Split type anti-falling aero-engine borescope plug disassembling and assembling tool

Abstract

The invention belongs to the technical field of aero-engine maintenance, and particularly relates to a split type anti-falling aero-engine borescope plug disassembling and assembling tool. According to the disassembling and assembling tool, a first limiting groove and a second limiting groove are formed in the two ends of a wrench adapter respectively; one end of the inner pipe is connected with the inner pipe end, and the other end is connected with the end nut; the end nut is in threaded connection with the borescope plug screw; the outer sleeve sleeves the outer side of the inner core, one end of the outer sleeve is connected with the outer sleeve adapter, and the other end of the outer sleeve is connected with the sleeve head; a limiting outer molded surface matched with the second limiting groove is arranged on the outer sleeve adapter; a tightening part is arranged on the outer pipe and can be limited by the end of the inner pipe and an end nut, so that the outer pipe is prevented from being separated from the inner pipe; inner sleeve teeth are arranged on the sleeve head, and the sleeve head is meshed with the borescope plug self-locking nut through the sleeve teeth; the check ring is arranged on the outer pipe in a sleeving mode and can be limited by the outer sleeve adapter and the sleeve head, and the check ring is prevented from being disengaged from the outer pipe.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft engine maintenance, and in particular relates to a split anti-fall-off aircraft engine borescope plug disassembly and assembly tool. Background Art

[0002] During periodic inspections of aircraft engines, it is necessary to perform borescope inspections on high and low pressure components through the borescope hole. In the installed state, there may be situations where the aircraft cover and the borescope hole are not aligned and the disassembly and assembly space is narrow. Maintenance personnel need to complete the disassembly and assembly of the borescope plug through the aircraft cover between the engine culvert and the aircraft skin, which increases the difficulty of disassembly and assembly of the borescope plug. Especially for engines with small bypass and medium bypass ratios and double-layer casings, it is more difficult to disassemble and assemble the borescope plug on the inner casing. The disassembly and assembly tools need to penetrate the inner and outer culvert casings in a limited space, which places high demands on maintenance personnel. In addition, the borescope plug may fall off during disassembly and assembly, or the disassembly and assembly time may be too long.

[0003] At present, for self-locking internal borescope plugs, an internal wrench is generally used for disassembly and assembly. If the aircraft cover and the borescope hole are not aligned, the borescope plug can be disassembled and assembled by removing the large maintenance cover if there is one. The disadvantages of this method are high maintenance time and cost and low maintenance efficiency. For engines without large covers, disassembly and assembly by experienced maintenance personnel is a disadvantage of this method in that it requires a high level of maintenance personnel, and there are risks such as the borescope plug falling off and the disassembly and assembly time being too long. If the maintenance work cannot be completed by both methods, the design plan will be changed or the maintenance point will be cancelled through coordination between Feifa. However, changing the design plan seriously affects the development cycle of the equipment and greatly increases the design cost. Canceling the maintenance point will make it impossible to accurately identify the engine status, increasing safety hazards.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of the present application is to provide a split anti-fall-off aircraft engine borescope plug disassembly and assembly tool to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is: A split anti-falling aircraft engine borescope plug disassembly and assembly tool, comprising: An adapter wrench, the adapter wrench comprising a wrench adapter, both ends of the wrench adapter are respectively provided with a first limit groove and a second limit groove, the first limit groove is used to cooperate with a force-limiting wrench; A combined sleeve, comprising an inner core, an outer sleeve and a retaining ring; The inner core comprises an inner tube end, an inner tube and an end nut, one end of the inner tube is connected to the inner tube end, and the other end is connected to the end nut; the end nut is connected to the borescope plug screw by threading; The outer sleeve is sleeved on the outside of the inner core, and the outer sleeve includes an outer sleeve adapter, an outer tube and a sleeve head. One end of the outer tube is connected to the outer sleeve adapter, and the other end is connected to the sleeve head. The outer sleeve adapter is provided with a limiting outer profile surface that matches the second limiting groove. The outer tube is provided with a tightening part, which can be limited by the inner tube end and the end nut to prevent the outer tube from being disengaged from the inner tube. The sleeve head is provided with an inner sleeve tooth, and the sleeve head is meshed with the self-locking nut of the borescope plug through the sleeve tooth. The retaining ring is sleeved on the outer tube, and the retaining ring can be limited by the outer sleeve adapter and the sleeve head to prevent the retaining ring from being separated from the outer tube.

