Aero-engine oil tank integrated with a reducer case

Abstract

The utility model relates to the technical field of oil tank, specifically is a kind of aero-engine oil tank integrated with speed reducer machine case, including speed reducer machine case, the oil tank is fixedly installed outside speed reducer machine case, connection port is jointly opened between speed reducer machine case, oil tank top is equipped with driving motor, the utility model improves space utilization and layout adaptability, adopt vertical structure, can naturally be embedded in the peripheral space of engine, compared with traditional horizontal oil tank, reduce radial occupied space, multi-attitude lubrication reliability guarantee, whether unmanned aerial vehicle is in normal flight, side flight or any transition attitude posture, can realize the lubrication to engine friction pair, system level reliability improves, safety and maintainability improve, vertical design is convenient for sensor, oil port and other key components are arranged in specific area, personnel is checked conveniently state, oil discharge and maintenance operation, improve the overall reliability, safety and maintainability.

Description

Technical Field

[0001] This utility model relates to the field of lubricating oil tank technology, specifically to an aero-engine lubricating oil tank integrated with the reducer casing. Background Technology

[0002] The lubricating oil tank is an important component of the lubrication system of an aircraft engine. Its core function is to store, supply, and recycle lubricating oil, ensuring that all critical friction pairs such as bearings and gears of the engine receive continuous, stable, and clean lubrication and cooling under any operating conditions.

[0003] With the rapid development of low-altitude economic sectors such as urban air traffic, drone logistics, and regional short-haul transportation, aircraft design concepts are undergoing a transformation. As the core system of low-altitude aircraft, the design of power plants, especially aero engines, faces unprecedentedly stringent requirements. Space utilization and structural compactness have become key constraints determining the overall performance, economy, and feasibility of aircraft. As one of the key subsystems of the engine, the lubrication system's core component, the oil tank, is currently mostly an independent, externally mounted, horizontal, flat structure. To ensure sufficient oil storage and maintain a stable oil level, its shape is typically flat and wide. This design results in low space utilization, disrupts aerodynamic shape, increases flight drag, and cannot meet the stringent requirements of drones for multi-attitude, high-reliability lubrication systems within complex, high-maneuver flight envelopes. Based on the current situation, the following key technical problems exist, particularly in the lubrication systems of small engines used in drones and other aircraft:

[0004] 1. Spatial layout and integration issues: Traditional horizontal oil tanks have a fixed shape and bulky size, which cannot effectively utilize the vertical space around the engine. Their low space-to-volume ratio restricts the optimization of the overall layout of the aircraft, which contradicts the design of low-altitude economic aircraft that pursues extreme compactness and high integration.

[0005] 2. Challenges in Multi-Attitude Adaptability: When performing reconnaissance, tracking, evasion, or special operations missions, UAVs frequently need to perform high-maneuverability maneuvers such as high angle-of-attack climbs, dives, inverted flight, and side-flying. Under these maneuvers, the fluid level in traditional fuel tanks can tilt drastically, easily leading to oil cut-off in the lubrication system and consequently, lubrication failure of the engine's friction pairs, posing a significant safety risk.

[0006] This invention comprehensively solves the above problems and provides a novel lubricating oil tank solution that is compact, highly integrated, and can achieve reliable lubrication throughout the entire flight envelope. Utility Model Content

[0007] To address the aforementioned issues, this application provides an integrated aero-engine oil tank that is integrated with the gearbox casing, thus resolving the problems of an uncompacted oil tank layout and inability to adapt to multi-attitude flight.

[0008] An integrated oil tank for an aircraft engine, comprising a gearbox, wherein an oil tank is fixedly mounted on the outside of the gearbox, and a connection port is provided between the gearbox and the oil tank.

[0009] A drive motor is installed on the top of the lubricating oil tank, and a rotating rod is driven to the output end of the drive motor. A stirring plate for stirring the lubricating oil is installed around the rotating rod.

[0010] A rotating heating plate is fixedly installed on the side of the stirring plate facing the direction of rotation, which is used to heat the lubricating oil at low temperatures;

[0011] A magnet is fixedly installed on the side of the stirring plate facing away from the direction of rotation to collect debris in the lubricating oil.

[0012] Preferably, the top of the lubricating oil tank has a disassembly through hole, and a sealing plate is fixedly installed on the outside of the drive motor housing. The sealing plate is fixedly installed on the top of the lubricating oil tank by bolts and seals the disassembly through hole.

[0013] Preferably, a rubber pad is embedded and fixedly installed at the bottom of the sealing plate.

[0014] Preferably, an auxiliary rotating protrusion is fixedly installed on the bottom inner side of the oil tank, and a groove is provided at the bottom of the rotating rod, with the groove and the auxiliary rotating protrusion being rotatably inserted into each other.

