Lubricating oil tank of aero-engine

Abstract

The invention belongs to the field of aero-engines, and particularly relates to an aero-engine lubricating oil tank which comprises a lubricating oil tank body, the lubricating oil tank body is provided with an upper oil tank and a lower oil tank, an oil tank partition plate is arranged between the upper oil tank and the lower oil tank, and a plurality of oil through holes communicating the upper oil tank with the lower oil tank are formed in the oil tank partition plate; the aperture of the oil through hole is gradually reduced from the upper oil tank to the lower oil tank; the side wall of the oil tank body is provided with an oil way communicated with the lower oil tank and the oil supply port. According to the invention, the oil through holes with variable apertures are formed, and the difference of the flowing speeds of the oil through holes in two directions is fully utilized, so that lubricating oil can quickly flow into the lower oil tank from the upper oil tank, and the unavailable volume of the lubricating oil in the instantaneous maneuvering large attitude is reduced; and the speed of the lubricating oil flowing from the lower oil tank to the upper oil tank is slowed down, so that the lubricating oil in the inner cavity of the lower oil tank is slightly influenced by large posture change, and the lubricating oil supply within a certain time can be ensured.

Description

Technical Field

[0001] The invention belongs to the field of aviation engines, and in particular relates to an aviation engine lubricating oil tank. Background Art

[0002] The lubricating oil tank 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. The lubricating oil system should have a lubricating oil storage device, namely the lubricating oil tank, to provide continuous replenishment capacity for the engine's lubricating oil consumption.

[0003] The total oil volume of an aircraft engine oil tank includes usable oil volume, unusable oil volume, and oil throughput volume. Due to the shape and size of the oil tank and its supply passages, and the need to accommodate large flight attitudes, the unusable volume accounts for a high proportion of the total volume.

[0004] The unusable volume directly affects the oil demand and the volume of the oil tank, which in turn affects the size and weight of the engine; therefore, in order to reduce the size and weight of the engine and thus improve the thrust-to-weight ratio of the aircraft, the unusable volume should be reduced as much as possible.

[0005] In view of this, the present invention is proposed. Summary of the Invention

[0006] In order to solve the technical problems existing in the prior art, the present invention provides an aircraft engine lubricating oil tank. The present invention provides an oil through hole with a variable aperture, fully utilizing the difference in flow velocity in two directions of the oil through hole, so that the lubricating oil can flow quickly from the upper oil tank to the lower oil tank, which has the advantage of reducing the unusable volume of lubricating oil during instantaneous maneuvering and large attitude flight. That is, during instantaneous maneuvering and large attitude flight, the speed of the lubricating oil flowing from the lower oil tank to the upper oil tank will become much slower, so the lubricating oil in the internal cavity of the lower oil tank is little affected by large attitude changes, and the lubricating oil supply can be ensured within a certain period of time.

[0007] The present invention includes the following technical solutions: The present invention provides an aircraft engine oil tank, comprising an oil tank body, wherein the oil tank body is provided with an upper oil tank and a lower oil tank, an oil tank partition is provided between the upper oil tank and the lower oil tank, and a plurality of oil holes connecting the upper oil tank and the lower oil tank are provided on the oil tank partition; the apertures of the oil holes gradually decrease from the upper oil tank to the lower oil tank; the upper oil tank is provided with an oil supply port, and an oil path connecting the lower oil tank and the oil supply port is provided on the side wall of the oil tank body.

[0008] Furthermore, a filtering mechanism is provided in the lower oil tank, and the filtering mechanism filters the lubricating oil entering the oil circuit.

[0009] Furthermore, the filtering mechanism is arranged below the fuel tank partition.

[0010] Furthermore, the filtering mechanism includes an oil supply channel and a filter screen. The filter screen is arranged outside the oil supply channel. The lubricating oil entering the lower oil tank passes through the filter screen and then enters the oil supply channel. The oil supply channel is connected to the oil circuit.

[0011] Furthermore, an oil outlet is provided at one axial end of the oil supply channel, and the oil outlet is communicated with the oil circuit.

[0012] Furthermore, the oil circuit includes a first oil circuit and a second oil circuit, the upper end of the first oil circuit is connected to the oil supply port, the lower end is connected to one end of the second oil circuit, and the other end of the second oil circuit is connected to the oil outlet of the filter mechanism.

[0013] Furthermore, it also includes a first partition and a second partition, the first partition is vertically arranged in the oil tank body, and encloses the first oil circuit with the wall surface of the oil tank body; the second partition is horizontally arranged, and encloses the second oil circuit with the bottom surface of the oil tank body.

[0014] Furthermore, it is characterized in that the filtering mechanism is detachably connected in the lower oil tank.

[0015] Furthermore, it is characterized in that the lower oil tank is provided with an oil drain port.