[0007] In at least one embodiment of the present application, a flat handle is provided on the wrench adapter.

[0008] In at least one embodiment of the present application, the first limiting groove and the second limiting groove are both square limiting grooves.

[0009] In at least one embodiment of the present application, a hollow structure is provided in the middle of the wrench adapter, and a pin hole is provided on the end of the inner tube; The adapter wrench also includes a positioning pin, which passes through the hollow structure of the wrench adapter and is inserted into the pin hole of the inner tube end.

[0010] In at least one embodiment of the present application, the adapter wrench further includes a chain, one end of the chain is connected to the wrench adapter, and the other end of the chain is connected to the locating pin.

[0011] In at least one embodiment of the present application, the inner tube is welded to the inner tube end, and the inner tube is welded to the end nut.

[0012] In at least one embodiment of the present application, the outer tube is welded to the outer sleeve adapter, and the outer tube is welded to the sleeve head.

[0013] In at least one embodiment of the present application, a weight-reducing hole is provided on the retaining ring.

[0014] The invention has at least the following beneficial technical effects: The split anti-falling aircraft engine borescope plug disassembly and assembly tool of the present application can realize the disassembly and assembly of the internal borescope plug in a narrow space. On the one hand, it solves the problem of maintenance being unable to be performed due to limited space. On the other hand, it improves maintenance efficiency, reduces the requirements for maintenance personnel, and solves the problem of the borescope plug being easy to fall off and the disassembly and assembly time being too long during the disassembly and assembly process. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a cross-sectional view of a split anti-fall-off aircraft engine borescope plug disassembly and assembly tool according to one embodiment of the present application; Figure 2 is a cross-sectional view of a combined sleeve according to an embodiment of the present application; Figure 3 is a schematic diagram of an adapter wrench according to an embodiment of the present application; Figure 4 is a schematic diagram of a combined casing according to an embodiment of the present application; Figure 5 It is a schematic diagram of a split anti-fall-off aircraft engine borescope plug disassembly and assembly tool according to one embodiment of the present application.

[0016] in: 1-wrench adapter; 2-locating pin; 3-chain; 4-inner core; 41-inner tube end; 42-inner tube; 43-end nut; 5-outer tube; 51-outer tube adapter; 52-outer tube; 53-socket head; 6-retaining ring. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0018] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application 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 operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0019] The following is combined with Figures 1 to 5 This application is described in further detail.

[0020] The present application provides a split anti-fall-off aircraft engine borescope plug disassembly and assembly tool, comprising: an adapter wrench and a combined sleeve.

[0021] like Figure 1-2 As shown, the adapter wrench includes a wrench adapter 1, and the combined sleeve includes an inner core 4, an outer sleeve 5 and a retaining ring 6, wherein the inner core 4 includes an inner tube end 41, an inner tube 42 and an end nut 43, and the outer sleeve 5 includes an outer sleeve adapter 51, an outer tube 52 and a sleeve head 53.

[0022] Specifically, the two ends of the wrench adapter 1 of the adapter wrench are respectively provided with a first limiting groove and a second limiting groove, the first limiting groove is used to cooperate with the force limiting wrench, and the second limiting groove is used to cooperate with the outer sleeve adapter 51.

[0023] In the combined casing, one end of the inner tube 42 of the inner core 4 is connected to the inner tube end 41, and the other end is connected to the end nut 43. The end nut 43 is provided with an internal thread, and the borescope plug screw is provided with an external thread. The end nut 43 is connected to the borescope plug screw through threads. The outer sleeve 5 is sleeved on the outside of the inner core 4, one end of the outer tube 52 is connected to the outer sleeve adapter 51, and the other end is connected to the sleeve head 53; the outer sleeve adapter 51 is provided with a limiting outer profile surface that cooperates with the second limiting groove; the outer tube 52 is provided with a tightening part, which can be limited by the inner tube end 41 and the end nut 43 to prevent the outer tube 52 from being disengaged from the inner tube 42; the sleeve head 53 is provided with inner sleeve teeth, and the borescope plug self-locking nut is provided with outer sleeve teeth, and the sleeve head 53 is meshed with the borescope plug self-locking nut through the sleeve teeth; the retaining ring 6 is sleeved on the outer tube 52, and the retaining ring 6 can be limited by the outer sleeve adapter 51 and the sleeve head 53 to prevent the retaining ring 6 from being disengaged from the outer tube 52.

[0024] In a preferred embodiment of the present application, Figure 3As shown, the wrench adapter 1 is provided with a straight handle for easy installation and disassembly. The first limit groove and the second limit groove at both ends of the wrench adapter 1 are both square limit grooves, and are through grooves, and the limit outer profile on the outer sleeve adapter 51 is a square limit outer profile. In this embodiment, a hollow structure is provided in the middle of the wrench adapter 1, and a pin hole is provided on the inner tube end 41. The adapter wrench also includes a positioning pin 2, which passes through the hollow structure of the wrench adapter 1 and is inserted into the pin hole of the inner tube end 41. The hollow structure design of the wrench adapter 1 is to ensure that there is enough insertion space for the positioning pin 2 on the one hand, and to achieve the purpose of weight reduction on the other hand. Advantageously, in this embodiment, the adapter wrench also includes a chain 3, one end of the chain 3 is connected to the wrench adapter 1, and the other end is connected to the positioning pin 2. The chain 3 can prevent the positioning pin 2 from falling off.

[0025] In a preferred embodiment of the present application, Figure 4 As shown, the inner tube 42 is welded to the inner tube end 41, and the inner tube 42 is welded to the end nut 43. The outer tube 52 is welded to the outer sleeve adapter 51, and the outer tube 52 is welded to the sleeve head 53. In this embodiment, the retaining ring 6 is provided with a weight reduction hole to achieve the purpose of weight reduction.

[0026] The split anti-falling aircraft engine borescope plug disassembly and assembly tool of the present application has an outer tube 52 which is a hollow tube with a tightening portion at one end, and the outer diameters of the inner tube end 41 and the end nut 43 are both larger than the inner diameter of the tightening portion of the outer tube 52, and the outer diameters of the inner tube 42 and the end nut 43 are both smaller than the inner diameter of the through tube of the outer tube 52 (the inner diameter of the non-tightening portion). This structure can ensure that the inner core 4 can rotate freely and move up and down in the outer sleeve 5 without being separated, thereby preventing the inner core 4 from falling off. At the same time, in a vertical state, when the combined sleeve is working, the overlap between the inner tube 42 and the outer tube 52 is maximized, and the tool length is minimized.

[0027] In the split anti-falling aircraft engine borescope plug disassembly and assembly tool of the present application, the inner diameter of the retaining ring 6 is larger than the outer diameter of the outer tube 52, and smaller than the maximum outer diameter of the outer sleeve adapter 51 and the sleeve head 53. This structure can ensure that the retaining ring 6 can move up and down on the outer sleeve 5 without falling off. The outer diameter of the retaining ring 6 should be larger than the aperture of the borescope hole, so as to ensure that the retaining ring 6 is always located outside the outer casing when the outer sleeve 5 is inserted into the borescope hole, preventing the outer sleeve 5 from falling between the inner casing and the outer casing.

[0028] The split anti-fall-off aircraft engine borescope plug disassembly and assembly tool of the present application is as follows Figure 5As shown, when assembling the combined sleeve, the outer sleeve 5 is first assembled with the retaining ring 6, and then the inner core 4 is assembled with the outer sleeve 5. The process of assembling the outer sleeve 5 with the retaining ring 6 is: welding the outer tube 52 with one of the outer sleeve adapter 51 and the sleeve head 53, then sleeve the retaining ring 6 on the outer tube 52, and then weld the outer tube 52 with the other of the outer sleeve adapter 51 and the sleeve head 53. The process of assembling the inner core 4 with the outer sleeve 5 is: welding the inner tube 42 with the end nut 43, then inserting the welded inner tube 42 and the end nut 43 into the outer sleeve 5, ensuring that the inner tube 42 can extend from the outer sleeve adapter 51, and welding the inner tube end 41 with the inner tube 42.

[0029] The split anti-fall-off aircraft engine borescope plug disassembly and assembly tool of the present application has the following working process: First, insert the combined sleeve into the outer culvert borescope hole through the aircraft cover. At this time, the retaining ring 6 is located outside the outer culvert casing to prevent the combined sleeve from falling between the inner casing and the outer culvert casing. By adjusting the position of the combined sleeve, ensure that the end nut 43 of the inner core 4 is aligned with the borescope plug screw, and by rotating the inner core 4, ensure that the inner core 4 is firmly connected to the borescope plug screw; then adjust the position of the outer sleeve 5 to ensure that the inner sleeve teeth of the sleeve head 53 of the outer sleeve 5 are meshed and aligned with the sleeve teeth of the self-locking nut of the borescope plug. Then, insert the square limit groove of the wrench adapter 1 of the adapter wrench into the square limit outer surface of the outer sleeve adapter 51 of the combined sleeve, and remove the self-locking borescope plug by pressing and rotating the adapter wrench. Then, take out the adapter wrench and the combined sleeve in turn according to the size of the space, and insert the positioning pin 2 into the pin hole on the inner tube end 41 of the inner core 4 to take out the disassembly and assembly tools at one time.

