Engine lubrication system of aircraft and aircraft

Abstract

The invention discloses an aircraft engine lubricating system and an aircraft, and relates to the field of aircrafts. An engine body is integrated with a first pump; the spacer is arranged in the oil storage tank, and the spacer and the bottom wall of the oil storage tank are spaced and jointly define an oil storage space; the first pipeline is connected between the engine body and the oil storage space, and one end of the first pipeline is located between the spacer and the bottom wall; the second pipeline is connected between the engine body and the oil storage tank. The second pump is arranged on the second pipeline. Therefore, by arranging the spacer, during weight loss, the spacer can block lubricating oil so that the lubricating oil can be stored in the oil storage space all the time, the first pump can conveniently and continuously suck oil through the first pipeline, the risk that the engine is damaged due to the fact that the lubricating oil is completely sucked is reduced, and the operation reliability of the engine is improved; lubricating oil in the oil pan can be pumped into the oil storage tank, and the risk of engine oil stirring loss caused by accumulation of the lubricating oil in the oil pan is reduced.

Description

Technical Field

[0001] This invention relates to the field of aircraft, and more particularly to an engine lubrication system for an aircraft and an aircraft itself. Background Technology

[0002] In related technologies, current aircraft engine lubrication systems typically use wet sump lubrication for oil storage. However, during the aircraft's accelerated descent, weightlessness causes the lubricating oil to rise to the surface, which can lead to oil being sucked into the air and resulting in insufficient lubrication of internal engine components, potentially causing engine damage. Summary of the Invention

[0003] This invention aims to at least solve one of the technical problems existing in the prior art. Therefore, one object of this invention is to provide an engine lubrication system for aircraft, which has a reasonable structure, can reduce the risk of lubricating oil cavitation, and improve the reliability of engine operation.

[0004] The present invention further proposes an aircraft.

[0005] The engine lubrication system of an aircraft according to the present invention includes: an engine body, an oil reservoir, a spacer, a first pipeline, a second pipeline, and a second pump. The engine body integrates the first pump. The spacer is disposed within the oil reservoir, and the spacer is spaced apart from the bottom wall of the oil reservoir, together defining an oil storage space. The first pipeline is connected between the engine body and the oil storage space, and one end of the first pipeline is located between the spacer and the bottom wall. The first pump is configured to pump lubricating oil in the oil storage space into the engine body through the first pipeline. The second pipeline is connected between the engine body and the oil reservoir, and the second pump is disposed in the second pipeline and configured to pump lubricating oil in the oil pan of the engine body into the oil reservoir through the second pipeline.

[0006] According to the engine lubrication system of the aircraft of the present invention, by setting a spacer, the spacer can block the lubricating oil in the weightless state so that the oil storage space always stores lubricating oil, which facilitates the first pump to continuously draw oil through the first pipeline, reduces the risk of engine damage caused by lubricating oil being sucked into the air, and improves the operational reliability of the engine. Furthermore, by setting a second pipeline and a second pump, the lubricating oil in the oil pan can be pumped into the oil storage tank, reducing the risk of engine oil churning loss caused by the accumulation of lubricating oil in the oil pan.

[0007] In some examples of the invention, the spacer is open at one end toward the bottom wall.

[0008] In some examples of the present invention, the spacer includes: a spacer plate and a side plate, wherein one end of the spacer plate is connected to one end of the side plate so that the spacer is open toward one end of the bottom wall.

[0009] In some examples of the present invention, the spacer is formed with a first vent hole.

[0010] In some examples of the present invention, the bottom wall is formed with a connecting hole, and the first conduit passes through the connecting hole such that one end of the first conduit is located between the spacer and the bottom wall.

[0011] In some examples of the present invention, a protrusion is formed on the surface of the bottom wall facing the spacer, the protrusion having a mating hole communicating with the connecting hole, and one end of the first pipeline passing through the mating hole.

