Aircraft engine nacelle front section skin

Abstract

An aircraft engine nacelle front section skin comprises a front section upper wall plate, an air inlet channel lip and a front section lower wall plate. The front section upper wall plate is located above the air inlet channel lip and the front section lower wall plate, and the air inlet channel lip is located on the front side of the front section lower wall plate. The whole front-section upper wall plate is of a semi-conical plate-shaped structure, and the air inlet lip and the upper end of the front-section lower wall plate are connected with the lower end of the front-section upper wall plate through rivets; the front end of the front section lower wall plate is connected with the rear end of the air inlet channel lip, a U-shaped groove is formed in the rear end of the air inlet channel lip, an elastic sealing strip is arranged in the U-shaped groove, and the front end of the front section lower wall plate abuts against the rear end of the air inlet channel lip and extrudes the elastic sealing strip, so that the elastic sealing strip deforms.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft manufacturing, and particularly relates to a front skin of a short nacelle of an aircraft engine. Background Art

[0002] An aircraft skin refers to a tapered component that surrounds the aircraft skeleton structure and is fixed to the skeleton with an adhesive or rivets to form the aerodynamic shape of the aircraft. The aircraft skin consists of multiple parts, and the connection of the skins of each part ensures the overall stiffness and strength of the aircraft, while maintaining the aerodynamic shape of the aircraft, thus ensuring the aerodynamic performance of the aircraft. In the prior art, the skins of various parts of the aircraft are mostly connected by riveting to provide stable connection performance throughout the service life of the aircraft. The rivets hardly loosen after installation, which guarantees the stability and safety of the aircraft structure. However, the riveting process requires precise hole alignment and rivet installation, increasing the complexity of installation and maintenance. Especially in the tight areas of the aircraft skin, special tools and techniques may be required for riveting operations. Summary of the Utility Model

[0003] In view of this, the utility model discloses a front skin of a short nacelle of an aircraft engine, which can reduce the use of rivets and improve the installation efficiency. The specific scheme is as follows:

[0004] A front skin of a short nacelle of an aircraft engine includes a front upper wall panel, an inlet lip, and a front lower wall panel;

[0005] The front upper wall panel is located above the inlet lip and the front lower wall panel, and the inlet lip is located in front of the front lower wall panel; the front upper wall panel is a semi-conical plate-like structure as a whole, and the upper ends of the inlet lip and the front lower wall panel are both connected to the lower end of the front upper wall panel through quick-release locks; the front end of the front lower wall panel is connected to the rear end of the inlet lip.

[0006] The inlet lip includes a lip skin, a web member, and a first U-shaped frame. The web member is arranged inside the lip skin and located at the rear of the lip skin. A plate-like flange is provided on the side of the web member close to the lip skin, and the plate-like flange is connected to the lip skin; the first U-shaped frame is arranged on the web member and there is a spacing between the first U-shaped frame and the plate-like flange on the web member.

[0007] The front lower wall panel includes a lower wall skin and a second U-shaped frame. The second U-shaped frame is riveted to the front end of the lower wall skin. The front end face of the second U-shaped frame is a flat plate surface, and the width of the front end face of the second U-shaped frame is greater than the distance between the plate-like flanges. The second U-shaped frame abuts against the plate-like flanges on the web member and the first U-shaped frame.

[0008] As a supplement to the technical solution of the present utility model, it further includes an elastic sealing strip. The second U-shaped frame, the web member, the plate-shaped flange, and the first U-shaped frame enclose a U-shaped strip-shaped space with a rectangular cross-section. The elastic sealing strip is arranged in the U-shaped strip-shaped space, and the second U-shaped frame squeezes the elastic sealing strip, causing the elastic sealing strip to undergo compressive deformation to fill the U-shaped strip-shaped space.

[0009] As a supplement to the technical solution of the present utility model, the plate-shaped flange on the web member is connected to the lip skin by rivets, and the rear end of the plate-shaped flange on the web member is flush with the rear end of the lip skin.

