An aircraft engine mounting section adapter

Abstract

The present invention discloses an aircraft engine mounting joint adapter, which is used to connect an engine and an aircraft mounting frame. A plurality of engine mounting joints are arranged circumferentially on the engine, and shock absorbers are arranged one by one at positions corresponding to the engine mounting joints on the aircraft mounting frame. The adapter comprises an adapter assembly having the same number as the engine mounting joints, and the adapter assembly comprises a first connecting portion and a second connecting portion fixedly connected as one, wherein the first connecting portion is suitable for being detachably connected to the engine mounting joint; and the second connecting portion is suitable for being detachably connected to the shock absorber. The present invention can realize the adaptation and installation of an engine on other aircraft mounting frames without modifying the aircraft mounting frame, thereby shortening the modification cycle and reducing the modification cost.

Description

Technical Field

[0001] The invention relates to the technical field of aero-engines, and in particular to an aero-engine mounting joint adapter. Background Art

[0002] The mounting node of an aircraft engine is the connecting structure between the engine and the aircraft. It is responsible for transmitting the thrust or pulling force of the engine to the aircraft and is an important component indispensable for the installation of an aircraft engine. Existing small and medium-sized turboprop engines mostly adopt a single-plane installation method. The mounting nodes of the engine are distributed on the same engine plane perpendicular to the engine axis. The mounting nodes located on the same engine plane perpendicular to the engine axis are directly connected to the mounting interface of the aircraft mounting frame. However, the mounting node of the engine cannot be easily changed after it is determined. When the engine needs to be installed on other aircraft mounting frames, the mounting interface of the aircraft mounting frame is generally modified to adapt to the mounting node of the engine. The modification cycle of the aircraft mounting frame is long and the cost is high. Summary of the invention

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the defects in the prior art that the engine mounting node is directly connected to the mounting interface of the aircraft mounting frame, and when it is assembled on other aircraft mounting frames, the aircraft mounting frame needs to be modified, and the modification cycle is long and the cost is high, thereby providing an aircraft engine mounting node adapter device.

[0004] According to the present invention, an aircraft engine mounting node adapter is provided, which is used to connect an engine and an aircraft mounting frame. The engine is provided with a plurality of engine mounting nodes along the circumferential direction, and shock absorbers are provided one by one at positions corresponding to the engine mounting nodes on the aircraft mounting frame. The adapter includes adapter components with the same number as the engine mounting nodes, and the adapter components include:

[0005] A first connection portion, adapted to be detachably connected to an engine mounting section;

[0006] The second connecting portion is fixedly connected to the first connecting portion and is suitable for being detachably connected to the shock absorber.

[0007] An aircraft engine mounting joint adapter according to the present invention has at least the following technical effects:

[0008] Each engine mounting joint is connected to the corresponding shock absorber through an adapter assembly, the first connection part is detachably connected to the engine mounting joint as a whole, and the second connection part is detachably connected to the shock absorber as a whole; when the engine needs to be installed on other aircraft mounting frames, that is, the spacing between the engine mounting joint and the aircraft mounting frame along the engine axis direction is different, the first connection part can be removed from the engine mounting joint, and the second connection part can be removed from the shock absorber, and the adapter assembly of the corresponding size can be replaced for adaptation, so that the engine can be adapted and installed on other aircraft mounting frames without modifying the aircraft mounting frame, shortening the modification cycle and reducing the modification cost. At the same time, by adding a shock absorber between the aircraft mounting frame and the second connection part, during the flight of the aircraft equipped with the aircraft engine mounting joint adapter device, the thrust generated by the engine propeller is transmitted to the engine mounting joint, and then transmitted from the engine mounting joint to the adapter assembly, and finally transmitted from the adapter assembly to the aircraft mounting frame through the shock absorber, thereby improving the suppression and buffering effect of the aircraft engine vibration.

[0009] Preferably, the first connection portion and the second connection portion are staggered along the thickness direction of the first connection portion, and an arc-shaped third connection portion is connected between the first connection portion and the second connection portion, and the third connection portion is suitable for being detachably connected to the end face of the engine mounting node facing the corresponding shock absorber.

[0010] Preferably, the engine mounting node is provided with at least two first internal threaded holes at the end surface facing the corresponding shock absorber; a first through hole is provided on the third connecting portion at a position corresponding to the first internal threaded hole; when the third connecting portion is connected to the engine mounting node, a first fastening bolt passes through the first through hole and is screwed into the first internal threaded hole.

[0011] Preferably, the connection between the third connection portion and the first connection portion is an arc transition.

