A flexible cowling for an aeroengine

Abstract

This invention belongs to the field of aero-engine design, specifically relating to a flexible aero-engine cowling. To solve the problem of reliable transition and connection between the aircraft fuselage and the adjustable engine tail cowling, and to adapt to changes in engine installation and adjustment positions, compensate for relative displacement between the engine and aircraft during flight, and guide airflow, this invention comprises a cowling and elastic plates riveted together as a single unit. The front end of the elastic plate is riveted to the cowling shell, and the rear end overlaps the tail cowling, providing supplementary support through elastic deformation. This achieves a smooth transition between the aircraft fuselage and the engine tail cowling, solving the problem of collision between the engine tail cowling and the fuselage when the engine position changes during installation. It also compensates for engine sway caused by high overload during maneuvering flight, thereby protecting the engine and preventing damage to engine components. This solution has a simple structure, is lightweight, economical, and relatively quick to implement in engineering.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aero-engine design, and particularly relates to a flexible fairing of an aero-engine. BACKGROUND

[0002] The tail nozzle of the afterburning engine is an adjustable tail nozzle, and the adjustable tail fairing on the outside of which plays a fairing role is fixed on the engine. When the engine is installed on the airplane, a transition section is needed to connect the airplane body and the adjustable tail fairing of the engine.

[0003] To solve the reliable transition and connection of the airplane body and the adjustable tail fairing of the engine, to adapt to the change of the installation and adjustment position of the engine, to compensate the relative displacement of the engine and the airplane in flight, and to play a role of guiding airflow, the fairing of the engine needs to be redesigned. SUMMARY

[0004] Through the design of the flexible fairing of the aero-engine, the transition of the airplane body and the tail nozzle of the engine is achieved, the external airflow passing through the engine in flight is adjusted, and the swing of the engine in the process of the airplane maneuvering flight due to large overload is compensated, so that the engine is protected and the components of the engine are prevented from being damaged.

[0005] The present application provides a flexible fairing of an aero-engine, which comprises a plurality of elastic adjusting pieces distributed in the circumferential direction at the front end of a fairing shell and a mounting ring frame at the rear end, wherein the elastic adjusting pieces have a first transition section with a height difference, the mounting structure of the elastic adjusting pieces comprises a limiting piece, a reinforcing piece, a reinforcing ring frame, a belt plate and a lap plate, the reinforcing ring frame is mounted at the front end of the fairing shell, the elastic adjusting pieces are mounted on the reinforcing ring frame through the reinforcing piece, the reinforcing piece has a first arch-shaped structure opposite to the first transition section, the limiting piece is mounted on the same side of the elastic adjusting piece and has a second transition section with a height difference, and the nesting and limiting of adjacent elastic adjusting pieces are realized through the limiting piece; the belt plate is press-fitted on the lap plate at the connecting area of the reinforcing piece and the reinforcing ring frame.

[0006] Advantageously, the elastic adjusting piece is divided into a front end part and a rear end part by the first transition section, the front end part is longer and comprises a sunken groove in the length direction, and the front end part and the rear end part both have mounting holes, and the front end part is radially outward relative to the rear end part after installation.

[0007] Advantageously, the reinforcing piece is divided into a front end part and a rear end part by the first arch-shaped structure, the front end part of the reinforcing piece is connected with the front end part of the elastic adjusting piece in a fit manner, and the rear end part of the reinforcing piece is connected with the rear end part of the elastic adjusting piece in a fit manner.

[0008] Advantageously, the reinforcing ring frame is composed of multiple sections that are evenly divided and has a second arch-shaped structure extending in the circumferential direction, and the lap plate has a third arch-shaped structure covering the second arch-shaped structure.

[0009] Advantageously, the band plate is located between the first arched structure and the second arched structure.

[0010] Advantageously, the material of the band plate is stainless steel.

[0011] Advantageously, the band plate is composed of multiple segments that are evenly divided, and the number of segments is consistent with the number of segments of the reinforcing ring frame.

[0012] Advantageously, the reinforcing ring frame and the band plate each include four segments.

[0013] Advantageously, there are 48 elastic adjusting pieces that are evenly distributed in the circumferential direction, and adjacent elastic adjusting pieces overlap each other.

[0014] Advantageously, there is a skin on the outer surface of the fairing shell.

