Aircraft engine firewall

Abstract

An aircraft engine firewall comprises a front firewall body, a rear firewall body and an upper firewall body. A first through hole is formed in the front firewall, and a second through hole is formed in the rear firewall; the upper firewall is arranged between the front firewall and the rear firewall; the front fireproof wall comprises an upper fireproof plate, a lower fireproof plate, a side reinforcing rib, a first arc-shaped reinforcing rib and a second arc-shaped reinforcing rib, and the side reinforcing rib is arranged on the plate surface of the upper fireproof plate; the first arc-shaped reinforcing rib is arranged at the circumferential position of the semicircular notch in the lower part of the upper fireproof plate; the second arc-shaped reinforcing rib is arranged at the circumferential position of the semicircular notch in the upper part of the lower fireproof plate; a protruding part is arranged at the lower end of the upper fireproof plate, the protruding part is of a plate-shaped structure extending downwards at the position of the lower end of the upper fireproof plate, the protruding part of the upper fireproof plate is located on the rear side of the lower fireproof plate, and the protruding part of the upper fireproof plate is connected with the lower fireproof plate.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft manufacturing, and relates to an aircraft engine firewall. Background Art

[0002] The aircraft engine firewall is a key safety component in aircraft design. Its main function is to prevent the spread of fire outside the engine compartment in case of abnormal situations in the engine, such as fire, explosion, etc., to ensure the safety of the aircraft. Traditional aircraft engine firewalls usually consist of multiple layers of heat-insulating materials and structural support members. These materials and members need to withstand extreme temperatures and pressures while maintaining their integrity and functionality.

[0003] Although the existing firewalls can meet the basic fire prevention requirements, their structural strength still needs to be improved when facing the impact force and heat load in extreme situations. Summary of the Utility Model

[0004] In view of this, the utility model is disclosed, and the specific scheme is as follows:

[0005] An aircraft engine firewall includes a front firewall, a rear firewall, and an upper firewall;

[0006] The front firewall and the rear firewall are arranged relatively parallel. The front firewall is provided with a first through hole, and the rear firewall is provided with a second through hole; the upper firewall is arranged between the front firewall and the rear firewall. The front end of the upper firewall is connected to the front firewall, and the rear end is connected to the rear firewall, and the upper firewall is located above the first through hole and the second through hole;

[0007] The front firewall includes an upper fireproof board, a lower fireproof board, side strengthening ribs, a first arc-shaped strengthening rib, and a second arc-shaped strengthening rib. A semi-circular notch is provided at the lower part of the upper fireproof board, and a semi-circular notch is provided at the upper part of the lower fireproof board. The semi-circular notch on the upper fireproof board and the semi-circular notch on the lower fireproof board form the first through hole,

[0008] The side strengthening ribs are arranged on the board surface of the upper fireproof board. There are two groups of side strengthening ribs. The first side strengthening rib is arranged on the left part of the upper fireproof board, and the second side strengthening rib is arranged on the right part of the upper fireproof board; the first arc-shaped strengthening rib is arranged at the circumferential position of the lower semi-circular notch of the upper fireproof board, and the second arc-shaped strengthening rib is arranged at the circumferential position of the upper semi-circular notch of the lower fireproof board; a convex part is provided at the lower end of the upper fireproof board. The convex part is a plate-like structure extending downward at the lower end position of the upper fireproof board. The convex part of the upper fireproof board is located at the rear side of the lower fireproof board, and the convex part of the upper fireproof board is connected to the lower fireproof board.

[0009] As a supplement to the technical solution of the present utility model, it further includes a strengthening connecting rod. The front end of the strengthening connecting rod is connected to the front firewall, and the rear end of the strengthening connecting rod is connected to the rear firewall. There are two groups of the strengthening connecting rods in total. The position where the first strengthening connecting rod is connected to the front firewall is on the left side of the first through hole, and the position where the first strengthening connecting rod is connected to the rear firewall is on the left side of the second through hole;

[0010] The position where the second strengthening connecting rod is connected to the front firewall is on the right side of the first through hole, and the position where the second strengthening connecting rod is connected to the rear firewall is on the right side of the second through hole.

[0011] As a supplement to the technical solution of the present utility model, it further includes a first joint, a second joint, and a strengthening beam. The first joint is arranged on the front firewall and is screwed to the upper firewall plate and the side strengthening ribs. The front end of the strengthening connecting rod is connected to the first joint. On one side of the first joint close to the center of the first through hole, there is a threaded hole for screwing with the engine;

[0012] The second joint is arranged on the rear firewall. The rear end of the strengthening connecting rod is connected to the second joint. A strengthening beam is connected between the two second joints arranged at the rear ends of the first strengthening connecting rod and the second strengthening connecting rod, and the strengthening beam is connected to the rear firewall.

[0013] As a supplement to the technical solution of the present utility model, the front end of the strengthening connecting rod is hinged to the first joint, and the rear end of the strengthening connecting rod is hinged to the second joint.

[0014] As a supplement to the technical solution of the present utility model, the upper firewall includes an upper firewall plate, a corner beam, and a U-shaped beam.

[0015] The corner beam is a long beam with an L-shaped cross-section composed of two mutually perpendicular plate surfaces. The horizontal plate surface of the corner beam is riveted to the upper firewall plate, and the vertical plate surface of the corner beam is connected to the front firewall;

[0016] The U-shaped beam has a U-shaped cross-section structure, which includes a top plate surface, a bottom plate surface, and a web. The top plate surface and the bottom plate surface are connected by a vertically arranged web; the bottom plate surface of the U-shaped beam is connected to the upper firewall plate, and the web is connected to the rear firewall.

[0017] As a supplement to the technical solution of the present utility model, the upper firewall further includes an engine rear suspension point installation box. There is a vertically opened through hole on the upper firewall plate. The lower bottom surface of the engine rear suspension point installation box has a groove. The engine rear suspension point installation box is located above the through hole on the upper firewall plate, and the lower end of the engine rear suspension point installation box is connected to the upper firewall plate. The through hole on the upper firewall plate is communicated with the inner space of the groove of the engine rear suspension point installation box.

[0018] As a supplement to the technical solution of the present utility model, it further includes an adapter plate. The adapter plate is vertically arranged on the upper firewall plate. The lower end of the adapter plate is connected to the upper firewall plate, and the front end is connected to the front firewall.

[0019] As a supplement to the technical solution of the present utility model, flanges are provided at the side edges of the front firewall, the left and right ends of the upper firewall plate, and the side edges of the rear firewall for connecting with the skin.

[0020] As a supplement to the technical solution of the present utility model, it further includes load-bearing support plates. There are two groups of load-bearing support plates. The first load-bearing support plate is vertically arranged on the left side of the engine rear suspension point mounting box, and the first load-bearing support plate is vertically arranged on the right side of the engine rear suspension point mounting box.

[0021] Beneficial effects: Through the structural design of the aircraft engine firewall system, the present utility model improves the structural strength. Through the structural design of the front firewall, while ensuring the structural strength, its weight is reduced. Through the settings of the first joint and the second joint, connecting the front firewall plate, the side reinforcing rib, the engine, and the reinforcing connecting rod at the same time, it can play a role in transmitting multi-party loads and ensure the structural stability. Description of the Drawings

[0022] Figure 1 It is a three-dimensional structural schematic diagram of the present utility model.

[0023] Figure 2 It is a three-dimensional structural schematic diagram of the present utility model.

[0024] Figure 3 It is a structural schematic diagram of the front firewall of the present utility model.

[0025] Figure 4 It is a structural schematic diagram of the upper firewall of the present utility model.

[0026] Figure 5 It is a three-dimensional structural schematic diagram of the present utility model.

[0027] In the figure: 1. Front firewall, 2. Rear firewall, 3. Upper firewall, 4. First through hole, 5. Second through hole, 6. Upper firewall plate, 7. Lower firewall plate, 8. Side reinforcing rib, 9. First arc-shaped reinforcing rib, 10. Second arc-shaped reinforcing rib, 11. Protrusion, 12. Reinforcing connecting rod, 13. First joint, 14. Second joint, 15. Reinforcing beam, 16. Upper firewall plate, 17. Corner beam, 18. U-shaped beam, 19. Engine rear suspension point mounting box, 20. Adapter plate, 21. Load-bearing support plate. Detailed Embodiments

[0028] In the description of the present utility model, it should be understood that the terms "first" and "second" are only used for descriptive purposes and cannot be construed 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 such feature. In the description of the present utility model, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0029] In the present utility model, unless otherwise clearly specified and defined, the terms "installed", "connected", "connected to", "fixed", etc. 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 capable of communicating with each other; it may be directly connected, or indirectly connected through an intermediate medium, and may be the communication inside two elements or the interaction relationship between two elements, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0030] As Figures 1 to 5 shown, an aircraft engine firewall includes a front firewall 1, a rear firewall 2, and an upper firewall 3.

[0031] The front firewall 1 and the rear firewall 2 are arranged relatively parallel, and the front firewall 1 is provided with a first through hole 4 for the engine to pass through, and the rear firewall 2 is provided with a second through hole 5 for the engine exhaust duct to pass through.

[0032] The upper firewall 3 is horizontally arranged between the front firewall 1 and the rear firewall 2. The front end of the upper firewall 3 is connected to the front firewall 1, the rear end is connected to the rear firewall 2, and the upper firewall 3 is located above the first through hole 4 and the second through hole 5.

[0033] Through the above arrangement, the fire area is divided into three parts. The first fire area is located on the front side of the front firewall 1, the second fire area is located within the area surrounded by the front firewall 1, the upper firewall 3, and the rear firewall 2, and the third fire area is located on the rear side of the rear firewall 2, realizing the separation of the three fire areas. When a hidden danger occurs in the engine and catches fire, it can effectively prevent the spread of the fire.

[0034] The front firewall 1 includes an upper fireproof board 6 and a lower fireproof board 7. Semi-circular notches are provided at the lower part of the upper fireproof board 6 and the upper part of the lower fireproof board. The lower end of the upper fireproof board 6 is connected to the upper end of the lower fireproof board 7, and the semi-circular notches on the upper fireproof board 6 and the lower fireproof board 7 enclose the first through hole 4.

[0035] Specifically, a convex portion 11 is provided at the lower end of the upper fireproof board 6. The convex portion 11 is a plate-like structure extending downward at the lower end position of the upper fireproof board 6. The convex portion 11 of the upper fireproof board 6 is located at the rear side of the lower fireproof board 7, and the convex portion 11 of the upper fireproof board 6 is connected to the lower fireproof board 7. The connection method can be selected as riveting or screwing. When installing the engine, first connect the upper fireproof board 6 to the engine, and then connect the lower fireproof board 7 to the engine and the upper fireproof board 6. When disassembling the engine, the lower fireproof board 7 can be disassembled together with the engine.

[0036] To ensure the structural strength of the upper fireproof board 6, the front fireproof board further includes side reinforcing ribs 8, a first arc-shaped reinforcing rib 9, and a second arc-shaped reinforcing rib 10.

[0037] The side reinforcing ribs 8 are arranged on the plate surface of the upper fireproof board 6. There are two groups of side reinforcing ribs 8. The first side reinforcing rib is arranged on the left part of the upper fireproof board 6, and the second side reinforcing rib is arranged on the right part of the upper fireproof board 6. The side reinforcing ribs 8 are provided with flanges, and the flanges are used to connect with the skin. By arranging the side reinforcing ribs 8, the structural strength of the left and right ends of the upper fireproof board 6 is enhanced.

[0038] The first arc-shaped reinforcing rib 9 is an arc-shaped structure, which is fitted at the circumferential position of the lower semi-circular notch of the upper fireproof board 6 for strengthening the semi-circular notch position of the upper fireproof board 6. The first arc-shaped reinforcing rib 9 and the upper fireproof board 6 can be connected by riveting. The second arc-shaped reinforcing rib 10 is an arc-shaped structure, which is fitted at the circumferential position of the upper semi-circular notch of the lower fireproof board 7 for strengthening the semi-circular notch position of the lower fireproof board 7. The first arc-shaped reinforcing rib 9 and the upper fireproof board 6 can be connected by riveting, and the second arc-shaped reinforcing rib 10 and the lower fireproof board 7 can be connected by riveting.

[0039] The front firewall 1 further includes connecting pieces, which are respectively arranged on the first arc-shaped beam and the second arc-shaped beam and are used to connect with the flange on the engine. To improve the connection strength between the front firewall 1 and the engine, several groups of connecting pieces are provided and are evenly arranged in an array along the circumference of the first through hole 4 on the outer periphery of the first through hole 4.

[0040] As a preferred technical solution of the present invention, it further includes a strengthening connecting rod 12. The front end of the strengthening connecting rod 12 is connected to the front firewall 1, and the rear end of the strengthening connecting rod 12 is connected to the rear firewall 2. There are two groups of strengthening connecting rods 12 in total. The position where the first strengthening connecting rod is connected to the front firewall 1 is located on the left side of the first through hole 4, and the position where the first strengthening connecting rod is connected to the rear firewall 2 is located on the left side of the second through hole 5;

[0041] The position where the second reinforcing link is connected to the front firewall 1 is on the right side of the first through hole 4, and the position where the second reinforcing link is connected to the rear firewall 2 is on the right side of the second through hole 5. The stability of the overall structure is improved by the arrangement of the reinforcing link 12.

[0042] As a supplement to the above technical solution, the front end of the reinforcing link 12 is connected to the front firewall 1 through the first joint 13. Specifically, the first joint 13 is a plate-like structure, and the first joint 13 is screwed to the upper firewall plate 6 and the side reinforcing rib 8. Through the arrangement of the first joint 13, the connection strength between the upper firewall plate and the side reinforcing rib 8 is improved. One side of the center of the first through hole 4 of the first joint 13 is connected to the flange on the engine.

[0043] The above-mentioned first joint 13 is simultaneously connected to the front firewall, the side reinforcing rib 8, the engine, and the first reinforcing link, and can play a role in conducting multi-party loads to ensure the structural stability.

[0044] To avoid the shear force on the rear firewall 2 caused by the different directions of the bearing forces of the two reinforcing links 12. For example, the first group of reinforcing links 12 exerts a pulling force towards the front side on the rear firewall 2, and the second group of reinforcing links 12 exerts a pulling force towards the rear side on the rear firewall 2, affecting the stability of the rear firewall 2. As a preferred technical solution of the present invention, the rear end of the reinforcing link 12 is connected to the rear firewall 2 through the second joint 14. A reinforcing beam 15 is provided between the second joints 14 at the rear ends of the two reinforcing links 12, and the reinforcing beam (15) is arranged on the rear firewall 2. Through the arrangement of the reinforcing beam 15, the forces exerted on the rear firewall 2 by the two groups of reinforcing links 12 can be conducted through the reinforcing beam 15.

[0045] As a preferred technical solution of the present invention, the front end of the reinforcing link 12 is hinged to the first joint 13, and the rear end of the reinforcing link 12 is hinged to the second joint 14. Hinging can make the reinforcing link 12 stable when subjected to external forces, and the hinge points can absorb and disperse part of the impact force, reducing the impact on the overall structure.

[0046] As a preferred technical solution of the present invention, the upper firewall 3 includes an upper firewall plate 16, an angle beam 17, and a U-shaped beam 18.

[0047] Both the left and right ends of the upper firewall plate 16 are provided with flanges for connecting to the skin.

[0048] The angle beam 17 is used to connect the upper firewall plate 16 to the front firewall 1. The angle beam 17 is an L-shaped long beam with a cross-section composed of two mutually perpendicular plate surfaces. The horizontal plate surface of the angle beam 17 is riveted to the upper firewall plate 16, and the vertical plate surface of the angle beam 17 is connected to the front firewall 1. The front end of the upper firewall plate 16 is connected to the front firewall 1 through the angle beam 17.

[0049] The cross-section of the U-shaped beam 18 is a U-shaped structure, which includes a top plate surface, a bottom plate surface, and a web. The top plate surface and the bottom plate surface are connected by a vertically arranged web. The bottom plate surface of the U-shaped beam 18 is connected to the upper firewall 3, and the web is connected to the rear firewall 2. Its top plate surface is used to connect to the wing of the aircraft to enhance the connection strength between the firewall and the wing.

[0050] As a preferred technical solution of the present invention, the upper firewall 3 further includes an engine rear suspension point mounting box 19. A vertically opened through hole is provided on the upper firewall plate 16. A groove is provided on the lower bottom surface of the engine rear suspension point mounting box 19. The engine rear suspension point mounting box 19 is located above the through hole on the upper firewall plate 16, and the lower end of the engine rear suspension point mounting box 19 is connected to the upper firewall plate 16. The position where the engine rear suspension point mounting box 19 is connected to the upper firewall plate 16 is located on the outer periphery of the through hole on the upper firewall plate 16, so that the through hole on the upper firewall plate 16 is communicated with the inner space of the groove of the engine rear suspension point mounting box 19. The rear suspension point of the engine is connected to the engine rear suspension point mounting box 19 through a transfer member. One end of the transfer member is connected to the rear suspension point of the engine, and the other end passes through the through hole on the upper firewall plate 16 and is connected to the engine rear suspension point mounting box 19. The upper end of the engine rear suspension point mounting box 19 is used to connect to the wing.

[0051] In the above structure, through the setting of the engine rear suspension point mounting box 19, the isolation between the second fire area and the wing is realized. At the same time, through the design of the engine rear suspension point mounting box 19, the connection between the engine and the wing is realized, reducing the load borne by the upper firewall plate 16 and enhancing the structural stability of the upper firewall plate 16.

[0052] As a preferred technical solution of the present invention, it further includes a transfer plate 20. The transfer plate 20 is vertically arranged on the upper firewall plate 16. The lower end of the transfer plate 20 is connected to the upper firewall plate 16, and the front end is connected to the front firewall 1. The upper end of the transfer plate 20 is used to connect to the wing and is used to support the wing.

[0053] As a preferred technical solution of the present invention, flanges are provided at the side edges of the side strengthening ribs 8 on the front firewall 1, at the left and right ends of the upper firewall plate 16, and at the side edges of the rear firewall 2 for connecting to the outer skin.

[0054] As a preferred technical solution of the present invention, it further includes two sets of load-bearing support plates 21. The first load-bearing support plate is vertically arranged on the left side of the engine rear suspension point mounting box 19, and the first load-bearing support plate is vertically arranged on the right side of the engine rear suspension point mounting box 19. A flange is provided at the upper end of the load-bearing support plate 21 for connecting to the wing and bearing the wing.

[0055] The above are only the preferred specific embodiments 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 inventive concept of the present invention, making equivalent substitutions or changes should be covered within the protection scope of the present invention.

Claims

1. An aircraft engine firewall, characterized in that: It includes a front firewall (1), a rear firewall (2), and an upper firewall (3); The front firewall (1) and the rear firewall (2) are arranged relatively parallel, the front firewall (1) is provided with a first through hole (4), and the rear firewall (2) is provided with a second through hole (5); the front end of the upper firewall (3) is connected to the front firewall (1), and the rear end is connected to the rear firewall (2), and the upper firewall (3) is located above the first through hole (4) and the second through hole (5); The front fire wall (1) comprises an upper fireproof plate (6), a lower fireproof plate (7), a side reinforcing rib (8), a first arc-shaped reinforcing rib (9), and a second arc-shaped reinforcing rib (10); the upper fireproof plate (6) is located above the lower fireproof plate (7); a semicircular notch is provided at the lower part of the upper fireproof plate (6); a semicircular notch is provided at the upper part of the lower fireproof plate (7); the semicircular notch on the upper fireproof plate (6) and the semicircular notch on the lower fireproof plate (7) form a first through hole (4); The side reinforcing ribs (8) are arranged on the plate surface of the upper fireproof plate (6), and the side reinforcing ribs (8) are provided with two groups, the first side reinforcing ribs are arranged on the left part of the upper fireproof plate (6), and the second side reinforcing ribs are arranged on the right part of the upper fireproof plate (6); the first arc-shaped reinforcing ribs (9) are arranged at the circumferential position of the lower semicircular notch of the upper fireproof plate (6), and the second arc-shaped reinforcing ribs (10) are arranged at the circumferential position of the upper semicircular notch of the lower fireproof plate (7); the lower end of the upper fireproof plate (6) is provided with a protrusion (11), and the protrusion (11) is a plate-like structure extending downward at the lower end position of the upper fireproof plate (6), and the protrusion (11) of the upper fireproof plate (6) is located on the rear side of the lower fireproof plate (7), and the protrusion (11) of the upper fireproof plate (6) is connected to the lower fireproof plate (7).