[0012] Preferably, the end surface of the engine mounting node facing the first connecting part is provided with four second internal threaded holes in a rectangular shape, and the first connecting part is provided with a second through hole at a position corresponding to the second internal threaded hole; when the first connecting part is connected to the engine mounting node, the second fastening bolt passes through the second through hole and is screwed into the second internal threaded hole.

[0013] Preferably, a first positioning hole is provided on an end surface of the engine mounting node facing the first connecting portion, and the first connecting portion is provided with a first positioning boss matching the first positioning hole.

[0014] Preferably, a first weight-reducing hole is formed on the first positioning boss through the thickness direction of the first connecting portion.

[0015] Preferably, the end surface of the shock absorber facing the second connecting part is provided with four third internal threaded holes in a rectangular shape, and the second connecting part is provided with a third through hole at a position corresponding to the third internal threaded holes; when the second connecting part is connected to the shock absorber, the third fastening bolt passes through the third through hole and is screwed into the third internal threaded hole.

[0016] Preferably, a second positioning boss is provided on the end surface of the shock absorber facing the second connecting portion, and a second positioning hole matching the second positioning boss is provided on the second connecting portion.

[0017] Preferably, a weight-reducing groove is provided on an end surface of the second connecting portion facing the shock absorber.

[0018] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 This is a schematic diagram of the structure of a switching device of this embodiment assembled between an engine and an aircraft mounting frame;

[0021] Figure 2 is a schematic diagram of the three-dimensional structure of a switching component in a switching device of this embodiment;

[0022] Figure 3 for Figure 2 A schematic diagram of the structure from another perspective;

[0023] Figure 4 for Figure 2 A schematic diagram of the cross-section structure viewed from above.

[0024] Description of reference numerals:

[0025] 1-engine, 11-engine mounting section, 12-propeller;

[0026] 2-aircraft mounting frame, 21-shock absorber;

[0027] 3-adapter assembly, 31-first connecting part, 311-second through hole, 312-first positioning boss, 313-first weight-reducing hole, 32-second connecting part, 321-third through hole, 322-second positioning hole, 323-weight-reducing groove, 33-third connecting part, 331-first through hole. DETAILED DESCRIPTION

[0028] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. 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 creative work are within the scope of protection of the present invention.

[0029] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0032] like Figures 1 to 4The present embodiment shows an aircraft engine mounting joint adapter device, which is used to connect an engine 1 and an aircraft mounting frame 2. The engine 1 is provided with a plurality of engine mounting joints 11 along the circumferential direction, and the aircraft mounting frame 2 is provided with shock absorbers 21 at positions corresponding to the engine mounting joints 11. The adapter device includes adapter assemblies 3 having the same number as the engine mounting joints 11. The adapter assembly 3 includes a first connection portion 31 and a second connection portion 32 fixedly connected as one body. The first connection portion 31 is suitable for being detachably connected to the engine mounting joint 11; the second connection portion 32 is suitable for being detachably connected to the shock absorber 21. It can be understood that the thickness direction of the first connection portion 31 mentioned herein refers to Figure 1 and Figure 4 The first direction in the text refers to the axial direction of the engine 1. Figure 1 Axial direction in.

[0033] The adapter device of this embodiment is connected between each engine mounting node 11 and the corresponding shock absorber 21 through an adapter assembly 3, the first connection part 31 and the engine mounting node 11 are detachably connected as one body, and the second connection part 32 and the shock absorber 21 are detachably connected as one body; when the engine 1 needs to be assembled on other aircraft mounting frames 2, that is, the spacing between the engine mounting node 11 and the aircraft mounting frame 2 along the axial direction of the engine 1 is different, the first connection part 31 can be removed from the engine mounting node 11, and the second connection part 32 can be removed from the shock absorber 21, and the adapter assembly 3 of the corresponding size can be replaced for adaptation, so that the engine 1 can be adapted and installed on other aircraft mounting frames 2 without modifying the aircraft mounting frame 2, thereby shortening the modification cycle and reducing the modification cost. At the same time, by adding a shock absorber 21 between the aircraft mounting frame 2 and the second connecting portion 32, during the flight of an aircraft equipped with the aircraft engine mounting node adapter device of this embodiment, the thrust generated by the propeller 12 of the engine 1 is transmitted to the engine mounting node 11, and then transmitted from the engine mounting node 11 to the adapter assembly 3, and finally transmitted from the adapter assembly 3 to the aircraft mounting frame 2 through the shock absorber 21, thereby improving the suppression and buffering effect of the vibration of the aircraft engine 1.