[0012] In some examples of the present invention, the engine lubrication system of the aircraft further includes: a third pipeline, wherein the oil reservoir has a second vent communicating with the interior of the oil reservoir, along the height direction of the oil reservoir (i.e., Figure 3 (as shown in the Z direction), the second vent is arranged at a height higher than the spacer, the engine body has a third vent, the third vent is arranged at a height higher than the oil pan, and the third pipeline is connected between the second vent and the third vent.

[0013] In some examples of the present invention, the second vent is formed on the top wall of the oil tank.

[0014] In some examples of the present invention, the engine lubrication system of the aircraft further includes: a controller and a level sensor, the level sensor being disposed in the oil pan, the controller being communicatively connected to the level sensor and the second pump, and the controller being configured to increase the power of the second pump when the level sensor detects that the lubricating oil level in the oil pan has reached a preset height.

[0015] The aircraft according to the present invention includes the engine lubrication system of the aircraft described above.

[0016] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0017] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which: Figure 1 This is a schematic diagram of the engine lubrication system according to an embodiment of the present invention; Figure 2This is a bottom view of the engine lubrication system (including a liquid level sensor) according to an embodiment of the present invention. Figure 3 This is a cross-sectional view of the interior of the oil storage tank according to an embodiment of the present invention (including spacers and a first pipeline).

[0018] Figure label: Engine lubrication system 100; Engine body 1; Third vent 11; Oil tank 2; bottom wall 21; connecting hole 211; protrusion 212; mating hole 2121; oil storage space 22; second vent 23; top wall 24; Spacer 3; Spacer plate 31; First vent 311; Side plate 32; First pipeline 4; Second pipeline 5; Second pump 6; Third pipeline 7; Liquid level sensor 8; Connector 9. Detailed Implementation

[0019] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0020] The following is for reference. Figures 1-3 An engine lubrication system 100 for an aircraft and an aircraft according to an embodiment of the present invention are described.

[0021] like Figures 1-3 As shown, the engine lubrication system 100 of an aircraft according to an embodiment of the present invention includes: an engine body 1, an oil tank 2, a spacer 3, a first pipeline 4, a second pipeline 5, and a second pump 6. The engine body 1 integrates the first pump; the spacer 3 is disposed in the oil tank 2, and the spacer 3 is spaced apart from the bottom wall 21 of the oil tank 2 and together defines an oil storage space 22; the first pipeline 4 is connected between the engine body 1 and the oil storage space 22, and one end of the first pipeline 4 is located between the spacer 3 and the bottom wall 21; the first pump is configured to pump the lubricating oil in the oil storage space 22 into the engine body 1 through the first pipeline 4; the second pipeline 5 is connected between the engine body 1 and the oil tank 2, and the second pump 6 is disposed in the second pipeline 5 and configured to pump the lubricating oil in the oil pan of the engine body 1 into the oil tank 2 through the second pipeline 5.

[0022] The engine body 1 integrates a first pump. As some embodiments of this application, the first pump is located inside the engine body 1. The first pump can provide power for the lubricating oil to pump the lubricating oil into the various moving parts inside the engine body 1.

[0023] Spacer 3 is disposed inside oil tank 2. Spacer 3 is spaced apart from bottom wall 21 of oil tank 2 and together defines oil storage space 22. As some embodiments of this application, along the height direction of oil tank 2 (i.e. Figure 3 (As shown in the Z direction), the spacer 3 is disposed above the bottom wall 21 of the oil tank 2 and spaced apart from the bottom wall 21. As some embodiments of this application, such as Figure 3 As shown, the engine lubrication system 100 also includes a connector 9, which is disposed in the oil reservoir 2. The connector 9 is used to connect the spacer 3 and the oil reservoir 2 so that the spacer 3 is separated from the bottom wall 21 of the oil reservoir 2 and together defines the oil storage space 22.

