Leaked oil collecting device of aero-engine

Abstract

The utility model belongs to the field of aero-engines, and discloses an aero-engine oil leakage collecting device which comprises an oil leakage box and a fixed cover plate. The top of the oil leakage box is provided with at least one quick-insertion pipe orifice, one half of the quick-insertion pipe orifice is a semi-arc fixed at the top of the oil leakage box, the other half of the quick-insertion pipe orifice is a U-shaped groove of the fixed cover plate, and after the fixed cover plate is arranged on the top surface of the oil leakage box, the semi-arc of the oil leakage box and the U-shaped groove of the fixed cover plate are combined to form a circular opening of the quick-insertion pipe orifice; a filler neck is arranged at the bottom of the oil leakage box. The main body of the leaked oil collecting device of the aero-engine is a sheet metal part, the structure is simple, machining is easy, through the structural design of the integrated multifunctional leaked oil box, the S-shaped bent section, the fixed cover plate with the U-shaped opening and the H-shaped pipe joint, the connecting structure is greatly simplified, and a large number of connecting pieces such as connecting pipe joints, outer sleeve nuts and pipe sleeves are reduced. The leaked oil collecting device of the aero-engine is simple and compact in structure, a large number of connecting structures are reduced, assembling and disassembling operation is convenient, a leaked liquid discharging system of the aero-engine can be simplified, the weight is reduced, and cost is reduced.

Description

Technical Field

[0001] The utility model belongs to the field of aviation engines and relates to a downstream collection device for an oil leakage pipeline, in particular to an aviation engine oil leakage collection device. Background Art

[0002] Since the seals of the engine main shaft, fuel pump and gearbox output shaft are non-contact seals, a small amount of lubricating oil will leak out during the operation of the aircraft engine, especially in the transition state. Therefore, there should be a leaked lubricating oil recovery design to discharge the leaked lubricating oil out of the aircraft.

[0003] In addition, when the engine is operating abnormally or accelerating normally to a certain speed, the controller drives the starting fuel drain valve to open, and uses the back pressure of the combustion chamber to blow the remaining fuel between the starting nozzle and the starting fuel drain valve to the engine drain port to prevent carbon deposits on the starting nozzle; after the engine stops, the drain valve automatically opens under the action of the back pressure of the combustion chamber, blowing the remaining fuel in the engine to the engine drain port to prevent oil accumulation in the engine.

[0004] Currently, the leakage oil discharge structure of aircraft engines is a single pipeline connected to the pipeline of the aircraft drainage system through an outer sleeve nut, or the leakage oil pipe is connected to the oil collection tank through an outer sleeve nut, and then connected to the pipeline of the aircraft drainage system through the oil collection tank. This has a large number of connectors and a redundant connection structure design, which increases the weight of the engine and makes assembly and disassembly inconvenient. Utility Model Content

[0005] Based on the above problems, the utility model provides an aircraft engine oil leakage collection device with a simple and compact structure, reducing a large number of connection structures, light structure weight, and easy assembly and disassembly. The designed structure adopts a large number of sheet metal parts to be integrally formed, with a short processing cycle and low processing cost.

[0006] The technical solution of the utility model is as follows:

[0007] An aircraft engine oil leakage collection device comprises an oil leakage box and a fixed cover plate; at least one quick-plug pipe port is provided on the top of the oil leakage box, half of the quick-plug pipe port is a semicircular arc fixed to the top of the oil leakage box, and the other half of the quick-plug pipe port is a U-shaped groove of the fixed cover plate. After the fixed cover plate is installed on the top surface of the oil leakage box, the semicircular arc of the oil leakage box and the U-shaped groove of the fixed cover plate are combined to form a circular opening of the quick-plug pipe port; a pipe nozzle is provided at the bottom of the oil leakage box.

[0008] Furthermore, it also includes connecting bolts, ear structures are provided at both ends of the fixed cover plate, and connecting holes are provided at both ends of the oil leakage box. The ear structure of the fixed cover plate and the connecting hole position of the oil leakage box match each other, and the ear structure and the connecting hole are connected by connecting bolts.

[0009] Furthermore, the back of the oil leakage box is a fan-shaped mounting edge, which fits the engine casing, and the fan-shaped mounting edge is provided with mounting holes corresponding to the mounting holes of the engine casing.

[0010] Furthermore, it also includes an H-type pipe joint. The bottom of the aircraft oil leakage pipeline is an H-type pipe joint, and the diameter and gap of the H-type pipe joint match the quick-plug pipe port.

[0011] Furthermore, the oil leak box includes an oil leak box shell, a baffle, a self-locking nut and a tapered pipe joint. The baffle is arranged on the top of the oil leak box shell and is provided with at least one semicircular arc. The self-locking nut is arranged inside the connecting hole and connected with the connecting bolt. The tapered pipe joint is the connecting nozzle at the bottom of the oil leak box.