[0016] Furthermore, the oil supply port is connected to a lubricating oil pump mounting seat.

[0017] By adopting the above technical solution, the present invention has the following advantages: 1. The present invention utilizes the difference in flow velocity in two directions through the oil holes by providing them with variable diameters, allowing lubricating oil to flow rapidly from the upper tank to the lower tank. This has the advantage of reducing the unusable volume of lubricating oil during transient maneuvers with large attitudes. Specifically, during transient maneuvers with large attitudes, the flow rate of lubricating oil from the lower tank to the upper tank slows significantly. Therefore, the lubricating oil in the lower tank's interior is minimally affected by large attitude changes, ensuring a consistent oil supply.

[0018] 2. The lubricating oil tank of the present invention does not use a flexible hose and has the advantages of stable and reliable structure and long service life.

[0019] 3. The present invention adopts the design of dynamic and static separation oil tank to ensure that the aircraft can Able to supply sufficient lubricating oil.

[0020] 4. The present invention can effectively increase the unusable volume of sliding oil during instantaneous maneuvering and large attitude, and at the same time integrates the oil supply filter. The split design can adjust the oil supply structure according to different requirements, and can be replaced with other adapters for related tests during the scientific research and testing phase. During the acceptance inspection of the lubricating oil tank, tooling can be designed for tightness testing.

[0021] Other features and advantages of the present invention will be described in the following description, and in part will become apparent from the description, or will be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0023] Figure 1 A schematic diagram of the structure of an aircraft engine oil tank according to an embodiment of the present invention Figure 1 ; Figure 2 A schematic diagram of the structure of an aircraft engine oil tank according to an embodiment of the present invention Figure 2 ; Figure 3 Schematic diagram of the structure of the lower oil tank in an embodiment of the present invention; Figure 4 Schematic diagram of the structure of the oil hole in an embodiment of the present invention; Figure 5 This is a schematic diagram of the partial structure of an aircraft engine oil tank according to an embodiment of the present invention; Figure 6 This is a structural diagram of a filtering mechanism in an embodiment of the present invention; Figure 7 This is a structural diagram of the oil supply channel in an embodiment of the present invention; Figure 8 Schematic diagram of the structure of the fuel tank cover in an embodiment of the present invention; Figure 9 A schematic diagram of the structure of an aircraft engine oil tank according to an embodiment of the present invention Figure 3 ; In the figure, 10-lubricating oil tank body, 11-upper oil tank, 111-refueling port, 12-lower oil tank, 121-oil drain port, 20-oil tank partition, 21-oil hole, 30-oil supply port, 40-oil circuit, 41-first oil circuit, 42-second oil circuit, 50-filtering mechanism, 51-oil supply channel, 511-tapered cylindrical section, 512-limiting boss, 52-filter screen, 60-oil tank plug cover, 61-bolt mounting hole, 62-lower limit groove, 63-upper limit groove, 64-rubber ring groove, 70-first partition, 80-second partition, 90-lubricating oil pump mounting seat. DETAILED DESCRIPTION

[0024] The following description provides many different embodiments or examples for implementing different features of the present invention. The components and arrangements described in the following specific examples are only used to simplify the present invention and are only used as examples, not to limit the present invention.

[0025] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0026] This embodiment provides an aircraft engine oil tank, such as Figure 1 、 Figure 2 As shown, it includes a lubricating oil tank body 10, the lubricating oil tank body 10 is provided with an upper oil tank 11 and a lower oil tank 12, an oil tank partition 20 is provided between the upper oil tank 11 and the lower oil tank 12, and the oil tank partition 20 is provided with a plurality of oil holes 21 connecting the upper oil tank 11 and the lower oil tank 12; the aperture of the oil holes 21 gradually decreases from the upper oil tank 11 to the lower oil tank 12; the upper oil tank 11 is provided with an oil supply port 30, and an oil path 40 connecting the lower oil tank 12 and the oil supply port 30 is provided on the side wall of the oil tank body.

[0027] Based on the structure of the present invention, the oil supply port 30 is arranged at the lowest point of the oil pipe relative to the liquid level.

[0028] In some embodiments, as Figure 3 The diagram shows the structure of the lower oil tank 12. It should be noted that the cavity of the lower oil tank 12 is not shown in the figure; the oil tank partition 20 is part of the lower oil tank 12. Preferably, the upper surface of the oil tank partition 20, located within the upper oil tank 11, is curved. This not only reduces weight but also ensures that the height from the oil level to the oil port remains essentially the same at different rotation angles.

[0029] It should be noted that the present invention does not limit the shape of the oil hole 21; preferably, the oil hole 21 is funnel-shaped; Figure 4 As shown, the funnel shape has the advantage of improving the stability of the lubricating oil flow.

[0030] In some embodiments, as Figure 1 、 Figure 2 、 Figure 5As shown, a filter mechanism 50 is provided in the lower oil tank 12 to filter the lubricating oil entering the oil passage 40. Filtering the lubricating oil entering the oil passage 40 by the filter mechanism 50 prevents impurities from being transported to the lubricating oil pump and lubrication points, thereby preventing damage to the lubricating oil pump and lubrication points.

[0031] In some embodiments, the filtering mechanism 50 is disposed below the oil tank partition 20. This provides a better filtering effect on the lubricating oil.

[0032] In some embodiments, as Figure 6 As shown, the filtering mechanism 50 includes an oil supply channel 51 and a filter screen 52. The filter screen 52 is disposed on the outer surface of the oil supply channel 51. The lubricating oil entering the lower oil tank 12 passes through the filter screen 52 and then enters the oil supply channel 51. The oil supply channel 51 is connected to the oil circuit 40. This structure ensures that the lubricating oil entering the oil filter is filtered, further improving the cleanliness of the lubricating oil and thus preventing damage to the lubricating oil pump and lubrication points.

[0033] In some embodiments, an oil outlet is provided at one axial end of the oil supply passage 51, and the oil outlet is connected to the oil circuit 40. This structure ensures that the lubricating oil entering the oil filter is filtered, further improving the cleanliness of the lubricating oil and thus preventing damage to the oil pump and lubrication points.

[0034] In some embodiments, as Figure 2 As shown, the oil circuit 40 includes a first oil circuit 41 and a second oil circuit 42 . The upper end of the first oil circuit 41 is connected to the oil supply port 30 , and the lower end is connected to one end of the second oil circuit 42 . The other end of the second oil circuit 42 is connected to the oil outlet of the filtering mechanism 50 .

[0035] In some embodiments, as Figure 2 As shown, the oil tank body 10 further includes a first baffle 70 and a second baffle 80. The first baffle 70 is vertically disposed within the oil tank body 10 and, together with the wall of the oil tank body 10, encloses the first oil passage 41. The second baffle 80 is horizontally disposed and, together with the bottom surface of the oil tank body 10, encloses the second oil passage 42. This structure avoids the use of hoses and has the advantage of reducing counterweight.

[0036] In some embodiments, the filter mechanism 50 is detachably connected to the lower oil tank 12. The detachable connection facilitates cleaning and replacement of the filter mechanism 50.

[0037] For example, the lower oil tank 12 is provided with a first connecting hole and a second connecting hole, which are respectively used to connect the two ends of the oil supply channel 51; such a structure realizes the detachable connection of the filter mechanism 50; this makes it easy to clean and replace the filter mechanism 50.

[0038] For example, Figure 7 The oil supply channel 51 shown is a section of circular tube, one end of which is provided with an oil outlet is a tapered cylindrical section 511, and the first connecting hole is a conical hole with the same angle; the oil supply channel 51 and the first connecting hole are subjected to axial pressure through the compression of the wave spring to ensure that the two are tightly matched and the sealing effect is guaranteed. At the same time, this fit can improve the structural stiffness and damping.

[0039] Combine Figure 7 、 Figure 8 As shown, a hole is opened on the lower side of the oil supply channel 51 (it should be noted that Figure 7 The hole described in the figure is upward facing; in actual use, it is downward facing. Its position, shape, and size are adaptively adjusted according to the overall structure and posture requirements of the oil tank. Two stopper bosses 512 are provided at the other end of the oil supply passage 51, which mate with the stopper grooves on the oil tank cover 60. To prevent errors, the two stopper bosses 512 are of different sizes. The oil tank cover 60 primarily consists of a bolt mounting hole 61, a rubber ring groove 64, an upper stopper groove 63, and a lower stopper groove 62. The oil tank cover 60 is primarily used to seal the lower oil tank 12. Two O-rings ensure oil leakage. It is secured to the casing with bolts. The hole in the casing at the oil tank cover 60 can be used for sand removal during casting and also serves as a subsequent inspection port. A circular hole is designed on the oil tank cover 60 to mate with the oil supply passage 51. A wave spring and an adjustment washer are located within the hole. The wave spring provides compression to the oil supply passage 51, while the adjustment washer adjusts the axial distance and controls the compression of the wave spring. The upper limit groove 63 on the fuel tank cover 60 is composed of multiple grooves. The vertical through groove can facilitate the axial entry of the boss of the oil supply channel 51, and the radial groove can allow the boss of the oil supply channel 51 to rotate. After rotating to the limit position, it is released. The oil supply channel 51 moves axially under the action of the elastic force of the wave spring and is stuck in the groove, thereby preventing it from loosening. It can also simplify the disassembly process and ensure that the oil supply channel 51 can be removed together when the fuel tank cover 60 is removed.