2. An aircraft engine firewall according to claim 1, characterized in that: It also includes a reinforcing link (12), the front end of the reinforcing link (12) being connected to the front firewall (1), and the rear end of the reinforcing link (12) being connected to the rear firewall (2), and the reinforcing link (12) being provided with two groups in total, the position where the first reinforcing link is connected to the front firewall (1) being located on the left side of the first through hole (4), and the position where the first reinforcing link is connected to the rear firewall (2) being located on the left side of the second through hole (5); The position where the second reinforcing connecting rod is connected to the front firewall (1) is located on the right side of the first through hole (4), and the position where the second reinforcing connecting rod is connected to the rear firewall (2) is located on the right side of the second through hole (5).

3. An aircraft engine firewall according to claim 2, characterized in that: It also includes a first joint (13), a second joint (14), and a reinforcing beam (15), wherein the first joint (13) is arranged on the front fire wall (1) and is screwed to the upper fireproof plate (6) and the side reinforcing rib (8), the front end of the reinforcing connecting rod (12) is connected to the first joint (13), and a threaded hole is arranged on one side of the first joint (13) close to the center of the first through hole (4); The second joint (14) is arranged on the rear firewall (2), the rear end of the reinforcing link (12) is connected to the second joint (14), a reinforcing beam (15) is connected between the two second joints (14) arranged at the rear ends of the first reinforcing link and the second reinforcing link, and the reinforcing beam (15) is connected to the rear firewall (2).

4. An aircraft engine firewall according to claim 3, characterized in that: The front end of the reinforcing connecting rod (12) is hinged to the first joint (13), and the rear end of the reinforcing connecting rod (12) is hinged to the second joint (14).

5. The aircraft engine firewall according to claim 1, characterized in that: The upper firewall (3) comprises an upper firewall plate (16), an angle beam (17), and a U-shaped beam (18); The angle beam (17) is a long beam with an L-shaped cross section composed of two mutually perpendicular plate surfaces, the horizontal plate surface of the angle beam (17) is riveted to the upper firewall plate (16), and the vertical plate surface of the angle beam (17) is connected to the front firewall (1); The cross section of the U-shaped beam (18) is a U-shaped structure, which includes a top plate surface, a bottom plate surface, and a web plate, wherein the top plate surface and the bottom plate surface are connected via a vertically arranged web plate; the bottom plate surface of the U-shaped beam (18) is connected to the upper firewall plate (16), and the web plate is connected to the rear firewall (2).

6. An aircraft engine firewall according to claim 5, characterized in that: The upper firewall (3) also includes an engine rear suspension point installation box (19), the upper firewall plate (16) is provided with a through hole opened vertically, the lower bottom surface of the engine rear suspension point installation box (19) is provided with a groove, the engine rear suspension point installation box (19) is located above the through hole on the upper firewall plate (16), and the lower end of the engine rear suspension point installation box (19) is connected to the upper firewall plate (16), and the through hole on the upper firewall plate (16) is connected to the space in the groove of the engine rear suspension point installation box (19).

7. An aircraft engine firewall according to claim 6, characterized in that: It also includes an adapter plate (20), which is vertically arranged on the upper fire wall plate (16), the lower end of the adapter plate (20) is connected to the upper fire wall plate (16), and the front end is connected to the front fire wall (1).

8. The aircraft engine firewall according to claim 5, characterized in that: The side edges of the front firewall (1), the left and right ends of the upper firewall plate (16), and the side edges of the rear firewall (2) are all provided with curved edges.

9. The aircraft engine firewall according to claim 5, characterized in that: It also includes a bearing support plate (21), wherein the bearing support plate (21) is provided in two groups, a first bearing support plate is vertically arranged on the left side of the engine rear suspension point installation box (19), and a second bearing support plate is vertically arranged on the right side of the engine rear suspension point installation box (19).

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