JP2000002156A - Mounting structure of electronic appliance on jet engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a mounting structure for electronic appliance on jet engine, whereby it is practicable to absorb a thermal expansion, bear a large load at acceleration properly, and reduce vibrational transmission in the axial direction and the gravitational direction. SOLUTION: A mounting structure is to mount a box-shaped electronic appliance 7 on a bypass duct 1a of a jet engine in approx. cylindrical form, wherein in front of the box shape, a first tie-in member 11a is provided having a surface parallel with the box facade and protruding out from the box width, and behind the box shape, a second tie-in member 12a is provided having a surface parallel with the box surface on the bypass duct side and protruding out from the box width, and the bypass duct 1a is equipped with a bracket 13 having a parallel surface with the box facade. The first tie-in member 11a is coupled by bolt in a position ahead of the bracket surface and in such a way as pinching a vibration isolating rubber piece 14, and a pad 17 is provided on the surface confronting the second tie-in member 12a, and the pad 17 and the second member 12a are coupled together by bolt in such a way as pinching vibration isolating rubber.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

The present invention relates to a structure for mounting electronic equipment on a jet engine.

[0002]

FIG. 4 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, an electronic control unit (hereinafter, referred to as an electronic control unit) for controlling the jet engine is provided on an outer peripheral portion of the jet engine.
Is simply attached to the bypass duct 1a, for example.

FIG. 5 is a schematic view showing a conventional electronic device mounting structure for a jet engine. As shown in this figure, conventionally, the electronic device 7 is attached to the bypass duct 1a or the like by a bracket + anti-vibration rubber method.

[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 on the electronic device 7 of the jet engine at the time of flight of the aircraft in the axial direction.
Vibrates in the axial and gravitational directions.

[0006] Therefore, the electronic equipment mounting structure to the jet engine must cope with thermal expansion of the bypass duct 1a, large acceleration in the axial direction, and vibration in the axial and gravitational directions.

In the bracket + anti-vibration rubber system shown in FIG. 5, a bracket 9a attached to the electronic device 7 is attached to an attachment seat 9c attached to the bypass duct 1a.
The bolt is tightened with the b in between. In order to oppose the maximum load, for example, the direction of the arrow at which 20G is generated, by the frictional force and the shearing force of the bolt, the bolt must be thick and the surrounding structure must be strong. Instead, it had a heavy structure.

The present invention has been made to solve such a problem. That is, an object of the present invention is to provide an electronic device mounting structure for a jet engine which can absorb thermal expansion, appropriately support a large load during acceleration, and reduce vibration transmission in the axial direction and the gravitational direction. Is to do.

[0009]

According to the first aspect of the present invention, there is provided a structure for mounting a box-shaped electronic device on a bypass duct of a substantially cylindrical jet engine. A first connecting member having a surface parallel to the box-shaped front surface and projecting outside the box width,
Further, at the rear of the box, a second connecting member having a surface parallel to the box-shaped surface on the bypass duct side and projecting outside the box width is provided, and the bypass duct has a surface parallel to the box-shaped front surface. A bracket having the first mounting member is provided in front of the surface of the bracket and bolted together with a vibration-proof rubber, and a pad is provided on a surface facing the second mounting member. The connecting member is bolted together with the vibration isolating rubber therebetween.

According to the configuration of the present invention, the first mounting member and the bracket are connected by bolts with the first mounting member forward of the surface of the bracket and sandwiching the vibration isolating rubber. For this reason, it becomes a structure that receives the maximum load applied from the front to the rear as a compressive force on the surface,
The support structure can be made simple and lightweight. Also,
By joining the second connecting member and the pad, a moment generated in the electronic device can be suppressed and run-out and vibration can be prevented.
Since the first and second connecting members are joined to the bracket or the pad with the vibration isolating rubber interposed therebetween, vibration and thermal expansion of the bypass duct can be absorbed.

According to the invention of claim 2, the second connecting member is bent along the arc of the bypass duct.

When the diameter of the bypass duct is larger than the width of the box of the electronic device, the second connecting member may be parallel to the surface of the box-shaped bypass duct, but when the diameter of the bypass duct becomes smaller. Since the distance between the second connecting member and the bypass duct becomes large, the second connecting member is bent along the arc of the bypass duct to reduce the distance and join.

[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 structural diagram of an electronic device mounted on a jet engine according to the present invention. 2 shows a sectional view taken along line XX of FIG. 1, and FIG. 3 shows a sectional view taken along line YY of FIG.

As shown in the drawings, the structure of the present invention is a front surface of a box-shaped electronic device 7 (a surface in a forward direction when attached to a bypass duct 1a of a jet engine. The left direction in FIG. 1 is a forward direction). Is protruded from the box width (length in the vertical direction in FIG. 1), and this protruding portion is used as a first connecting member 11a. The first connection members 11a are provided on both sides of the box width.

A plate 12 inside the box-shaped electronic device 7 (on the side facing the bypass duct 1a when attached to the bypass duct 1a) is made to protrude beyond the box width at the rear, and this protruding portion is connected to the second fitting member 12a. I do. The second connection members 12a are provided on both sides of the box width, and are bent along the arc of the bypass duct 1a as shown in FIG.

A bracket 13 and a pad 17 are provided at positions corresponding to the bypass duct 1a with respect to the connecting members 11a and 12a of such a box-shaped electronic device 7. The bracket 13 includes a pad 13a joined to the bypass duct 1a by bolts or welding, and a pad 13a.
A vertical plate 13b whose surface is parallel to the box-shaped front surface 3a
Is attached, and a support member 1 for supporting the vertical plate 13b is provided.
3c is fixed to the vertical plate 13b and the pad 13a.
The pad 17 is joined to the bypass duct 1a by bolts or welding.

The first connecting member 11a and the bracket 13
The vibration-proof rubber 14, the first connecting member 11a, the vibration-proof rubber 14, and the pressing plate 15 are arranged in this order in front of the vertical plate 13b, and are connected by bolts 16 penetrating these. Further, the second mounting member 12a and the pad 17 are placed on the pad 17 with the vibration-proof rubber 18 and the second mounting member 12 placed thereon.
a, the vibration isolating rubber 18 and the holding plate 19 are arranged in this order,
They are connected by bolts 20 penetrating them.

Next, the operation will be described. For the maximum acceleration indicated by the arrow in FIG.
The load caused by the acceleration applied to the first member 11a
And transmitted to the anti-vibration rubber 14 via the bracket 13 to the bypass duct 1a. Since the load is transmitted to the surfaces of the first connecting member 11a, the vibration isolating rubber 14, and the vertical plate 13b, the force is appropriately transmitted, and the structure for transmitting the force is also simple, and the weight can be reduced. Since the moment applied to the electronic device 7 is suppressed by joining the second connection member 12a and the pad 17, vibration can be prevented.

With respect to the thermal expansion of the bypass duct 1a in the axial direction, the fixing position of the first connecting member 11a and the bracket 13 is fixed, and the vibration isolating rubber 18 is fixed at the connecting portion of the second connecting member 12a and the pad 17. Thermal expansion can be absorbed by shear deformation. This is anti-vibration rubber 1
Since the spring constant in the shearing direction is one-hundredths to tens of tenths of the compression spring constants 4 and 18, the first connecting member 11
a of the second engaging member 1 than the compression deformation of the vibration isolating rubber 14 of FIG.
This is because the shear deformation of the vibration-proof rubber 18 of 2a is much larger. In addition, with respect to the thermal expansion in the circumferential direction of the bypass duct 1a, the vibration isolating rubber 14 of the first connecting member 11a and the vibration isolating rubber 18 of the second connecting member 12a both perform shear deformation to absorb the thermal expansion.

As for the vibration in the axial direction, similar to the thermal expansion in the axial direction, the vibration isolating rubber 1 of the second connecting member 12a is mainly used.
The vibration is attenuated by the shear deformation of FIG. Also, regarding vibration in the direction of gravity (vertical direction in FIG. 1), the vibration-proof rubber 14 of the first
Each of the anti-vibration rubbers 18 a undergoes shear deformation to attenuate vibration.

[0021]

As described above, the structure for mounting the electronic device to the jet engine according to the present invention is a structure that receives a compressive force on the surface with respect to the maximum load, and the vibration-proof rubber against the thermal expansion and vibration. Absorption and attenuation are achieved by utilizing the shear characteristics, so the mounting structure can be simplified and reduced in weight, and the anti-vibration properties and escape properties of thermal deformation can be improved by utilizing the shear characteristics of the anti-vibration rubber. .

[Brief description of the drawings]

FIG. 1 is a view showing a structure for mounting electronic devices on a jet engine according to the present invention.

FIG. 2 is a sectional view taken along line XX of FIG.

FIG. 3 is a sectional view taken along line YY of FIG. 1;

FIG. 4 is an overall configuration diagram of a jet engine.

FIG. 5 is a diagram showing a conventional electronic device mounting structure for a jet engine.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Jet engine 1a Bypass duct 2 Fan 3 Compressor 4 Combustor 5 Turbine 6 Afterburner 7 Electronic equipment 11 Front plate 11a First connection member 12 Inner plate 12a Second connection member 13 Bracket 13a Pad 13b Vertical plate 13c Support member 14 Vibration rubber 15 Holding plate 16 Bolt 17 Pad 18 Vibration-proof rubber 19 Holding plate 20 Bolt

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁷ Identification symbol FI Theme coat ゛ (Reference) F02C 7/32 F02C 7/32

Claims (2)

[Claims] In a structure for mounting a box-shaped electronic device to a bypass duct of a substantially cylindrical jet engine, a box-shaped front portion has a surface parallel to a box-shaped front surface and protrudes outside the box width. A first connecting member, and a second connecting member provided at a rear portion of the box and having a surface parallel to the box-shaped surface on the bypass duct side and protruding outside the box width; A bracket having a surface parallel to the front surface of the shape is provided, and the first mounting member is provided forward of the surface of the bracket and bolted with vibration-proof rubber therebetween, and a pad is placed on a surface facing the second mounting member. An electronic device mounting structure for a jet engine, wherein the pad and the second connecting member are bolted to each other with an anti-vibration rubber therebetween. 2. The structure for mounting an electronic device on a jet engine according to claim 1, wherein the second connecting member is bent along an arc of a bypass duct.