[0015] Preferably, an observation window is fixedly installed on the outside of the lubricating oil tank.

[0016] Preferably, a fixed heating rod is fixedly installed inside the lubricating oil tank.

[0017] Preferably, a temperature sensor is fixedly installed inside the lubricating oil tank, and the temperature sensor is electrically connected to a fixed heating rod and a rotating heating plate.

[0018] Preferably, a drain valve is fixedly installed at the bottom of the lubricating oil tank.

[0019] Preferably, a metal chip sensor is fixedly installed inside the lubricating oil tank.

[0020] Preferably, the lubricating oil tank is connected to the top of the reducer via an oil pump.

[0021] The beneficial effects of this utility model are as follows:

[0022] The present invention provides an integrated aero-engine oil tank with a reducer casing, which improves space utilization and layout adaptability. The vertical structure allows it to be naturally embedded in the surrounding space of the engine, reducing radial space occupation compared to traditional horizontal oil tanks.

[0023] Multi-attitude lubrication reliability assurance: Regardless of whether the UAV is in forward flight, side flight, or any transitional attitude, it can achieve lubrication of the engine friction pair;

[0024] Improved system-level reliability, safety, and maintainability: The vertical design allows for the placement of key components such as sensors and oil ports in specific areas, facilitating personnel to perform status checks, oil draining, and maintenance operations, thereby improving overall reliability, safety, and maintainability. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of this utility model, the accompanying drawings used in the description of the embodiments of this utility model will be briefly introduced below. Obviously, the drawings described below are merely some exemplary embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the content of the exemplary embodiments of this utility model and these drawings without any creative effort.

[0026] Figure 1 A schematic diagram of the installation structure of an aero-engine lubricating oil tank integrated with a reducer casing, provided by this utility model;

[0027] Figure 2 A schematic diagram of the gearbox connection for an aero-engine lubricating oil tank integrated with the gearbox, provided for the present invention;

[0028] Figure 3 A schematic diagram showing the connection of an observation window to an aero-engine oil tank integrated with a reducer housing, provided by this utility model;

[0029] Figure 4 A schematic diagram of the internal structure of an aero-engine oil tank integrated with a reducer casing, provided for the purposes of this utility model;

[0030] Figure 5 A schematic diagram of the oil tank structure of an aero-engine oil tank integrated with a reducer housing, provided for the present invention;

[0031] Figure 6 This utility model provides a schematic diagram of the connection of the stirring plate in an aero-engine lubricating oil tank integrated with the reducer casing.

[0032] In the picture:

[0033] 1. Reducer housing; 2. Oil tank; 3. Connection port; 4. Observation window; 5. Fixed heating rod; 6. Oil drain valve; 7. Temperature sensor; 8. Metal chip sensor; 9. Drive motor; 10. Sealing plate; 11. Disassembly through hole; 12. Auxiliary rotating protrusion; 13. Rubber pad; 14. Rotating rod; 15. Stirring plate; 16. Rotating heating plate; 17. Magnet; 18. Groove. Detailed Implementation

[0034] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and not intended to limit its scope.

[0035] To keep the drawings concise, only the parts relevant to the utility model are shown schematically in each drawing; these do not represent the actual structure of the product. Furthermore, for ease of understanding, in some drawings, only one of the components with the same structure or function is schematically shown, or only one is labeled. In this document, "a" not only means "only one," but can also mean "more than one," and "several" includes "two" and "more than two."

[0036] In this document, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0037] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0038] In the description of this embodiment, terms such as "upper," "lower," "left," and "right" are based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of description and simplification of operation, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0039] Furthermore, in the description of this application, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0040] like Figure 1 , Figure 2 As shown, this utility model embodiment provides an integrated aero-engine oil tank with a gearbox, including a gearbox 1. An oil tank 2 is fixedly installed on the outside of the gearbox 1. The oil tank 2 is connected to the top of the gearbox via an oil pump. A connection port 3 is provided between the gearbox 1 and the oil tank 2. Unlike conventional designs, this embodiment directly fixes the oil tank 2 to the bottom of the gearbox 1. The bottom of the gearbox 1 is machined with a connection port 3, connecting its internal cavity to the internal oil storage cavity of the oil tank 2. This forms a compact unit with an "upper gearbox and lower oil tank". The shape of the oil tank 2 has a high degree of design flexibility and can be customized and optimized according to the actual space constraints inside the aircraft to achieve efficient conformal integration with the airframe.

[0041] In this embodiment, the oil pump delivers the oil from the lubricating oil tank 2 to the reducer to lubricate the internal components of the reducer. After lubrication, the oil temperature rises, and during the return process, its heat can be effectively dissipated to the environment through the reducer housing 1, achieving natural cooling of the system. At the same time, the lubricated and cooled oil naturally collects at the bottom of the reducer housing 1 under the action of gravity. Since the reducer housing 1 is directly connected to the lubricating oil tank 2, it naturally flows back into the lubricating oil tank 2 through the connection port 3 under the action of gravity, completing the entire lubrication cycle.