[0010] As a supplement to the technical solution of the present utility model, the front-section upper wall plate includes an upper wall plate skin and upper wall plate reinforcing ribs. The upper wall plate reinforcing ribs are arranged inside the upper wall plate and riveted to the upper wall plate skin.

[0011] The air inlet lip further includes a first connecting backing plate. The lower part of the first connecting backing plate is located inside the lip skin and is connected to the lip skin. The upper part of the first connecting backing plate protrudes above the upper edge of the lip skin. The upper part of the first connecting backing plate is located inside the upper wall plate skin and is connected to the upper wall plate skin through a quick-release lock.

[0012] As a supplement to the technical solution of the present utility model, the front-section lower wall plate further includes a second connecting backing plate. The lower part of the second connecting backing plate is located inside the lower wall plate skin and is connected to the lower wall plate skin. The upper part of the second connecting backing plate protrudes above the upper edge of the lower wall plate skin. The upper part of the second connecting backing plate is located inside the upper wall plate skin and is connected to the upper wall plate skin through a quick-release lock.

[0013] As a supplement to the technical solution of the present utility model, the front-section lower wall plate further includes lower wall plate reinforcing ribs. The lower wall plate reinforcing ribs are arranged inside the lower wall plate skin and riveted to the lower wall plate skin. A groove is provided on the rear end face of the second U-shaped frame. The front part of the lower wall plate reinforcing rib bends upward and is placed in the groove on the rear end face of the second U-shaped frame. Rivets pass through the front part of the lower wall plate reinforcing rib, the second U-shaped frame, and the lower wall plate skin to rivet the three together.

[0014] Beneficial effects: By dividing the front-section skin of the engine nacelle into an air inlet lip, a front-section upper wall plate, and a front-section lower wall plate, the present utility model can ensure the structural strength of the front-section skin of the engine nacelle without using rigid connections between the front-section upper wall plate and the front-section lower wall plate, while ensuring the sealing performance between the air inlet lip and the front-section lower wall plate, and improving the assembly efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a three-dimensional structural schematic diagram of the front-section skin of the engine nacelle.

[0016] Figure 2 It is an exploded structural schematic diagram of the front-section skin of the engine nacelle.

[0017] Figure 3 It is a schematic diagram of the upper wall panel of the front section and the inlet lip structure.

[0018] Figure 4 It is a schematic diagram of the inlet lip structure of the engine nacelle.

[0019] Figure 5 It is Figure 4 an enlarged schematic diagram of the structure at position A in

[0020] Figure 6 It is a schematic diagram of the lower wall panel of the front section of the engine nacelle.

[0021] Figure 7 It is a schematic diagram of the lower wall panel of the front section of the engine nacelle.

[0022] Figure 8 It is a schematic diagram of the structure at the U-shaped strip space.

[0023] In the figure: 1. Upper wall panel of the front section, 2. Inlet lip, 3. Lower wall panel of the front section, 4. Lip skin, 5. Web member, 6. First U-shaped frame, 7. Plate-shaped flange, 8. Lower wall panel skin, 9. Second U-shaped frame, 10. Elastic sealing strip, 11. Upper wall panel skin, 12. Upper wall panel stiffener, 13. First connecting pad, 14. Second connecting pad, 15. Lower wall panel stiffener. Specific implementation manner

[0024] In the description of the present invention, it should be understood that the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, "a plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0025] In the present invention, unless otherwise clearly defined and limited, the terms "installed", "connected", "connected", "fixed" and other terms should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection or communication with each other; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the communication inside two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0026] Such as Figures 1 to 8As shown in the figure, the present utility model discloses a front skin of an aircraft engine nacelle, which includes a front upper wall panel 1, an inlet lip 2, and a front lower wall panel 3.

[0027] The front upper wall panel 1 is located above the inlet lip 2 and the front lower wall panel 3. The inlet lip 2 is located in the front side of the front lower wall panel 3. The front upper wall panel 1, the inlet lip 2, and the front lower wall panel 3 are connected to form the front skin of the engine nacelle with a conical structure.

[0028] The front end of the inlet lip 2 is connected to the engine by bolts. An air inlet is provided at the lower part of the inlet lip 2, which is used to effectively guide air into the engine, ensuring that the air flows in at an appropriate speed and angle to meet the operating requirements of the engine. A flange is provided at the rear end of the air inlet of the inlet lip 2, and the inlet lip 2 is connected to the engine by bolts through the flange.

[0029] The front upper wall panel 1 is integrally a semi-conical plate-like structure. The front end of the front upper wall panel 1 is connected to the front end of the inlet lip 2, and the lower end of the front upper wall panel 1 is connected to the upper end of the inlet lip 2 by a quick-release lock.

[0030] The front lower wall panel 3 is arranged below the front upper wall panel 1. The upper end of the front lower wall panel 3 is connected to the lower end of the front upper wall panel 1 by a quick-release lock.

[0031] The front end of the front lower wall panel 3 is connected to the rear end of the inlet lip 2, and the connection structure is specifically a non-rigid connection.

[0032] The inlet lip 2 includes a lip skin 4, a web member 5, and a first U-shaped frame 6. The web member 5 is riveted to the inner side of the lip skin 4 and is located at the rear part of the lip skin 4. The web member 5 is a U-shaped ribbed plate structure. A plate-like flange 7 is provided on the side of the web member 5 close to the lip skin 4, and the web member 5 is riveted to the lip skin 4 through the plate-like flange 7. The first U-shaped frame 6 is a U-shaped structure, and the first U-shaped frame 6 is arranged on the web member 5 and there is a certain distance between the first U-shaped frame 6 and the plate-like flange 7 on the web member 5.

[0033] The front lower wall panel 3 includes a lower wall skin 8 and a second U-shaped frame 9. The second U-shaped frame 9 is riveted to the front end of the lower wall skin 8. The front end face of the second U-shaped frame 9 is a flat plate surface, and the width of the front end face of the second U-shaped frame 9 is greater than the distance between the first U-shaped frame 6 and the plate-like flange 7 on the web member 5.

[0034] The second U-shaped frame 9 abuts against the plate-like flange 7 of the web member 5 and the rear end of the first U-shaped frame 6.

[0035] By dividing the skin of the front section of the engine nacelle into the inlet lip, the front upper wall panel, and the front lower wall panel, and through the connection structure between the inlet lip, the front upper wall panel, and the front lower wall panel, it is possible to avoid using a rigid connection between the inlet lip 2 and the front lower wall panel 3, reducing the overall weight of the skin.

[0036] As a supplement to the above technical solution, to improve the connection sealing performance between the front lower wall panel 3 and the inlet lip 2, an elastic sealing strip 10 is provided between the plate-shaped flange 7 on the first U-shaped frame 6 and the web member 5. As Figure 8 shown, the second U-shaped frame 9, as well as the web member 5, the plate-shaped flange 7, and the first U-shaped frame 6 on the inlet lip 2 enclose a U-shaped strip space with a rectangular cross-section. The elastic sealing strip 10 is arranged in the U-shaped strip space. After assembling the front lower wall panel 3, the front upper wall panel 1, and the inlet lip 2, the second U-shaped frame 9 provided at the front end of the front lower wall panel 3 can squeeze the elastic sealing strip 10, causing the elastic sealing strip to undergo compressive deformation and filling the U-shaped strip space, achieving the sealing effect between the front end of the front lower wall panel 3 and the rear end of the inlet lip 2.

[0037] To ensure that the plate-shaped flange 7 on the web member 5 and the rear end of the first U-shaped frame 6 can better abut against the front end of the front lower wall panel 3, the plate-shaped flange 7 and the first U-shaped frame 6 have the same width.

[0038] Through the above settings, it is realized that there is no need to rivet the front lower wall panel 3 and the inlet lip 2 during the assembly process. After the inlet lip 2 and the front lower wall panel 3 are connected to the front upper wall panel 1, the front end of the front lower wall panel 3 can abut against the rear end of the inlet lip 2. At the same time, through the settings of the first U-shaped frame 6, the web member 5, and the elastic sealing strip 10, the sealing connection effect between the two is achieved, which can improve the assembly efficiency while ensuring the sealing effect.

[0039] As a supplement to the above technical solution, the plate-shaped flange 7 on the web member 5 and the lip skin 4 can be connected by rivets, and the rear end of the plate-shaped flange 7 on the web member 5 is flush with the rear end of the lip skin 4.

[0040] As a preferred technical solution of the present invention, the front upper wall panel 1 includes an upper wall skin 11 and an upper wall reinforcing rib 12. The upper wall reinforcing rib 12 is arranged inside the upper wall and riveted to the upper wall skin 11 for supporting the upper wall skin 11. The inlet lip also includes a first connecting pad 13. The lower part of the first connecting pad 13 is located inside the lip skin 4 and connected to the lip skin 4, preferably by riveting. The upper end of the first connecting pad 13 protrudes and is higher than the upper end of the lip skin 4. The upper part of the first connecting pad 13 is located inside the upper wall skin 11 and connected to the upper wall skin 11 through a quick-release lock.

[0041] As a supplement to the above technical solution, the upper end of the first connecting backing plate 13 is provided with a bent edge, and the bent edge of the first connecting backing plate 13 is riveted to the upper wall plate reinforcing rib 12 of the front section upper wall plate 1 located above the bent edge, so as to realize the stable connection between the front section upper wall plate 1 and the inlet lip 2 through the above setting.

[0042] As a preferred technical solution of the present invention, the front section lower wall plate 3 further includes a second connecting backing plate 14. The lower part of the second connecting backing plate 14 is located inside the lower wall plate skin 8 and is connected to the lower wall plate skin 8. The upper end of the second connecting backing plate 14 is higher than the upper end of the lower wall plate skin 8. The upper part of the second connecting backing plate 14 is located inside the upper wall plate skin 11 and is connected to the upper wall plate skin 11 through a quick-release lock.

[0043] As a supplement to the above technical solution, the upper end of the second connecting backing plate 14 is provided with a bent edge, and the bent edge of the second connecting backing plate 14 is riveted to the upper wall plate reinforcing rib 12 located above the bent edge, so as to realize the stable connection between the front section lower wall plate 3 and the front section upper wall plate 1 through the above setting.

[0044] As a supplement to the technical solution of the present invention, the front section lower wall plate 3 further includes a lower wall plate reinforcing rib 15. The lower wall plate reinforcing rib 15 is arranged inside the lower wall plate skin 8 and is riveted to the lower wall plate skin 8. A groove is provided on the rear end face of the second U-shaped frame 9. The front part of the lower wall plate reinforcing rib 15 is bent upward and placed in the groove on the rear end face of the second U-shaped frame 9. A rivet passes through the front part of the lower wall plate reinforcing rib 15, the second U-shaped frame 9, and the lower wall plate skin 8 to rivet the lower wall plate reinforcing rib 15, the second U-shaped frame 9, and the lower wall plate skin 8.

[0045] As a supplement to the technical solution of the present invention, the inlet lip 2 further includes a conical plate connecting piece. The conical plate connecting piece is arranged at the front end of the lip skin 4. The inlet lip 2 is bolted to the engine through the conical plate connecting piece, and the front end of the front end upper wall plate is screwed to the conical plate connecting piece to achieve the purpose of connecting the front end upper wall plate and the front end of the inlet lip 2.

[0046] The above is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and the inventive concept of the present invention, makes equivalent substitutions or changes, and should be covered by the protection scope of the present invention.