[0012] Furthermore, the fixed cover plate has an S-shaped curved section, the S-shaped low plane portion of the fixed cover plate matches the portion of the top of the oil leakage box shell without a baffle, the S-shaped high plane portion of the fixed cover plate is placed above the baffle, and the S-shaped high plane portion of the fixed cover plate is a U-shaped groove, which is combined with the semicircular arc of the baffle to form a quick-plug pipe port that matches the H-type pipe joint.

[0013] The utility model has the following beneficial effects:

[0014] The main body of this aircraft engine oil leakage collection device is entirely sheet metal, offering a simple and easy-to-machine structure. The integrated multifunctional oil leakage box, an S-shaped curved section, a fixed cover plate with a U-shaped opening, and an H-shaped pipe joint significantly simplify the connection structure, eliminating numerous connecting components such as pipe joints, outer nuts, and pipe sleeves. This simple and compact aircraft engine oil leakage collection device eliminates numerous connecting components, allowing for easy assembly and disassembly, simplifying the aircraft engine leakage drainage system, reducing weight, and lowering costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solution of the implementation method of the utility model patent, the following is a brief introduction to the drawings required for use in the implementation method. It should be understood that the following drawings only show certain embodiments of the utility model patent and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 It is a structural diagram of an aircraft engine oil leakage collection device.

[0017] Figure 2 Schematic diagram of the structure of the oil leakage box.

[0018] Figure 3 It is a structural diagram of the oil leakage box shell.

[0019] Figure 4 It is a structural diagram of an H-type pipe joint.

[0020] Figure 5 It is a schematic diagram of the use of the oil leakage collection device in the preferred embodiment of the utility model.

[0021] Among them, 1 is the oil leakage box, 2 is the fixed cover plate, 3 is the connecting bolt, 11 is the oil leakage box shell, 12 is the baffle, 13 is the self-locking nut, and 14 is the tapered pipe joint. DETAILED DESCRIPTION

[0022] This section is an embodiment of the present invention, which is used to explain and illustrate the technical solution of the present invention. In the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0023] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicating directions or positional relationships are based on the orientations or positional relationships in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the device or case referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second" and the like are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implying the number of technical features indicated. Therefore, features defined as "first", "second" and the like may explicitly or implicitly include more of such features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0024] In the description of this utility model, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integrated connections; mechanical connections, point connections; direct connections, indirect connections through an intermediate medium, and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on specific circumstances.

[0025] Example 1:

[0026] An aircraft engine oil leakage collection device includes an oil leakage box 1 and a fixed cover plate 2; at least one quick-plug pipe port is provided on the top of the oil leakage box 1, half of the quick-plug pipe port is a semicircular arc fixed on the top of the oil leakage box 1, and the other half of the quick-plug pipe port is a U-shaped groove of the fixed cover plate 2. After the fixed cover plate 2 is installed on the top surface of the oil leakage box 1, the semicircular arc of the oil leakage box 1 and the U-shaped groove of the fixed cover plate 2 are combined to form a circular opening of the quick-plug pipe port; a pipe nozzle is provided at the bottom of the oil leakage box 1.

[0027] It also includes connecting bolts 3, ear structures are provided at both ends of the fixed cover plate 2, and connecting holes are provided at both ends of the oil leakage box 1. The ear structure of the fixed cover plate 2 matches the position of the connecting hole of the oil leakage box 1, and the ear structure and the connecting hole are connected by connecting bolts 3.

[0028] The back of the oil leakage box 1 is a fan-shaped mounting edge, which fits the engine casing. The fan-shaped mounting edge is provided with mounting holes corresponding to the mounting holes of the engine casing.

[0029] It also includes an H-type pipe joint 4. The bottom of the aircraft oil leakage pipeline is the H-type pipe joint 4. The diameter and gap of the H-type pipe joint 4 match the quick-plug pipe port.

[0030] The oil leakage box 1 includes an oil leakage box shell 11, a baffle 12, a self-locking nut 13 and a tapered pipe joint 14. The baffle 12 is arranged on the top of the oil leakage box shell 11 and is provided with at least one semicircular arc. The self-locking nut 13 is arranged inside the connecting hole and connected to the connecting bolt 3. The tapered pipe joint 14 is the pipe nozzle at the bottom of the oil leakage box 1.

[0031] The fixed cover plate 2 has an S-shaped curved section. The S-shaped low plane portion of the fixed cover plate 2 matches the portion of the top of the oil leakage box housing 11 without the baffle 12. The S-shaped high plane portion of the fixed cover plate 2 is placed above the baffle 12. The S-shaped high plane portion of the fixed cover plate 2 is a U-shaped groove, which is combined with the semicircular arc of the baffle 12 to form a quick-plug pipe port that matches the H-type pipe joint 4.

[0032] Example 2:

[0033] like Figure 1 As shown, the aircraft engine oil leakage collection device of the present invention comprises an oil leakage box 1, a fixed cover plate 2, and connecting bolts 3. The oil leakage box 1 is designed with a fan-shaped mounting edge to fit snugly against the engine casing, and the mounting holes correspond to the mounting holes of the engine casing. The oil leakage box 1 fits snugly against the S-shaped curved extension of the fixed cover plate 2 and is secured by connecting bolts 3. The oil leakage box 1 is designed with a tapered pipe joint to connect to the aircraft's main oil leakage pipe via the pipe joint.