[0015] The present application provides a fairing solution, which is an integral whole formed by a fairing and elastic pieces through riveting. The front ends of the elastic adjusting pieces are riveted on the fairing shell, and the rear ends of the elastic adjusting pieces are overlapped on the tail cover, and play a compensating role through elastic deformation.

[0016] Beneficial effects: The flexible fairing of the present application realizes smooth transition of the aircraft body and the engine tail cover, solves the problem of collision between the engine tail cover and the body when the position changes during engine installation, compensates for the engine swing caused by large overload during maneuvering flight, thereby protecting the engine and preventing damage to the components of the engine. The scheme has a simple structure, light weight, good economy, and relatively fast engineering implementation. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a structure schematic diagram of the aero-engine and the flexible fairing after assembly;

[0018] Figure 2 is a front side schematic diagram of the flexible fairing;

[0019] Figure 3 is a rear side schematic diagram of the flexible fairing;

[0020] Figure 4 is a partial enlarged view of Figure 2 ;

[0021] Figure 5 is a partial enlarged view of Figure 4 ;

[0022] Figure 6 is a structure schematic diagram of the reinforcing ring frame;

[0023] Figure 7 is a structure schematic diagram of the elastic adjusting piece;

[0024] Figure 8is a structural diagram of the limiting sheet;

[0025] Figure 9 is a structural diagram of the reinforcing sheet.

[0026] 1 - engine tail cover, 2 - elastic adjusting sheet, 3 - fairing shell, 4 - reinforcing ring frame, 5 - belt plate, 6 - lap plate, 7 - mounting ring frame, 8 - skin, 9 - first transition section, 10 - second transition section, 11 - first arch structure, 12 - limiting sheet, 13 - reinforcing sheet, 14 - second arch structure, 15 - third arch structure DETAILED DESCRIPTION

[0027] Referring to Figures 1-3 the embodiment shown, the flexible fairing of the present application includes elastic adjusting sheets 2 mounted at the front end of the fairing shell 3 and a mounting ring frame 7 at the rear end of the fairing shell 3, and has a skin 8 on the outer surface of the fairing shell 3. The fairing shell is connected to the fuselage of the aircraft by bolts. When combined with an aero-engine, the engine tail cover 1 is wrapped in the elastic adjusting sheet 2 at the front end of the flexible fairing.

[0028] Referring to Figures 4-5 , the mounting structure of the elastic adjusting sheet 2 includes a limiting sheet 12, a reinforcing sheet 13, a reinforcing ring frame 4, a belt plate 5 and a lap plate 6. The elastic adjusting sheets 2 are arranged circumferentially, and the minimum distance between adjacent elastic adjusting sheets 2 is limited by the limiting sheet 12. The elastic adjusting sheet 2 is fixed at the front end of the reinforcing ring frame 4 at the root through the reinforcing sheet 13, and the rear end of the reinforcing ring frame 4 is fixed on the fairing shell 3. A belt plate 5 is also press-fitted on the mounting area of the reinforcing sheet 13 and the reinforcing ring frame 4, the front end of the belt plate 5 is pressed tightly by the lap plate 6, and the rear end of the lap plate 6 is connected to the rear end of the reinforcing ring frame 4. The lap plate 6 has a third arch structure 15 in the middle.

[0029] The structure of the reinforcing ring frame 4 is shown in Figure 6 , which has a ring-shaped second arch structure 14 in the middle, the part at the rear side of the second arch structure is fixed at the front end of the fairing shell 3, and the part at the front side is the basis for mounting other structures. The reinforcing ring frame 4 is composed of 4 sections and is evenly distributed on the fairing, which plays a role in stabilizing the structure of the fairing barrel. The belt plate 5 also includes 4 sections and is made of stainless steel, which can make the stress distribution of each elastic adjusting sheet 1 and reinforcing sheet 3 more uniform.

[0030] The structure of the elastic adjusting sheet 2 is shown in Figure 7 , which includes a sheet structure with a height difference, which is transitioned by a first transition section 9 for smooth transition with the front structure of the fairing. The sheet structure at the front end has a sunken groove along the length direction, which is used to enhance the stiffness of the elastic adjusting sheet 2, and has a plurality of rivet holes on the two-part sheet structure. There are 48 elastic adjusting sheets 1 and reinforcing sheets 3 arranged circumferentially. The elastic adjusting sheet 2, the reinforcing sheet 13 and the belt plate 5 are riveted on the reinforcing ring frame 4 by rivets.