[0042] Attitude adaptability assurance: Although the oil tank 2 is located at the bottom, there is a connection port 3 between the gearbox and the oil tank 2. When the aircraft is rolling, pitching or other attitude changes, because the gearbox is directly connected to the oil tank 2 and there is a connection port, the oil supply can continue under the action of gravity, ensuring the continuity of lubrication during continuous large-angle maneuvers.

[0043] Furthermore, such as Figure 3 , Figure 4 , Figure 6 As shown, a fixed heating rod 5 is fixedly installed inside the lubricating oil tank 2 for heating the lubricating oil. A drive motor 9 is installed on the top of the lubricating oil tank 2. A rotating rod 14 is driven and installed at the output end of the drive motor 9. A stirring plate 15 for stirring the lubricating oil is installed around the rotating rod 14. A rotating heating plate 16 is fixedly installed on the side of the stirring plate 15 facing the direction of rotation for heating the lubricating oil at low temperature. A magnet 17 is fixedly installed on the side of the stirring plate 15 away from the direction of rotation for collecting debris in the lubricating oil.

[0044] Furthermore, a temperature sensor 7 is fixedly installed inside the lubricating oil tank 2, and the temperature sensor 7 is electrically connected to the fixed heating rod 5 and the rotating heating plate 16.

[0045] In this embodiment, under low-temperature conditions, the temperature sensor 7 sends an electrical signal to the data processor, which in turn sends an electrical signal to the fixed heating rod 5 and the rotating heating plate 16. Both of these activate to heat the lubricating oil, driving the motor 9 to rotate. This causes the rotating rod 14, the stirring plate 15, the rotating heating plate 16, and the magnet 17 to rotate. The rotating heating plate 16 is located on the front side of the rotation direction, and the heat generated is directly transferred to the oil in contact with it through its surface. The density of the heated oil decreases and rises, and the surrounding low-temperature oil comes to replenish it, forming natural convection. Combined with the stirring of the stirring plate 15, the oil temperature in the entire oil tank gradually becomes uniform. The magnet 17 is located on the back side of the rotation direction. When the stirring plate 15 rotates, a relatively low-pressure vortex zone is generated on its back side. The oil flow in this area is relatively slow and turbulent, which is beneficial for the magnet 17 to collect metal debris. The fixed heating rod 5 and the rotating heating plate 16 heat the lubricating oil, reducing its viscosity and ensuring smooth oil supply.

[0046] Furthermore, such as Figure 5 , Figure 6 As shown, the top of the lubricating oil tank 2 has a disassembly through hole 11 to facilitate cleaning of metal debris adhering to the outside of the magnet 17. A sealing plate 10 is fixedly installed on the outside of the drive motor 9 housing. A rubber gasket 13 is embedded and fixedly installed at the bottom of the sealing plate 10 to enhance the sealing performance of the sealing plate 10. The sealing plate 10 is fixedly installed on the top of the lubricating oil tank 2 by bolts and seals the disassembly through hole 11.

[0047] Furthermore, such as Figure 5 , Figure 6 As shown, an auxiliary rotating protrusion 12 is fixedly installed on the bottom inner side of the oil tank 2, and a groove 18 is provided at the bottom of the rotating rod 14. The groove 18 and the auxiliary rotating protrusion 12 are rotatably inserted and engaged. The groove 18 and the auxiliary rotating protrusion 12 work together to make the rotating rod 14 rotate more smoothly.

[0048] Furthermore, such as Figure 3 As shown, an observation window 4 is fixedly installed on the outside of the lubricating oil tank 2, which makes it convenient for staff to check the oil status and level.

[0049] Furthermore, such as Figure 3 As shown, the bottom of the lubricating oil tank 2 is connected to and fixedly installed with an oil drain valve 6, which is used to drain the oil and replace it with new lubricating oil.

[0050] Furthermore, such as Figure 3 As shown, a metal chip sensor 8 is fixedly installed inside the lubricating oil tank 2 to detect the content of metal chips in the lubricating oil. If the content exceeds the standard, it means that the magnet 17 is saturated and needs to be cleaned. The metal chip sensor 8 can send an electrical signal to the background control room to remind the staff to clean the magnet 17 or replace the lubricating oil in time.

[0051] Specific working methods:

[0052] The oil pump delivers oil from the lubricating oil tank 2 to the reducer to lubricate the internal components of the reducer. After lubrication, the oil temperature rises, and during the return process, its heat can be effectively dissipated into the environment through the reducer housing 1, achieving natural cooling of the system. At the same time, the lubricated and cooled oil naturally collects at the bottom of the reducer housing 1 under the action of gravity. Since the reducer housing 1 is directly connected to the lubricating oil tank 2, it naturally flows back into the lubricating oil tank 2 through the connection port 3 under the action of gravity, completing the entire lubrication cycle.

