JPH11336611A - Auxiliary equipment mounting structure to jet engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To follow thermal expansion in an axial direction and in a peripheral direction of an auxiliary machinery mounting surface, to surely support great load at acceleration, and to reduce a transmission of vibration in the axial direction and in a radial direction without using a vibration isolating rubber of short lifetime. SOLUTION: This mounting structure comprises a plurality of support members 12 which extend along an auxiliary machinery mounting surface 1a of a jet engine and to which an auxiliary machinery 7 is mounted, and flanges 14 for fixing both ends of the support member 12 to the auxiliary machinery mounting surface 1a. The support members 12 have elasticity following thermal expansion in an axial direction X and in a peripheral direction Y of an auxiliary machinery mounting surface 1a.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a structure for attaching auxiliary equipment to a jet engine.

[0002]

2. Description of the Related Art FIG. 6 is a schematic view of a jet engine. As shown in FIG. 1, the jet engine 1 includes a fan 2 for taking in air, a compressor 3 for compressing the taken-in air, a combustor 4 for burning fuel with the compressed air,
The fuel cell system includes a turbine 5 for driving the fan 2 and the compressor 3 with the combustion gas from the combustor 4, an afterburner 6 for re-injecting the fuel and re-burning the fuel.

Further, on the outer peripheral portion of the jet engine, auxiliary devices (hereinafter, simply referred to as auxiliary devices) such as an electronic control device and a hydraulic control device for controlling the jet engine are attached to, for example, a bypass duct 1a.

FIG. 7 is a schematic view showing a conventional accessory mounting structure for a jet engine. As shown in this figure, conventionally, the auxiliary equipment 7 is connected to the bypass duct 1a by the (A) pin + connecting rod method or (B) bracket + vibration isolation rubber method.
And so on.

[0005]

The bypass duct 1a of the jet engine is operated at 150.degree.
It is heated to around 00 ° C, so that the bypass duct 1a
Thermally expands in the circumferential direction and in the axial direction as compared with when the motor is stopped. In addition, a large acceleration of up to about 20 G acts in the axial direction on the auxiliary machine 7 of the jet engine during the flight of the aircraft, and also vibrates in the axial and radial directions.

[0006] Therefore, the accessory mounting structure to the jet engine must cope with the thermal expansion of the bypass duct 1a, large acceleration in the axial direction, and vibration in the axial and radial directions. In the conventional (A) pin + connecting rod system shown in FIG. 7, the auxiliary device 7 is attached with three pin joints 8a and one connecting rod 8b. However, in this method, it is possible to follow the thermal expansion in the axial direction (right and left in the figure) of the bypass duct 1a, but it is difficult to follow the thermal expansion in the circumferential direction (perpendicular to the paper surface). There is a problem that the vibration in the radial direction is transmitted to the auxiliary machine as it is. Therefore, in order to absorb the thermal expansion in the circumferential direction,
If a gap (play) is provided in the circumferential direction in the pin joint 8a or the connecting rod 8b, there is a problem that the portion is easily damaged by vibration. Further, when a vibration isolating rubber is used for the mounting portion to absorb thermal expansion and vibration, there is a problem that the life is extremely short due to a large load and heating during acceleration. That is, conventionally, three points are restricted, but one point is completely fixed, and the other two points have a pin structure with a gap to escape thermal deformation of the bypass duct, so that appropriate rigidity cannot be given. Also, it was weak against vibration.

[0007] On the other hand, in the case of the bracket + anti-vibration rubber system shown in Fig. 7B, since the auxiliary equipment is mounted on the bypass duct 1a via the bracket 9a, it is necessary to reinforce the bracket mounting part of the auxiliary equipment and the structure is complicated. There is a problem that the weight increases. Further, since the vibration isolating rubber 9b is used for the mounting portion in order to absorb thermal expansion and vibration, there is a problem that the life of the vibration isolating rubber 9b is short due to a large load and heating during acceleration.

The present invention has been made to solve such a problem. That is, the object of the present invention is to be able to follow the thermal expansion in the axial and circumferential directions of the accessory mounting surface without using a vibration-proof rubber having a short life, to reliably support a large load during acceleration, and Another object of the present invention is to provide an accessory mounting structure for a jet engine which can reduce vibration transmission in a radial direction.

[0009]

According to the present invention, there are provided a plurality of support members (12) extending along an accessory mounting surface (1a) of a jet engine to which an auxiliary device (7) is mounted, and the support member. Flanges (1) that fix both ends of the
4), wherein the support member has elasticity to follow thermal expansion in the axial direction and the circumferential direction of the accessory mounting surface, and the accessory mounting structure for a jet engine is provided. According to a preferred embodiment of the present invention, a pair of support members crossing each other in an X-shape at a central portion is provided.