[0031] The 48 elastic adjusting pieces 2 are evenly distributed in the circumferential direction, each elastic adjusting piece 1 is overlapped with each other, a limiting piece 2 is riveted on each elastic adjusting piece 1 for limiting the movement of the adjacent elastic piece, and a reinforcing piece 3 is arranged above the front end of each elastic adjusting piece 1 for increasing the rigidity of the elastic piece.

[0032] Referring to Figure 8 The limiting piece 12 comprises a sheet structure with a height difference, and a second transition section 10 is arranged between the two sheet structures. One end of the limiting piece 12 is mounted on one side of the elastic adjusting piece 2.

[0033] Referring to Figure 9 The reinforcing piece comprises a sheet structure with a height difference, and a first arch-shaped structure 11 is arranged between the two sheet structures.

[0034] The mounting ring 7 is provided with four mounting holes for bolt connection of the fairing and the aircraft body, and two positioning holes are further designed for positioning during the installation of the fairing. The front end face of the mounting ring 7 is mounted on the aircraft body through the four mounting holes.

[0035] The skin 8 is provided with four cover openings 8-1 for facilitating the tightening of the nuts after installation. The skin 8 is riveted on the mounting ring 7 and the reinforcing ring 4 at the front and rear ends, respectively.

Claims

1. An aircraft engine flexible cowl, characterized by: The rectifier cover shell (3) is provided with a plurality of elastic tuning pieces (2) and a mounting ring frame (7) at the front end, wherein the elastic tuning piece (2) has a first transition section (9) with a height difference, the mounting structure of the elastic tuning piece (2) comprises a limiting piece (12), a reinforcing piece (13), a reinforcing ring frame (4), a belt plate (5) and a lap plate (6), the reinforcing ring frame (4) is mounted at the front end of the rectifier cover shell (3), the elastic tuning piece (2) is mounted on the reinforcing ring frame (4) through the reinforcing piece (13), the reinforcing piece (13) has a first arch structure (11) opposite to the first transition section (9), the limiting piece (12) is mounted on the same side of the elastic tuning piece (2), the limiting piece (12) has a second transition section (10) with a height difference, the nesting and limiting of adjacent elastic tuning pieces (2) are realized through the limiting piece (12); the belt plate (5) is press-fitted through the lap plate (6) at the connecting area of the reinforcing piece (13) and the reinforcing ring frame (4).

2. The flexible nacelle of claim 1, wherein: The elastic tuning piece (2) is divided into a front end part and a rear end part by the first transition section (9), the front end part is longer and includes a sunken groove in the length direction, the front end part and the rear end part both have mounting holes, and the front end part is radially outward relative to the rear end part after installation.

3. The aeroengine flexible cowling of claim 2, wherein: The reinforcing piece (13) is divided into a front end part and a rear end part by the first arch structure (11), the front end part of the reinforcing piece (13) is connected with the front end part of the elastic tuning piece (2), and the rear end part of the reinforcing piece (13) is connected with the rear end part of the elastic tuning piece (2).

4. The flexible nacelle of claim 1, wherein: The reinforcing ring frame (4) is composed of multiple sections, has a second arch structure (14) extending in the circumferential direction, and the lap plate (6) has a third arch structure (15) covering the second arch structure (14).

5. The flexible nacelle of claim 4, wherein: The belt plate (5) is located between the first arch structure (11) and the second arch structure (14).

6. The flexible nacelle of claim 4, wherein: The material of the belt plate (5) is stainless steel.

7. The flexible nacelle of claim 4, wherein: The belt plate (5) is composed of multiple sections, and the number of sections is consistent with the number of sections of the reinforcing ring frame (4).

8. The aeroengine flexible cowling of claim 7, wherein: The reinforcing ring frame (4) and the belt plate (5) both comprise four sections.

9. The flexible nacelle of claim 1, wherein: There are 48 elastic tuning pieces (2) evenly distributed in the circumferential direction, and adjacent elastic tuning pieces (2) are overlapped with each other.

10. The flexible nacelle of claim 1, wherein: The rectifier cover shell (3) has a skin (8) on the outer surface.

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