to claim 1, characterized in that: The first oil inlet (111), the second oil inlet (122) and the oil return port (121) are located on the same side of the housing (1).
4. The aircraft engine oil return device according to claim 1, characterized in that: The housing (1) comprises a first shell (11) and a second shell (12); the first oil inlet (111) is arranged on the first shell (11); the oil return port (121) and the second oil inlet (122) are arranged on the second shell (12); the second shell (12) is provided with the oil containing cavity (123); the first shell (11) and the second shell (12) are sealedly connected to close the opening of the oil containing cavity (123); one end of the connecting rod (2) is fixedly connected to the first shell (11); and the other end of the connecting rod (2) is fixedly connected to the second shell (12).
5. The aircraft engine oil return device according to claim 4, characterized in that: Both ends of the connecting rod (2) are respectively interference-connected with the outer shell (1), and sealing rings are provided between both ends of the connecting rod (2) and the outer shell (1).
6. The aircraft engine oil return device according to claim 4, characterized in that: The connecting rod (2) is provided with a first limiting structure, and the second housing (12) is provided with a second limiting structure, and the first limiting structure cooperates with the second limiting structure to limit the connecting rod (2).
7. The aircraft engine oil return device according to claim 6, characterized in that: The first limiting structure comprises a limiting ring (27) extending outwardly along the outer circumference of the connecting rod (2), and the second limiting structure comprises a bottom wall of the oil containing cavity (123), the limiting ring (27) abuts against the bottom wall of the cavity, and the limiting ring (27) is located on the side of the second opening (26) facing the bottom wall of the oil containing cavity (123).
8. The aircraft engine oil return device according to any one of claims 1 to 7, characterized in that: The partition plate (202) and the rod body (201) are an integrally formed structure.
9. The aircraft engine oil return device according to any one of claims 1 to 7, characterized in that: The end surfaces at both ends of the movable shielding member (3) and the circumferential side wall are smoothly connected via the guide wall (31).
10. An aircraft engine, characterized in that: The invention comprises the aircraft engine oil return device according to any one of claims 1 to 9.