According to the configuration of the present invention, the support member (1)
2) is a flexible structure that follows thermal expansion, so that it is possible to escape thermal deformation in the axial and circumferential directions of the accessory mounting surface (for example, a bypass duct). In addition, vibration can be effectively reduced by the elasticity of the support member. In addition, since it is an integrated structure that does not use anti-vibration rubber and has no gaps, it can have appropriate support rigidity, has a structure that is strong against vibration, and can stably handle large loads during acceleration for a long time. Can be supported.

Further, according to the present invention, there are provided a plurality of attachment members (16) which are sandwiched between the accessory attachment surface (1a) of the jet engine and the accessory (7) and are attached to the respective accessories. Has a flexure portion (16a) that follows the thermal expansion of the accessory mounting surface in the axial and circumferential directions, and a damping portion (16b) that absorbs vibration by friction. A machine mounting structure is provided. According to a preferred embodiment of the present invention, the mounting member (16) is a metal flat plate which is entirely curved in a U-shape, and has curved portions (17a) bulging inward at both ends,
Vibration is absorbed by friction between the curved portion, the accessory mounting surface (1a), and the accessory (7). According to another embodiment, said mounting member (16) is an annular member, said annular member having mutually urged cutting surfaces (17b).

According to the configuration of the present invention, the accessory mounting surface (1a) and the accessory (7) are directly connected via the plurality of mounting members (16). Large load can be reliably supported, and simplification of the structure and weight reduction can be expected. In addition, since the mounting member has the bent portion (16a) that follows the thermal expansion, the elastic deformation of this portion makes it possible to follow the axial and circumferential thermal expansion of the accessory mounting surface. Further, since the mounting member has the damping portion (16b), vibration transmitted by friction at this portion can be reduced.

[0013]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Preferred embodiments of the present invention will be described below with reference to the drawings. In the drawings, common portions are denoted by the same reference numerals, and redundant description is omitted. FIG. 1 is a view showing a structure for attaching auxiliary equipment to a jet engine according to the present invention. In this figure, (A) is a side view,
(B) is a view on arrow A, and (C) is a view on arrow BB. The structure of the present invention includes a plurality of (two in this example) support members 12 and flanges 14 as shown in the drawing. In this example, the two support members 12 intersect each other in an X-shape at the center, and extend along the accessory mounting surface 1a (for example, a bypass duct) of the jet engine. The intersections are joined by welding or the like and are integrated with each other. Further, a through hole is provided in the middle of the support member 12, and an auxiliary machine 7 such as an electronic control unit or a hydraulic control unit is fixed by a bolt 13 passing therethrough. Further, both ends of each support member 12 are welded to a flange 14, and the flange 14 is fixed to the accessory mounting surface 1a with bolts 13. The support member 12 is a rod-shaped member having a circular or flat cross section, and is formed so as to follow the thermal expansion in the axial direction X and the circumferential direction Y of the accessory mounting surface 1a within an elastic range.

According to the configuration of the present invention described above, since the support member 12 has a flexible structure capable of following the thermal expansion in the elastic range, the support member mounting surface 1a (for example, the bypass duct) has the axial direction X and the circumferential direction. The thermal deformation of Y can be escaped. Further, the elasticity of the support member 12 can effectively reduce the vibration. In addition, since it is an integrated structure that does not use anti-vibration rubber and has no gaps, it can have appropriate support rigidity, has a structure that is strong against vibration, and can stably handle large loads during acceleration for a long time. Can be supported.

FIG. 2 is a view showing another structure for attaching auxiliary equipment to a jet engine according to the present invention. In this figure, (A)
Is a partial sectional view in the axial direction, (B) is a view taken in the direction of arrow BB, and (C) is an enlarged view of a portion A. As shown in (A) and (B), the structure of the present invention comprises the accessory mounting surface 1a of the jet engine and the accessory 7
And a plurality of mounting members 16 respectively mounted with bolts 13 or the like. Further, as shown in (C), the mounting member 16 is attached to the auxiliary machine mounting surface 1a in the axial direction X.
And a bending portion 16a that follows thermal expansion in the circumferential direction Y, and a damping portion 16b that absorbs vibration by friction. In the example of FIG. 2, the mounting member 16 is a metal flat plate curved in a U-shape as a whole, and a portion curved in a U-shape constitutes a bent portion 16a. In addition, it has a curved portion 17a bulging inward at both ends, and this portion is tightened to the accessory mounting surface 1a and the accessory 7 with bolts 13 so that the curved portion 17a functions as a damping portion 16b. Vibration is absorbed by friction between the auxiliary machine mounting surface 1a and the auxiliary machine 7.

According to the configuration of the present invention described above, since the accessory mounting surface 1a and the accessory 7 are directly connected via the plurality of mounting members 16, the rigidity of the mounting member 16 reduces a large load during acceleration. It can be reliably supported, and simplification of the structure and weight reduction can be expected. Further, since the mounting member 16 has the bent portion 16a that follows the thermal expansion, the elastic deformation of this portion can follow the thermal expansion of the accessory mounting surface in the axial direction X and the circumferential direction Y. . Further, the mounting member 1
6 has a damping portion 16b, so that vibration transmitted by friction at this portion can be reduced.