[0034] Specifically, in a small or medium-sized turboprop engine 1, the number of the engine mounting sections 11 is preferably three or four.

[0035] like Figure 1 and 4As shown, optionally, the first connection part 31 and the second connection part 32 are staggered in the thickness direction of the first connection part 31, and a third connection part 33 in the shape of an arc is connected between the first connection part 31 and the second connection part 32, and the third connection part 33 is suitable for being detachably connected to the end face of the engine mounting section 11 facing the corresponding shock absorber 21 along the axial direction. By staggering the first connection part 31 and the second connection part 32, so that the first connection part 31 is connected to the outer side of the engine mounting section 11 along the thickness direction of the first connection part 31, and the second connection part 32 is connected to the inner side of the shock absorber 21 along the thickness direction of the first connection part 31, the structure is more compact and the connection is more firm. At the same time, a third connection portion 33 is added between the first connection portion 31 and the second connection portion 32. The third connection portion 33 abuts against the end surface of the engine mounting node 11, which, on the one hand, plays a positioning role so as to accurately connect the adapter assembly 3 between the engine mounting node 11 and the corresponding shock absorber 21; on the other hand, the connection area with the engine mounting node 11 is increased to ensure the tightness of the structural connection, and the axial load can be assisted in transmitting through the third connection portion 33.

[0036] like Figure 2 and Figure 3 As shown, optionally, the end surface of the engine mounting section 11 facing the corresponding shock absorber 21 is preferably provided with two first internal threaded holes; the position corresponding to the first internal threaded hole is provided with a first through hole 331 on the third connecting portion 33; when the third connecting portion 33 is connected to the engine mounting section 11, the first fastening bolt passes through the first through hole 331 and is screwed to the first internal threaded hole. The engine mounting section 11 and the third connecting portion 33 are detachably connected to form a whole by screwing the first fastening bolt and the first internal threaded hole, which can ensure the tightness of the connection and facilitate the disassembly and assembly of the two.

[0037] like Figure 4 As shown, optionally, the connection between the third connection part 33 and the first connection part 31 is an arc transition, so as to prevent interference when the first connection part 31 and the third connection part 33 are assembled with the engine mounting section 11 .

[0038] like Figure 2 and Figure 3As shown, optionally, the end surface of the engine mounting section 11 facing the first connection part 31 is rectangularly provided with four second internal threaded holes, and the first connection part 31 is provided with a second through hole 311 at a position corresponding to the second internal threaded hole; when the first connection part 31 is connected to the engine mounting section 11, the second fastening bolt passes through the second through hole 311 and is screwed to the second internal threaded hole. The engine mounting section 11 and the first connection part 31 are detachably connected to form a whole by screwing four second fastening bolts arranged in a rectangular outline to the corresponding second internal threaded holes, which can ensure the tightness of the connection, so that the aircraft equipped with the adapter device of this embodiment can be reliably launched; and it is convenient to disassemble and assemble the two.

[0039] like Figures 2 to 4 As shown, optionally, the end surface of the engine mounting section 11 facing the first connecting portion 31 is provided with a first positioning hole, and the first connecting portion 31 is provided with a first positioning boss 312 matching the first positioning hole. Through the guiding and limiting effect of the first positioning hole and the first positioning boss 312, the second internal threaded hole is quickly aligned with the corresponding second through hole 311, thereby reducing the difficulty of assembling the engine mounting section 11 and the first connecting portion 31 into one body.

[0040] like Figures 2 to 4 As shown, optionally, a first weight-reducing hole 313 is formed on the first positioning boss 312 along the thickness direction of the first connecting portion 31. The weight of the adapter assembly 3 is reduced by adding the first weight-reducing hole 313, so that the adapter device of this embodiment is lightweight, thereby ensuring that the weight of the aircraft equipped with the adapter device of this embodiment does not have a difference that affects the function compared to the weight of the existing aircraft.

[0041] like Figure 2 and Figure 3 As shown, optionally, the end surface of the shock absorber 21 facing the second connection part 32 is rectangularly provided with four third internal threaded holes, and the second connection part 32 is provided with a third through hole 321 at a position corresponding to the third internal threaded hole; when the second connection part 32 is connected to the shock absorber 21, the third fastening bolt passes through the third through hole 321 and is screwed to the third internal threaded hole. The shock absorber 21 and the second connection part 32 are detachably connected to each other as a whole by screwing four third fastening bolts arranged in a rectangular outline with the corresponding third internal threaded holes, which can ensure the tightness of the connection, so that the aircraft equipped with the adapter device of this embodiment can be reliably launched; and it is convenient to disassemble and assemble the two.