[0053] Attitude adaptability assurance: Although the oil tank 2 is located at the bottom, there is a connection port 3 between the gearbox and the oil tank 2. When the aircraft is rolling, pitching or other attitude changes, because the gearbox is directly connected to the oil tank 2 and there is a connection port, the oil supply can continue under the action of gravity, ensuring the continuity of lubrication during continuous large-angle maneuvers.

[0054] Thermal Management and Environmental Adaptability: In low-temperature environments, temperature sensor 7 sends an electrical signal to data processor, which in turn sends an electrical signal to fixed heating rod 5 and rotating heating plate 16. Both of these activate to heat the lubricating oil, driving motor 9 to rotate and causing rotating rod 14, stirring plate 15, rotating heating plate 16, and magnet 17 to rotate. Rotating heating plate 16 is located on the front side of the rotation direction, and the heat generated is directly transferred to the oil in contact with it through its surface. The density of the heated oil decreases and rises, and the surrounding low-temperature oil comes to replenish it, forming natural convection. Combined with the stirring of stirring plate 15, the oil temperature in the entire oil tank gradually becomes uniform.

[0055] Magnet 17 is located on the back side in the direction of rotation. When the stirring plate 15 rotates, a relatively low-pressure vortex zone is generated on its back side. The oil flow in this zone is relatively slow and turbulent, which is conducive to magnet 17 collecting metal debris.

[0056] The fixed heating rod 5 and the rotating heating plate 16 heat the lubricating oil, reducing its viscosity and ensuring smooth oil supply. At the same time, the oil tank 2 is equipped with an observation window 4 for direct monitoring of the internal oil condition and level, allowing ground staff to quickly obtain oil quantity information.

[0057] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and is not intended to limit the scope of protection of this utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the scope of protection of this utility model.

Claims

1. An aircraft engine oil tank integrated with a gearbox housing, comprising a gearbox housing (1), characterized in that: The reducer housing (1) is fixedly installed with an oil tank (2) on the outside, and a connection port (3) is provided between the reducer housing (1) and the oil tank (2); A drive motor (9) is installed on the top of the lubricating oil tank (2). A rotating rod (14) is installed at the output end of the drive motor (9). A stirring plate (15) for stirring the lubricating oil is installed around the rotating rod (14). A rotating heating plate (16) is fixedly installed on the side of the stirring plate (15) facing the direction of rotation, for heating the lubricating oil at low temperature; A magnet (17) is fixedly installed on the side of the stirring plate (15) facing away from the direction of rotation, for collecting debris in the lubricating oil.

2. The aircraft engine oil tank integrated with the reducer casing according to claim 1, characterized in that: The top of the lubricating oil tank (2) has a disassembly through hole (11), and a sealing plate (10) is fixedly installed on the outside of the drive motor (9) housing. The sealing plate (10) is fixedly installed on the top of the lubricating oil tank (2) by bolts and seals the disassembly through hole (11).

3. The aircraft engine oil tank integrated with the reducer casing according to claim 2, characterized in that: A rubber pad (13) is embedded and fixedly installed at the bottom of the sealing plate (10).

4. The aircraft engine oil tank integrated with the reducer casing according to claim 1, characterized in that: An auxiliary rotating protrusion (12) is fixedly installed on the bottom inner side of the lubricating oil tank (2), and a groove (18) is provided at the bottom of the rotating rod (14). The groove (18) and the auxiliary rotating protrusion (12) are rotatably inserted into each other.

5. The aircraft engine oil tank integrated with the reducer casing according to claim 1, characterized in that: An observation window (4) is fixedly installed on the outside of the lubricating oil tank (2).

6. The aircraft engine oil tank integrated with the reducer casing according to claim 1, characterized in that: A fixed heating rod (5) is fixedly installed inside the oil tank (2).

7. The aircraft engine oil tank integrated with the reducer casing according to claim 6, characterized in that: A temperature sensor (7) is fixedly installed inside the lubricating oil tank (2), and the temperature sensor (7) is electrically connected to the fixed heating rod (5) and the rotating heating plate (16).

8. The aircraft engine oil tank integrated with the reducer casing according to claim 1, characterized in that: The bottom of the lubricating oil tank (2) is connected to and fixedly installed with an oil drain valve (6).

9. The aircraft engine oil tank integrated with the reducer casing according to claim 1, characterized in that: A metal chip sensor (8) is fixedly installed inside the lubricating oil tank (2).

10. An aircraft engine oil tank integrated with a reducer casing according to claim 1, characterized in that: The lubricating oil tank (2) is connected to the top of the reducer via an oil pump.

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