Claims

1. A front section skin of an aircraft engine nacelle, characterized in that: It comprises a front upper wall plate (1), an air inlet lip (2), and a front lower wall plate (3); The front upper wall plate (1) is located above the air inlet lip (2) and the front lower wall plate (3), and the air inlet lip (2) is located on the front side of the front lower wall plate (3); the upper ends of the air inlet lip (2) and the front lower wall plate (3) are connected to the lower end of the front upper wall plate (1) through a quick release lock; the front end of the front lower wall plate (3) is connected to the rear end of the air inlet lip (2), The air inlet lip (2) comprises a lip skin (4), a web member (5), and a first U-shaped frame (6); the web member (5) is arranged on the inner side of the lip skin (4) and located at the rear of the lip skin (4); a plate-shaped flange (7) is provided on the side of the web member (5) close to the lip skin (4); the plate-shaped flange (7) is connected to the lip skin (4) by a quick release lock; the first U-shaped frame (6) is arranged on the web member (5) and there is a gap between the web member (5) and the plate-shaped flange (7) on the web member (5); The front section lower wall panel (3) comprises a lower wall panel skin (8) and a second U-shaped frame (9). The second U-shaped frame (9) is riveted to the front end of the lower wall panel skin (8). The front end surface of the second U-shaped frame (9) is a flat surface, and the width of the front end surface of the second U-shaped frame (9) is greater than the distance between the first U-shaped frame (6) and the plate-shaped flange (7). The second U-shaped frame (9) abuts against the plate-shaped flange (7) on the web member (5) and the first U-shaped frame (6).

2. The aircraft engine nacelle front skin according to claim 1, characterized in that: The invention also comprises an elastic sealing strip (10), a second U-shaped frame (9), a web member (5), a plate-shaped flange (7), and a first U-shaped frame (6) which together enclose a U-shaped strip-shaped space with a rectangular cross-section, wherein the elastic sealing strip (10) is arranged in the U-shaped strip-shaped space, and the second U-shaped frame (9) presses the elastic sealing strip (10) to cause the elastic sealing strip to be compressed and deformed, thereby filling the U-shaped strip-shaped space.

3. The aircraft engine nacelle front skin according to claim 1, characterized in that: The rear end of the plate-shaped flange (7) on the web member (5) is flush with the rear end of the lip skin (4).

4. The aircraft engine nacelle front skin according to claim 1, characterized in that: The front section upper wall panel (1) comprises an upper wall panel skin (11) and an upper wall panel reinforcement rib (12), wherein the upper wall panel reinforcement rib (12) is arranged on the inner side of the upper wall panel skin (11) and is riveted to the upper wall panel skin (11); The air inlet lip also includes a first connecting pad (13), the lower part of the first connecting pad (13) is located on the inner side of the lip skin (4) and is connected to the lip skin (4), the upper part of the first connecting pad (13) protrudes from the upper edge of the lip skin (4) and is located on the inner side of the upper wall panel skin (11), and the upper part of the first connecting pad (13) is connected to the upper wall panel skin (11) via a quick release lock.

5. The aircraft engine nacelle front skin according to claim 1, characterized in that: The front lower wall panel (3) also includes a second connecting pad (14), the lower part of which is located on the inner side of the lower wall panel skin (8) and connected to the lower wall panel skin (8), the upper part of which protrudes from the upper edge of the lower wall panel skin (8) and is located on the inner side of the upper wall panel skin (11), and the second connecting pad is connected to the upper wall panel skin (11) via a quick-release lock.

6. The aircraft engine nacelle front skin according to claim 1, characterized in that: The front section lower wall panel (3) also includes a lower wall panel reinforcement rib (15), which is arranged on the inner side of the lower wall panel skin (8) and riveted to the lower wall panel skin (8), and a groove is provided on the rear end surface of the second U-shaped frame (9), and the front part of the lower wall panel reinforcement rib (15) is bent upward and placed in the groove on the rear end surface of the second U-shaped frame (9), and the rivet passes through the front part of the lower wall panel reinforcement rib (15), the second U-shaped frame (9), and the lower wall panel skin (8) to rivet the three together.

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