[0030] The split anti-falling aircraft engine borescope plug disassembly and assembly tool of the present application realizes the anti-falling function through the structure and size design, and at the same time shortens the tool length to the greatest extent, reducing the demand for maintenance space. The present application can solve the problem of poor maintainability of the internal borescope plug caused by the trade-off design without changing the original design of the engine or aircraft, greatly reducing the design cost; it can improve maintenance efficiency, reduce maintenance man-hours, and is conducive to the realization of quantitative indicators of maintainability; it reduces the requirements for maintenance personnel, solves the problem of easy falling of the borescope plug, and prevents the occurrence of secondary maintenance.

[0031] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A split anti-fall-off aircraft engine borescope plug disassembly and assembly tool, characterized in that: include: An adapter wrench, the adapter wrench comprising a wrench adapter (1), the two ends of the wrench adapter (1) being respectively provided with a first limit groove and a second limit groove, the first limit groove being used for cooperating with a force-limiting wrench; A combined sleeve, the combined sleeve comprising an inner core (4), an outer sleeve (5) and a retaining ring (6); The inner core (4) comprises an inner tube end (41), an inner tube (42) and an end nut (43); one end of the inner tube (42) is connected to the inner tube end (41), and the other end is connected to the end nut (43); the end nut (43) is connected to the borescope plugging screw by a threaded connection; The outer sleeve (5) is sleeved on the outer side of the inner core (4), and the outer sleeve (5) comprises an outer sleeve adapter (51), an outer tube (52) and a sleeve head (53); one end of the outer tube (52) is connected to the outer sleeve adapter (51), and the other end is connected to the sleeve head (53); the outer sleeve adapter (51) is provided with a limiting outer profile surface that cooperates with the second limiting groove; the outer tube (52) is provided with a tightening portion, and the tightening portion can be limited by the inner tube end (41) and the end nut (43) to prevent the outer tube (52) from being disengaged from the inner tube (42); the sleeve head (53) is provided with an inner sleeve tooth, and the sleeve head (53) is meshed with the self-locking nut of the borescope plug through the sleeve tooth; The retaining ring (6) is sleeved on the outer tube (52), and the retaining ring (6) can be limited by the outer sleeve adapter (51) and the sleeve head (53) to prevent the retaining ring (6) from being separated from the outer tube (52).

2. The split anti-fall-off aircraft engine borescope plug disassembly and assembly tool according to claim 1 is characterized in that: The wrench adapter (1) is provided with a straight handle.

3. The split anti-fall-off aircraft engine borescope plug disassembly and assembly tool according to claim 2 is characterized in that: The first limiting groove and the second limiting groove are both square limiting grooves.

4. The split anti-fall-off aircraft engine borescope plug disassembly and assembly tool according to claim 1 is characterized in that: The middle part of the wrench adapter (1) is provided with a hollow structure, and the inner tube end (41) is provided with a pin hole; The adapter wrench further comprises a positioning pin (2), wherein the positioning pin (2) passes through the hollow structure of the wrench adapter (1) and is inserted into the pin hole of the inner tube end (41).

5. The split anti-fall-off aircraft engine borescope plug disassembly and assembly tool according to claim 4 is characterized in that: The adapter wrench further comprises a chain (3), one end of the chain (3) being connected to the wrench adapter (1), and the other end of the chain (3) being connected to the positioning pin (2).

6. The split anti-fall-off aircraft engine borescope plug disassembly and assembly tool according to claim 1 is characterized in that: The inner tube (42) is welded to the inner tube end (41), and the inner tube (42) is welded to the end nut (43).

7. The split anti-fall-off aircraft engine borescope plug disassembly and assembly tool according to claim 1 is characterized in that: The outer tube (52) is welded to the outer sleeve adapter (51), and the outer tube (52) is welded to the sleeve head (53).

8. The split anti-fall-off aircraft engine borescope plug disassembly and assembly tool according to claim 1 is characterized in that: The retaining ring (6) is provided with a weight-reducing hole.

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