[0034] like Figure 2As shown, the oil leakage box 1 is composed of an oil leakage box housing 11, a baffle 12, a self-locking nut 13 and a tapered pipe joint 14. The baffle 12, the self-locking nut 13 and the tapered pipe joint 14 are fixed to the oil leakage box housing 11 by welding.

[0035] like Figure 3 As shown, the oil leakage box housing 11 is a U-shaped structure formed by integrated sheet metal, with a fan-shaped mounting edge designed on the front side, mounting holes matching the connecting bolts 3 designed on the left and right sides, and a mounting hole for the tapered pipe joint 14 reserved at the bottom.

[0036] The baffle 12 has an S-shaped fitting section that cooperates with the fixed cover plate 2 and a plurality of semicircular holes corresponding to the fixed cover plate 2, which are formed by sheet metal.

[0037] The fixed cover plate 2 has an S-shaped curved section and multiple U-shaped openings to achieve compression of the pipeline with the H-shaped pipe joint 4, and has left and right flanged lugs to achieve fitting and fixation with the oil leakage box shell 11, and is formed by sheet metal.

[0038] In addition, if Figure 4 As shown, the present invention provides an H-shaped pipe joint 4 to match the structure of the oil leakage box 1 and the fixed cover plate 2 of the oil leakage collection device of the present invention.

[0039] The H-shaped pipe joint 4 has an H-shaped structure with openings on both sides, and the notches on both sides correspond to the U-shaped opening structure of the fixed cover plate 2 .

[0040] When the oil leakage collection device is used, the oil leakage box 1 is fixed to the engine casing through the mounting hole of the fan-shaped mounting edge, the relevant oil leakage pipeline with the H-type pipe joint 4 is installed, one side of the H-type pipe joint 4 is pressed against the baffle 12 of the oil leakage box 1, the fixed cover plate 2 is moved horizontally through the oil leakage box 1 and clamped to the H-type pipe joint 4, and finally the fixed cover plate 2 is fixed to the oil leakage box 1 by the connecting bolts 3.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the field can easily think of various equivalent modifications or replacements within the technical scope disclosed in the present invention, and these modifications or replacements should all be included in the protection scope of the present invention.

Claims

1. An aircraft engine oil leakage collection device, characterized in that: The oil leakage box (1) comprises an oil leakage box (1) and a fixed cover plate (2); the top of the oil leakage box (1) is provided with at least one quick-plug pipe port, half of which is a semicircular arc fixed to the top of the oil leakage box (1), and the other half of which is a U-shaped groove of the fixed cover plate (2); after the fixed cover plate (2) is mounted on the top surface of the oil leakage box (1), the semicircular arc of the oil leakage box (1) and the U-shaped groove of the fixed cover plate (2) are combined to form a circular opening of the quick-plug pipe port; A receiving nozzle is provided at the bottom of the oil leakage box (1).

2. The aircraft engine oil leakage collection device according to claim 1, characterized in that: It also includes connecting bolts (3), ear structures are provided at both ends of the fixed cover plate (2), and connecting holes are provided at both ends of the oil leakage box (1), the ear structures of the fixed cover plate (2) and the connecting holes of the oil leakage box (1) are matched in position, and the ear structures and the connecting holes are connected via the connecting bolts (3).

3. The aircraft engine oil leakage collection device according to claim 1, characterized in that: The back of the oil leakage box (1) is a fan-shaped mounting edge, which is fitted with the engine casing, and the fan-shaped mounting edge is provided with mounting holes corresponding to the mounting holes of the engine casing.

4. The aircraft engine oil leakage collection device according to claim 2, characterized in that: It also includes an H-type pipe joint (4). The bottom of the aircraft oil leakage pipeline is the H-type pipe joint (4). The diameter and gap of the H-type pipe joint (4) match the quick-plug pipe port.

5. The aircraft engine oil leakage collection device according to claim 4, characterized in that: The oil leakage box (1) comprises an oil leakage box housing (11), a baffle (12), a self-locking nut (13) and a tapered pipe joint (14). The baffle (12) is arranged on the top of the oil leakage box housing (11) and is provided with at least one semicircular arc. The self-locking nut (13) is arranged inside the connecting hole and is connected to the connecting bolt (3). The tapered pipe joint (14) is a pipe nozzle at the bottom of the oil leakage box (1).

6. The aircraft engine oil leakage collection device according to claim 5, characterized in that: The fixed cover plate (2) has an S-shaped curved section. The S-shaped low plane portion of the fixed cover plate (2) matches the portion of the top of the oil leakage box shell (11) without the baffle (12). The S-shaped high plane portion of the fixed cover plate (2) is placed above the baffle (12). The S-shaped high plane portion of the fixed cover plate (2) is a U-shaped groove, which is combined with the semicircular arc of the baffle (12) to form a quick-plug pipe port that matches the H-shaped pipe joint (4).

Images