[0042] like Figures 2 to 4As shown, optionally, a second positioning boss is provided on the end surface of the shock absorber 21 facing the second connecting portion 32, and a second positioning hole 322 matching the second positioning boss is provided on the second connecting portion 32. The second positioning hole 322 and the second positioning boss are guided and limited so that the third internal threaded hole is quickly aligned with the corresponding third through hole 321, thereby reducing the difficulty of assembling the shock absorber 21 and the second connecting portion 32 into one piece.

[0043] like Figures 2 to 4 As shown, optionally, a weight-reducing groove 323 is provided on the end surface of the second connection portion 32 facing the shock absorber 21. The weight of the adapter assembly 3 is reduced by adding the weight-reducing groove 323, so that the adapter device of this embodiment is lightweight, thereby ensuring that the weight of the aircraft equipped with the adapter device of this embodiment does not have a difference that affects the function relative to the weight of the existing aircraft.

[0044] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. An aircraft engine mounting joint adapter, used to connect an engine (1) and an aircraft mounting frame (2), characterized in that: The engine (1) is provided with a plurality of engine mounting nodes (11) along the circumferential direction, and the aircraft mounting frame (2) is provided with shock absorbers (21) at positions corresponding to the engine mounting nodes (11), and the adapter device comprises adapter assemblies (3) having the same number as the engine mounting nodes (11), and the adapter assemblies (3) comprise: A first connecting portion (31) adapted to be detachably connected to the engine mounting section (11); A second connecting portion (32) is fixedly connected to the first connecting portion (31) and is suitable for being detachably connected to the shock absorber (21); The first connection portion (31) and the second connection portion (32) are staggered along the thickness direction of the first connection portion (31); a third connection portion (33) in the shape of an arc is connected between the first connection portion (31) and the second connection portion (32); the third connection portion (33) is suitable for being detachably connected to the end surface of the engine mounting node (11) facing the corresponding shock absorber (21).

2. The aircraft engine mounting joint adapter according to claim 1, characterized in that: The engine mounting joint (11) is provided with at least two first internal threaded holes on the end surface facing the corresponding shock absorber (21); a first through hole (331) is provided on the third connecting portion (33) at a position corresponding to the first internal threaded hole; when the third connecting portion (33) is connected to the engine mounting joint (11), a first fastening bolt passes through the first through hole (331) and is screwed to the first internal threaded hole.

3. The aircraft engine mounting joint adapter according to claim 2, characterized in that: The connection between the third connection portion (33) and the first connection portion (31) is an arc transition.

4. An aircraft engine mounting joint adapter according to any one of claims 1 to 3, characterized in that: The end surface of the engine mounting section (11) facing the first connecting portion (31) is provided with four second internal threaded holes in a rectangular shape, and the first connecting portion (31) is provided with a second through hole (311) at a position corresponding to the second internal threaded hole; when the first connecting portion (31) is connected to the engine mounting section (11), a second fastening bolt passes through the second through hole (311) and is screwed to the second internal threaded hole.

5. The aircraft engine mounting joint adapter according to claim 4, characterized in that: The end surface of the engine mounting section (11) facing the first connecting portion (31) is provided with a first positioning hole, and the first connecting portion (31) is provided with a first positioning boss (312) matching the first positioning hole.

6. The aircraft engine mounting joint adapter according to claim 5, characterized in that: A first weight-reducing hole (313) is formed on the first positioning boss (312) and penetrates along the thickness direction of the first connecting portion (31).

7. An aircraft engine mounting joint adapter according to any one of claims 1 to 3, characterized in that: The end surface of the shock absorber (21) facing the second connecting portion (32) is provided with four third internal threaded holes in a rectangular shape, and the second connecting portion (32) is provided with a third through hole (321) at a position corresponding to the third internal threaded holes; when the second connecting portion (32) is connected to the shock absorber (21), a third fastening bolt passes through the third through hole (321) and is screwed to the third internal threaded hole.

8. The aircraft engine mounting joint adapter according to claim 7, characterized in that: The end surface of the shock absorber (21) facing the second connecting portion (32) is provided with a second positioning boss, and the second connecting portion (32) is provided with a second positioning hole (322) matching the second positioning boss.

9. The aircraft engine mounting joint adapter according to claim 8, characterized in that: The end surface of the second connecting portion (32) facing the shock absorber (21) is provided with a weight-reducing groove (323).

Images