[0024] The first pipe 4 is connected between the engine body 1 and the oil reservoir 22, and one end of the first pipe 4 is located between the spacer 3 and the bottom wall 21. As some embodiments of this application, the lubricating oil in the oil reservoir 22 can flow to the engine body 1 through the first pipe 4. As some embodiments of this application, the connection method between the first pipe 4 and the engine body 1 and the oil reservoir 2 can be, but is not limited to, welding connection, snap-fit ​​connection, etc.

[0025] The first pump is configured to pump the lubricating oil in the oil storage space 22 into the engine body 1 through the first pipeline 4. As some embodiments of this application, the first pump is located inside the engine body 1. The first pump can provide power for the lubricating oil to pump the lubricating oil in the oil storage space 22 into the engine body 1 through the first pipeline 4.

[0026] The second pipe 5 is connected between the engine body 1 and the oil reservoir 2. Specifically, the second pipe 5 is connected between the oil pan of the engine body 1 and the oil reservoir 2. As some embodiments of this application, the lubricating oil in the oil pan can flow to the oil reservoir 2 through the second pipe 5. As some embodiments of this application, the connection method between the second pipe 5 and the engine body 1 and the oil reservoir 2 can be, but is not limited to, welding connection, snap-fit ​​connection, etc.

[0027] The second pump 6 is located in the second pipeline 5 and is configured to pump the lubricating oil in the oil pan of the engine body 1 into the oil reservoir 2 through the second pipeline 5. As some embodiments of this application, the second pump 6 can provide power for the lubricating oil to pump the lubricating oil in the oil pan into the oil reservoir 2.

[0028] It should be noted that the engine lubrication system 100 of the aircraft in this application, by setting a first pump and configuring the first pump to pump the lubricating oil in the oil storage space 22 into the engine body 1 through the first pipeline 4, can significantly improve the flow rate of the lubricating oil and enhance the lubrication effect of the engine lubrication system 100. Furthermore, by setting a spacer 3 and separating the spacer 3 from the bottom wall 21 of the oil tank 2 to jointly define the oil storage space 22, and with one end of the first pipeline 4 located between the spacer 3 and the bottom wall 21, the oil storage space 22 can always store lubricating oil under any operating condition (e.g., when the aircraft accelerates and descends), and one end of the first pipeline 4 can always be placed in the lubricating oil, which facilitates the continuous oil suction of the first pipeline 4, reduces the risk of engine damage caused by lubricating oil cavitation, and improves the operational reliability of the engine. At the same time, by setting a second pipeline 5 and a second pump 6, the lubricating oil in the oil pan can be pumped into the oil tank 2, reducing the risk of lubricating oil accumulation in the oil pan, thereby reducing the loss of oil churning in the engine. In addition, the external oil storage tank 2 makes it easier to install spacers 3 inside the oil storage tank 2, reducing assembly difficulty.

[0029] Therefore, the engine lubrication system 100 of the aircraft of this application, by setting a spacer 3, and separating the spacer 3 from the bottom wall 21 of the oil tank 2 and jointly defining the oil storage space 22, with one end of the first pipeline 4 located between the spacer 3 and the bottom wall 21, can block the lubricating oil in the weightless state so that the oil storage space 22 always stores lubricating oil, which facilitates the first pump to continuously draw oil through the first pipeline 4, reduces the risk of engine damage caused by lubricating oil cavitation, and improves the operational reliability of the engine. Furthermore, by setting a second pipeline 5 and a second pump 6, the lubricating oil in the oil pan can be pumped into the oil tank 2, reducing the risk of engine oil loss due to lubricating oil accumulation in the oil pan.

[0030] In some embodiments of the present invention, such as Figure 3 As shown, the spacer 3 is open at one end facing the bottom wall 21.

[0031] As some embodiments of this application, the spacer 3 can be constructed as a cylindrical hollow structure with one end open and the open end facing the bottom wall 21. As some embodiments of this application, the spacer 3 can be constructed as a square hollow structure with one end open and the open end facing the bottom wall 21.

[0032] This design reduces the risk of lubricating oil flowing out of the oil storage space 22 circumferentially, ensuring that the oil storage space 22 always contains lubricating oil, making it easier for one end of the first pipe 4 to be inserted into the oil storage space 22 for oil suction.

[0033] In some embodiments of the present invention, such as Figure 3As shown, the spacer 3 includes a spacer plate 31 and a side plate 32. One end of the spacer plate 31 and the side plate 32 are connected so that the spacer 3 is open at one end toward the bottom wall 21.

[0034] As some embodiments of this application, along the height direction of the oil tank 2 (i.e. Figure 3 (As shown in the Z direction), the spacer 31 is located above the side plate 32 and connected to the side plate 32. As some embodiments of this application, the connection method between the spacer 31 and the side plate 32 can be, but is not limited to, welding connection, snap-fit ​​connection, etc., or the spacer 31 and the side plate 32 can be integrally formed.

[0035] This arrangement makes the spacer 3 structurally reasonable, allowing the end of the spacer 3 facing the bottom wall 21 to be open. It also simplifies the structure of the spacer 3, reduces the processing difficulty of the spacer 3, and reduces the risk of lubricating oil flowing out of the oil storage space 22 in the circumferential direction, so that the oil storage space 22 always contains lubricating oil.

[0036] In some embodiments of the present invention, such as Figure 3 As shown, the partition plate 31 has a first vent 311.

[0037] As some embodiments of this application, the first vent 311 can communicate with the oil storage space 22, and gas can circulate between the oil storage space 22 and other spaces of the oil tank 2 through the first vent 311.

[0038] This design helps maintain the air pressure balance within the oil storage space 22, which is beneficial for the flow of lubricating oil and thus improves the lubrication effect of the engine lubrication system 100.

[0039] In some embodiments of the present invention, such as Figure 3 As shown, the bottom wall 21 has a connecting hole 211, and the first pipe 4 passes through the connecting hole 211 so that one end of the first pipe 4 is located between the spacer 3 and the bottom wall 21.

[0040] As some embodiments of this application, the first pipe 4 passes through the connecting hole 211, and one end of the first pipe 4 is higher than the lower end of the side plate 32, so that one end of the first pipe 4 extends into the oil storage space 22 to absorb oil.

[0041] This configuration makes the structure of the engine lubrication system 100 reasonable, and facilitates placing one end of the first pipe 4 between the spacer 3 and the bottom wall 21, so that the first pump can smoothly draw oil through the first pipe 4 and reduce the risk of engine damage caused by lubricating oil being sucked into the air.

[0042] In some embodiments of the present invention, such as Figure 3As shown, a protrusion 212 is formed on the surface of the bottom wall 21 facing the spacer 3. The protrusion 212 has a mating hole 2121 that communicates with the connecting hole 211. One end of the first pipe 4 passes through the mating hole 2121.

[0043] In some embodiments of this application, the axes of the mating hole 2121 and the connecting hole 211 coincide, and both the mating hole 2121 and the connecting hole 211 are adapted to one end of the first pipeline 4, along the height direction of the oil tank 2 (i.e., Figure 3 (As shown in the Z direction), one end of the first pipe 4 is sequentially inserted into the connecting hole 211 and the mating hole 2121.

[0044] By providing the protrusion 212 and the mating hole 2121, the first pipe 4 can be guided, which facilitates the assembly of the first pipe 4, improves the assembly efficiency, and makes it easier for one end of the first pipe 4 to be accurately inserted between the spacer 3 and the bottom wall 21.

[0045] In some embodiments of the present invention, such as Figure 1 and Figure 2 As shown, the aircraft's engine lubrication system 100 also includes: a third pipeline 7, and an oil tank 2 having a second vent 23 communicating with the interior of the oil tank 2, along the height direction of the oil tank 2 (i.e., Figure 3 (As shown in the Z direction), the second vent 23 is arranged at a height higher than the spacer 3, the engine body 1 has a third vent 11, the third vent 11 is arranged at a height higher than the oil pan, and the third pipe 7 is connected between the second vent 23 and the third vent 11.

[0046] The oil storage tank 2 has a second vent 23 that communicates with the inside of the oil storage tank 2. As some embodiments of this application, gas can circulate between the oil storage tank 2 and the outside through the second vent 23.

[0047] Along the height direction of oil tank 2 (i.e. Figure 3 (As shown in the Z direction), the second vent 23 is arranged at a height higher than the spacer 3. As some embodiments of this application, the second vent 23 can be arranged on the top wall 24 of the oil tank 2, or the second vent 23 can be arranged on any side of the oil tank 2 that is higher than the spacer 3.

[0048] The engine body 1 has a third vent 11. As some embodiments of this application, gas can flow between the engine body 1 and the outside through the third vent 11.

[0049] Along the height direction of oil tank 2 (i.e. Figure 3(As shown in the Z direction), the third vent 11 is arranged at a height higher than the oil pan. As some embodiments of this application, the third vent 11 can be arranged at the upper end of the engine body 1, or the third vent 11 can be arranged on any side of the engine body 1 that is higher than the oil pan.

[0050] The third pipe 7 is connected between the second vent 23 and the third vent 11. As some embodiments of this application, gas can flow between the engine body 1 and the fuel tank 2 through the third pipe 7. As some embodiments of this application, one end of the third pipe 7 passes through the second vent 23 and is connected to the fuel tank 2. The connection method between the third pipe 7 and the fuel tank 2 can be, but is not limited to, welding connection, snap-fit ​​connection, etc. The other end of the third pipe 7 passes through the third vent 11 and is connected to the engine body 1. The connection method between the third pipe 7 and the engine body 1 can be, but is not limited to, welding connection, snap-fit ​​connection, etc.

[0051] By setting a second vent 23 and a third vent 11, and connecting the third pipe 7 between the second vent 23 and the third vent 11, gas can flow between the engine body 1 and the oil reservoir 2, which helps to maintain the air pressure balance in the engine lubrication system 100, thereby reducing the difficulty of oil suction for the first pump and the second pump 6 and improving the operational stability of the engine lubrication system 100.

[0052] In some embodiments of the present invention, such as Figure 1 As shown, the second vent 23 is formed on the top wall 24 of the oil tank 2.

[0053] This design is reasonable, allowing gas to flow out of the oil tank 2 through the second vent 23 without the need for external force, thus reducing energy consumption.

[0054] In some embodiments of the present invention, such as Figure 2 As shown, the engine lubrication system 100 of the aircraft also includes: a controller and a liquid level sensor 8. The liquid level sensor 8 is located in the oil pan. The controller is communicatively connected to the liquid level sensor 8 and the second pump 6. The controller is configured to increase the power of the second pump 6 when the liquid level sensor 8 detects that the lubricating oil level in the oil pan has reached a preset height.

[0055] The level sensor 8 is located in the oil pan. As some embodiments of this application, the level sensor 8 can detect the level of lubricating oil in the oil pan.

[0056] The controller is communicatively connected to the level sensor 8 and the second pump 6. As some embodiments of this application, the controller can be connected to the level sensor 8 and the second pump 6 via wires, or the controller can be wirelessly connected to the level sensor 8 and the second pump 6.

[0057] The controller is configured to increase the power of the second pump 6 when the level sensor 8 detects that the lubricating oil level in the oil pan has reached a preset height. Specifically, when the lubricating oil level in the oil pan reaches the preset height, the level sensor 8 can be triggered. After the level sensor 8 is triggered, it can transmit the lubricating oil level information in the oil pan to the controller, and the controller can increase the power of the second pump 6 according to the information.

[0058] As some embodiments of this application, the power of the second pump 6 is higher than that of the first pump to reduce the risk of lubricating oil accumulation in the oil pan, thereby reducing the oil churning loss of the engine.

[0059] According to an embodiment of the present invention, the aircraft includes the engine lubrication system 100 of the aircraft described above. The engine lubrication system 100 of the aircraft of this application defines an oil storage space 22 by setting a spacer 3, which is spaced apart from the bottom wall 21 of the oil tank 2. One end of the first pipeline 4 is located between the spacer 3 and the bottom wall 21. In the event of weightlessness, the spacer 3 can block the lubricating oil so that the oil storage space 22 always stores lubricating oil, which facilitates the first pump to continuously draw oil through the first pipeline 4, reduces the risk of engine damage caused by lubricating oil being sucked into the air, and improves the operational reliability of the engine. Furthermore, by setting a second pipeline 5 and a second pump 6, the lubricating oil in the oil pan can be pumped into the oil tank 2, reducing the risk of engine oil loss due to lubricating oil accumulation in the oil pan.

[0060] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not 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 invention.

[0061] In the description of this invention, "first feature" and "second feature" may include one or more of the features.

[0062] In the description of this invention, "a plurality of" means two or more.

[0063] In the description of this invention, the first feature being "above" or "below" the second feature may include the first and second features being in direct contact, or it may include the first and second features not being in direct contact but being in contact through another feature between them.

[0064] In the description of this invention, the terms "above," "over," and "on top" for the first feature and the second feature include the first feature being directly above or diagonally above the second feature, or simply indicating that the first feature is at a higher horizontal level than the second feature.

[0065] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0066] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. An engine lubrication system for an aircraft, characterized in that, include: An engine body, wherein the engine body integrates a first pump; An oil storage tank and a spacer, wherein the spacer is disposed inside the oil storage tank and is spaced apart from the bottom wall of the oil storage tank and together define an oil storage space; A first pipeline is connected between the engine body and the oil reservoir, with one end of the first pipeline located between the spacer and the bottom wall. The first pump is configured to pump lubricating oil in the oil reservoir into the engine body through the first pipeline. A second pipeline and a second pump are provided. The second pipeline is connected between the engine body and the oil reservoir. The second pump is located on the second pipeline and configured to pump the lubricating oil in the oil pan of the engine body into the oil reservoir through the second pipeline.

2. The engine lubrication system of the aircraft according to claim 1, characterized in that, The spacer is open at one end toward the bottom wall.

3. The engine lubrication system of the aircraft according to claim 2, characterized in that, The spacer includes a spacer plate and a side plate, wherein one end of the spacer plate is connected to one end of the side plate so that the spacer is open toward the bottom wall.

4. The engine lubrication system of the aircraft according to claim 3, characterized in that, The partition plate has a first vent hole.

5. The engine lubrication system of the aircraft according to claim 1, characterized in that, The bottom wall has a connecting hole, and the first pipe passes through the connecting hole so that one end of the first pipe is located between the spacer and the bottom wall.

6. The engine lubrication system of the aircraft according to claim 5, characterized in that, The bottom wall has a protrusion on the surface facing the spacer, and the protrusion has a mating hole that communicates with the connecting hole. One end of the first pipeline passes through the mating hole.

7. The engine lubrication system of the aircraft according to claim 1, characterized in that, Also includes: The third pipeline has a second vent hole that communicates with the inside of the oil reservoir. Along the height direction of the oil reservoir (i.e., the Z direction shown in Figure 3), the second vent hole is arranged at a height higher than the spacer. The engine body has a third vent hole that is arranged at a height higher than the oil pan. The third pipeline is connected between the second vent hole and the third vent hole.

8. The engine lubrication system of the aircraft according to claim 7, characterized in that, The second vent is formed on the top wall of the oil tank.

9. The engine lubrication system of the aircraft according to any one of claims 1-8, characterized in that, Also includes: The controller and the liquid level sensor are located in the oil pan. The controller is communicatively connected to the liquid level sensor and the second pump. The controller is configured to increase the power of the second pump when the liquid level sensor detects that the lubricating oil level in the oil pan has reached a preset height.

10. An aircraft, characterized in that, Includes the engine lubrication system of the aircraft according to any one of claims 1-9.

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