FIG. 3 is a view showing another embodiment of the mounting member of the present invention. In this figure, the mounting member 16 is an annular member, and this annular member has cut surfaces 17b urged together. That is, the portion curved in an arc in this figure is the bent portion 16a, and this portion follows the thermal expansion of the accessory mounting surface 1a. The right cut surface 17b has partially folded ends that are in close contact with each other and are strongly pressed together by the elasticity of the member itself. Other configurations are the same as those in FIG. With this configuration, it is possible to follow the thermal expansion of the accessory mounting surface 1a at the bent portion 16a and to reduce vibration transmitted by friction between the cut surfaces 17b. This structure is particularly suitable for relatively small and medium volumes.

FIG. 4 is a view showing still another embodiment of the mounting member of the present invention. The mounting member 16 in this figure is particularly suitable for a relatively large capacity. The mounting member 16 is an annular member having a rectangular cross section obtained by bending a thick metal plate. This member can be manufactured relatively easily by welding a part thereof (the center at the left end). Also, the right cut surface 17b has its ends in close contact with each other and is strongly pressed against each other by the elasticity of the member itself. Other configurations are the same as those in FIG.

FIG. 5A is a view showing still another embodiment of the mounting member of the present invention. The mounting member 16 in this figure also
It is the same as FIG. 4 except that it is particularly suitable for a relatively large capacity and has an octagonal cross-sectional shape. FIG. 5B is a view taken along the line AA in FIG. In this figure, the cut surface 17b on the right side is a tapered surface that extends obliquely with respect to the axial direction of the engine, and is a surface of the tapered surface (cut surface 17b) that applies a large load to the auxiliary equipment 7 during acceleration. Accessory mounting surface 1 by pressure
a. With this configuration, it is possible to reliably support a large load during acceleration while freely following thermal expansion. This configuration can also be applied to the mounting member shown in FIG. FIG. 5C shows the cut surface 1.
7b shows a manufacturing method in which the members 7b are brought into close contact with each other and strongly pressed together by the elasticity of the member itself. That is, a jig 19 as shown in FIG.
Is fixed and clamped in a state where it is strongly stretched inside, and in this state, the attachment members 16 are welded to each other, so that the contact surface pressure remains on the cut surface 17b.

It should be noted that the present invention is not limited to the above-described embodiment, and it goes without saying that various changes can be made without departing from the spirit of the present invention.

[0021]

As described above, the accessory mounting structure for a jet engine according to the present invention can follow the axial and circumferential thermal expansion of the accessory mounting surface without using a vibration-proof rubber having a short life. It has excellent effects such as being able to reliably support a large load during acceleration and reducing the transmission of vibrations in the axial and radial directions.

[Brief description of the drawings]

FIG. 1 is a view showing a structure for attaching auxiliary equipment to a jet engine according to the present invention.

FIG. 2 is a diagram of another accessory mounting structure for a jet engine according to the present invention.

FIG. 3 is a view showing another embodiment of the mounting member of the present invention.

FIG. 4 is a view showing still another embodiment of the mounting member of the present invention.

FIG. 5 is a view showing still another embodiment of the mounting member of the present invention.

FIG. 6 is an overall configuration diagram of a jet engine.

FIG. 7 is a diagram of a conventional accessory mounting structure for a jet engine.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Jet engine 1a Bypass duct (accessory mounting surface) 2 Fan 3 Compressor 4 Combustor 5 Turbine 6 Afterburner 7 Auxiliary device 12 Supporting member 14 Flange 16 Mounting member 16a Flexure 16b Damping 17a Curved 17b Cutting 19 Ingredient

Claims (5)

[Claims] 1. An accessory mounting surface (1a) of a jet engine.
And a flange (14) for fixing both ends of the support member to the accessory mounting surface, the support member being attached to the accessory (7). An auxiliary machine mounting structure for a jet engine, characterized by having elasticity to follow thermal expansion of a mounting surface in an axial direction and a circumferential direction. 2. The accessory mounting structure for a jet engine according to claim 1, further comprising a pair of support members crossing each other in an X shape at a central portion. 3. An accessory mounting surface (1a) of a jet engine.
And a plurality of attachment members (16) sandwiched between and attached to the auxiliary device (7), and the attachment member has a flexure portion ( 16a) and a damping portion (16b) for absorbing vibration by friction, for attaching an accessory to a jet engine. 4. The mounting member (16) is a metal plate which is entirely curved in a U-shape, has a curved portion (17a) bulging inward at both ends, and the curved portion and an auxiliary machine mounting portion. Surface (1a)
The accessory mounting structure for a jet engine according to claim 3, wherein vibration is absorbed by friction between the auxiliary engine (7) and the auxiliary machine (7). 5. The mounting member (16) is an annular member, the annular members being biased to each other by cut surfaces (17b).
The accessory mounting structure for a jet engine according to claim 3, comprising: