JP2002127996A - Support device for gear box for aircraft engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To apply a load on an elastic body mainly comprising vibration only by minimizing displacement between sleeves during operation. SOLUTION: An engine side bracket 4 and a gear box side bracket 5 are rotatably connected to each other by a pin 6. A pin hole 7 is the gear box side bracket 5 is of a large diameter, an outer sleeve 8 is installed on an inner circumferential part of the pin hole 7, an inner sleeve 9 is installed on the pin 6, and the elastic body 12 is installed between the sleeves 8 and 9. Between the outer sleeve 8 and the inner sleeve 9, an offset quantity E in an inverse direction to thermal expansion displacement to be generated during operation is initially set to eliminate the offset quantity E during operation, thereby durability of the elastic body 12 is improved.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

The present invention relates to a gearbox support device for an aircraft engine.

[0002]

2. Description of the Related Art An aircraft engine is equipped with a gearbox such as an accessory gearbox in which various accessory devices are housed, and a thermal expansion displacement (difference) between the engine and the gearbox due to a temperature difference. Therefore, it is necessary to flexibly absorb these thermal expansion displacements and vibrations.

For this reason, conventionally, as shown in FIG. 3A, a plurality of support devices 1 having a cushion mechanism are used to equip the aircraft engine 2 with the gearbox 3.

The supporting device 1 is called a mounting device, and as shown in FIGS. 3 (b) and 3 (c) in an enlarged manner, a concave engine-side bracket 4 to be attached to an aircraft engine 2, and a gearbox. And a convex gearbox-side bracket 5 mounted on the gearbox-side bracket 3. The pinhole 7 provided in the gearbox-side bracket 5 has a large diameter, and an outer sleeve is provided on the inner peripheral surface of the large-diameter pinhole 7. 8, and an inner sleeve 9 that is fitted inside the outer sleeve 8 to the outer peripheral portion of the pin 6.
Is arranged so that an annular gap is formed between the inner peripheral surface of the outer sleeve 8 and the outer peripheral surface of the inner sleeve 9, and the silicone rubber 10 is entirely filled in the gap between the sleeves 8 and 9. A thin metal strip 11 coated in a thin film
The engine-side bracket 4 and the gearbox-side bracket 5 are assembled as an elastic body 12 having a coil-shaped laminated structure that is soft in the axial direction of the pin 6 and has a hard spring characteristic in the direction perpendicular to the pin 6. The two brackets 4 and 5 are rotatably connected by one pin 6 which is fitted and inserted into the inner sleeve 9, and is generated between the engine side bracket 4 and the gear box side bracket 5. The displacement of the pin 6 along the axial direction is absorbed by utilizing the displacement between the layers of the metal band 11 of the elastic body 12 and the pin generated between the engine side bracket 4 and the gear box side bracket 5. The vibration in the direction perpendicular to the direction 6 is absorbed by utilizing the elastic deformation of the silicone rubber 10 of the elastic body 12.

[0005]

However, in the case of the above-mentioned conventional supporting device 1, a thin metal band 1 is used as a cushion mechanism.
Since the elastic body 12 having the laminated structure of No. 1 is employed, vibration is absorbed in a state where the axial displacement between the outer sleeve 8 and the inner sleeve 9 due to thermal expansion is increased during operation of the engine. Therefore, there is a problem that deterioration such as abrasion easily progresses in the silicon rubber 10. That is, during operation, since high-frequency vibration is superimposed on static displacement due to heat with respect to the elastic body 12, the durability of the silicon rubber 10 is reduced. The spring characteristics along the axial direction will be lost. As a result, abnormal wear and abnormal vibration of the sleeve portion occur.

Accordingly, the present invention provides a gearbox support device for an aircraft engine that can minimize the axial displacement between sleeves during engine operation and can mainly apply a load to an elastic body mainly by vibration. What you want to do.

[0007]

SUMMARY OF THE INVENTION In order to solve the above-mentioned problems, according to the present invention, an engine-side bracket attached to an aircraft engine and a gearbox-side bracket attached to a gearbox are rotatably connected by pins. The pin hole of one of the brackets has a large diameter, and an outer sleeve is mounted on an inner peripheral portion of the large-diameter pin hole, and an inner sleeve is mounted on an outer peripheral portion of the pin. An elastic body is attached to the gap between the inner sleeve and the outer sleeve, and the offset amount in the opposite direction to the axial thermal expansion displacement that occurs during engine operation by interposing a spacer between the two brackets. The configuration is initialized.

When the thermal expansion displacement in the axial direction occurs due to the operation of the engine, the displacement is absorbed by the elastic body. At this time, the elastic body returns to the original shape without deformation by setting the initial offset amount. Therefore, the load acting on the elastic body is mainly only vibration.

Further, when a bolt or a spring made of a shape memory alloy is interposed between the facing surfaces of the engine side bracket and the gear box side bracket as a spacer for initial setting of the offset amount, the initial setting of the offset amount is made possible. Can be easily performed.

[0010]

Embodiments of the present invention will be described below with reference to the drawings.

FIGS. 1 (a) and 1 (b) show an embodiment of the present invention. Similar to the support device 1 shown in FIGS. 4 (a), 4 (b) and 4 (c), a gear box side bracket 5 is shown. A pin hole 7 having a large diameter is provided in the pin insertion portion, and an annular gap is formed between the outer sleeve 8 and the inner sleeve 9 disposed in the pin hole 7, and the elastic body 12 is formed in the annular gap. In a configuration in which the engine-side bracket 4 and the gearbox-side bracket 5 are connected to each other by the pins 6 fitted and mounted and inserted through the inner sleeve 9, thermal expansion during engine operation at the time of assembling the device. The engine 2 is engineered so that the generated displacement in the direction opposite to the axial displacement between the outer sleeve 8 and the inner sleeve 9 is given as an offset E between the outer sleeve 8 and the inner sleeve 9. Fixes the side bracket 4,
A supporting device 1 ′ having a structure in which the gearbox-side bracket 5 is fixed to the gearbox 3, and the load on the elastic body 12 is limited to vibration only by reducing the offset amount E by thermal expansion during engine operation. And

At the time of assembling, a bolt 13 as a spacer is threaded through a required portion of the engine-side bracket 4 at the time of assembling, and the distal end portion is pressed against the side surface of the gearbox-side bracket 5 so that the elastic body 12 is pressed. The initial setting is made by transforming it into a bamboo shoot.

As shown in FIG. 1A, the engine 2 is operated in a state where the axial offset E between the outer sleeve 8 and the inner sleeve 9 is initially set by pressing the bolt 13 during assembly. In case, Figure 1
As shown in (b), the bolt 13 can be applied or removed.

When thermal expansion occurs in the engine 2 due to operation, the displacement is transmitted from the engine side bracket 4 to the inner sleeve 9 via the pin 6, so that the elasticity which has been deformed into a bamboo shoot as shown in FIG. The body 12 is shown in FIG.
As shown in (b), the shape is returned to the original shape, and the offset amount E is eliminated. Since the thermal expansion displacement between the outer sleeve 8 and the inner sleeve 9 can be empirically obtained, by setting the offset amount E appropriately, the elastic body 12 mainly absorbs only vibration during operation. Therefore, the load acting on the elastic body 12 during operation can be reduced, and the durability of the elastic body 12 can be improved. Therefore, when the life is the same as that of the conventional support device 1, it can be used with a longer operating length (displacement absorption amount due to thermal expansion) in the axial direction.

Next, FIGS. 2A and 2B show another embodiment of the present invention. In the same configuration as the supporting device 1 'shown in FIGS. The initial setting of the axial offset E between the inner sleeve 8 and the outer sleeve 9 at the time of attachment is performed by using a shape memory alloy spring 14 instead of using the bolt 13. It is. That is, the spring 14 made of a shape memory alloy, which normally contracts at the operating temperature of the engine 2 with a required elongation at normal temperature (at a normal temperature), as shown in FIG.
At the time of assembly, a spacer is interposed between the opposing surfaces of the engine-side bracket 4 and the gearbox-side bracket 5 as a spacer, and the offset amount E is initially set between the inner sleeve 8 and the outer sleeve 9. .

According to this embodiment, when the high temperature during operation of the engine 2 is transmitted to the spring 14, the spring 1
4 automatically contracts to allow the displacement of the engine-side bracket 4, so that the operation of applying and removing the bolt 13 as shown in FIGS. .

It should be noted that the present invention is not limited to the above-described embodiment, and the bolt 1 shown in FIGS.
Instead of the spring 14 made of a shape memory alloy shown in FIG. 3 or FIGS. 2 (a) and 2 (b), a solid paraffin such as a wedge which is melted at the operating temperature of the engine 2 is used as a spacer for setting the offset amount. That it may be used,
The shape of the engine-side bracket 4 and the gearbox-side bracket 5 may be reversely uneven, and it goes without saying that various changes can be made without departing from the scope of the present invention.

[0018]

As described above, according to the aircraft engine gear box support device of the present invention, the engine side bracket attached to the aircraft engine and the gear box side bracket attached to the gear box are rotated by the pins. The pin hole of one of the brackets has a large diameter, and an outer sleeve is attached to the inner peripheral portion of the large-diameter pin hole, and an inner sleeve is attached to the outer peripheral portion of the pin. An elastic body is attached to the gap between the sleeve and the outer sleeve, and the offset between the inner sleeve and the outer sleeve is opposite to the axial thermal expansion displacement that occurs during engine operation. The configuration is initialized by intervening, so when the engine is running, the axial displacement between the sleeves is minimized. As a result, the load on the elastic body can be mainly caused only by vibration, whereby the durability of the elastic body can be improved, and the engine side bracket and the gear can be used as spacers for initial setting of the offset amount. The excellent effect that the initial setting of the offset amount can be easily performed and the assembling can be easily performed by interposing a bolt or a spring made of a shape memory alloy between the facing surface portion with the box side bracket. Demonstrate.

[Brief description of the drawings]

FIG. 1 shows an embodiment of a gearbox support device for an aircraft engine according to the present invention, in which (a) is a schematic diagram showing a state at the time of assembly, and (b) is a schematic diagram showing a state at the time of operation. FIG.

FIG. 2 shows another embodiment of the present invention.
Is a schematic diagram showing a state at the time of assembly, and (b) is a schematic diagram showing a state at the time of operation.

3A and 3B show an example of a conventional supporting device, wherein FIG. 3A is an overall schematic view showing an assembled state, FIG. 3B is an enlarged view of a portion A in FIG. 3A, and FIG. FIG.

[Explanation of symbols]

 2 Aviation engine 3 Gear box 4 Engine side bracket 5 Gear box side bracket 6 Pin 7 Pin hole 8 Outer sleeve 9 Inner sleeve 12 Elastic body 13 Bolt (spacer) 14 Spring (spacer)

Claims (3)

[Claims] 1. An engine-side bracket attached to an aircraft engine and a gearbox-side bracket attached to a gearbox are rotatably connected by pins, and the pin hole of one of the brackets has a large diameter. The outer sleeve is attached to the inner peripheral portion of the pin hole having a diameter, and the inner sleeve is attached to the outer peripheral portion of the pin, and an elastic body is attached to a gap between the inner sleeve and the outer sleeve. A gearbox for an aircraft engine, characterized in that the offset amount in the direction opposite to the axial thermal expansion displacement generated during engine operation is initially set by interposing a spacer between the brackets. Support device. 2. The aircraft engine gearbox according to claim 1, wherein a bolt is interposed and pressed between opposing surfaces of the engine side bracket and the gearbox side bracket as a spacer for initial setting of the offset amount. Support device. 3. The aviation engine according to claim 1, wherein a spring made of a shape memory alloy is interposed between the facing surfaces of the engine-side bracket and the gearbox-side bracket as a spacer for initial setting of the offset amount. Gearbox support device.