[0040] Among them, the design of sealing the oil tank cover 60 with two O-rings improves the fire protection capability.

[0041] The oil supply channel 51 cooperates with the oil tank cover 60 through two bosses and grooves to achieve error prevention and axial limiting functions.

[0042] The lower oil tank 12 is provided with an oil drain port 121. It should be noted that the position of the oil drain port 121 is not limited in the present invention; for example, Figure 1 As shown, the oil drain port 121 may be opened at the bottom of the lower oil tank 12; Figure 2 As shown, the oil drain port 121 may be opened on the side wall of the lower oil tank 12 close to the bottom.

[0043] In some embodiments, the oil supply port 30 is connected to a lubricating oil pump mounting base 90 to facilitate the installation of the lubricating oil pump.

[0044] It should be noted that the upper fuel tank 11 is also provided with a fuel filling port 111. Figure 9 As shown, lubricating oil is gravity-fed into the upper oil tank 11 through the oil filling port 111, and then into the lower oil tank 12 through the oil through-hole 21. After the lower oil tank 12 is full of oil, oil is continuously added to fill the upper oil tank 11. During operation, after the engine is running, lubricating oil passes through the filter mechanism 50 into the oil passage 40, and then enters the lubricating oil pump through the oil supply port 30, and is then supplied to other parts requiring lubrication.

[0045] In the description of the present invention, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features indicated. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of the specified features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0046] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they may refer to fixed, detachable, or integral connections; mechanical, electrical, or intercommunication connections; direct or indirect connections through an intermediary; and may encompass internal connectivity between multiple components or interactions between multiple components. Those skilled in the art will understand the specific meanings of these terms in the present invention based on specific circumstances.

[0047] In the description of the present invention, it should be understood that all terms used to indicate orientation or positional relationships are based on the orientation or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and cannot be understood as a limitation on the present invention.

[0048] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aircraft engine oil tank, characterized in that: The invention comprises a lubricating oil tank body (10), wherein the lubricating oil tank body (10) is provided with an upper oil tank (11) and a lower oil tank (12), an oil tank partition (20) is provided between the upper oil tank (11) and the lower oil tank (12), and the oil tank partition (20) is provided with a plurality of oil holes (21) communicating with the upper oil tank (11) and the lower oil tank (12); the aperture of the oil holes (21) gradually decreases from the upper oil tank (11) to the lower oil tank (12); the upper oil tank (11) is provided with an oil supply port (30), and an oil passage (40) communicating with the lower oil tank (12) and the oil supply port (30) is provided on the side wall of the oil tank body.

2. The aircraft engine oil tank according to claim 1, characterized in that: A filtering mechanism (50) is provided in the lower oil tank (12), and the filtering mechanism (50) filters the lubricating oil entering the oil circuit (40).

3. The aircraft engine oil tank according to claim 2, characterized in that: The filtering mechanism (50) is arranged below the oil tank partition (20).

4. The aircraft engine oil tank according to claim 3, characterized in that: The filtering mechanism (50) comprises an oil supply channel (51) and a filter screen (52). The filter screen (52) is disposed outside the oil supply channel (51). The lubricating oil entering the lower oil tank (12) passes through the filter screen (52) and then enters the oil supply channel (51). The oil supply channel (51) is communicated with the oil circuit (40).

5. The aircraft engine oil tank according to claim 4, characterized in that: An oil outlet is provided at one axial end of the oil supply channel (51), and the oil outlet is communicated with the oil circuit (40).

6. The aircraft engine oil tank according to claim 5, characterized in that: The oil circuit (40) comprises a first oil circuit (41) and a second oil circuit (42). The upper end of the first oil circuit (41) is connected to the oil supply port (30), and the lower end is connected to one end of the second oil circuit (42). The other end of the second oil circuit (42) is connected to the oil outlet of the filter mechanism (50).

7. The aircraft engine oil tank according to claim 6, characterized in that: The invention also includes a first partition plate (70) and a second partition plate (80), wherein the first partition plate (70) is vertically arranged in the oil tank body (10) and encloses the first oil path (41) with the wall surface of the oil tank body (10); and the second partition plate (80) is horizontally arranged and encloses the second oil path (42) with the bottom surface of the oil tank body (10).

8. An aircraft engine oil tank according to any one of claims 2 to 7, characterized in that: The filtering mechanism (50) is detachably connected to the lower oil tank (12).

9. An aircraft engine oil tank according to any one of claims 2 to 7, characterized in that: The lower oil tank (12) is provided with an oil drain port (121).

10. The aircraft engine oil tank according to claim 1, characterized in that: The oil supply port (30) is connected to a lubricating oil pump mounting seat (90).

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