CN214616780U

CN214616780U - Mechanism convenient for reducing vibration of intermediate speed reducer of aircraft engine

Info

Publication number: CN214616780U
Application number: CN202120307671.8U
Authority: CN
Inventors: 吴江; 赵严; 吴勇生; 赵玉琼
Original assignee: Jiangsu Jianghangzhi Aircraft Engine Components Research Institution Co Ltd
Current assignee: Jiangsu Jianghangzhi Aircraft Engine Components Research Institution Co Ltd
Priority date: 2021-02-03
Filing date: 2021-02-03
Publication date: 2021-11-05
Anticipated expiration: 2031-02-03

Abstract

The utility model belongs to the technical field of aero-engines, in particular to a mechanism for conveniently reducing vibration of an intermediate reducer of an aero-engine, which comprises an aero-engine body, wherein a spray pipe is arranged on the right side of the aero-engine body, a turbine is arranged on the right side inside the aero-engine body, a compressor is arranged on the left side inside the aero-engine body, when the reducer is vibrated, two damping springs on the bottom contract to absorb and buffer the vibration force in the vertical direction, so that the vibration is greatly reduced, when the reducer moves left and right, the damping springs on the left and right sides contract to further absorb the vibration force in the horizontal direction, so that the damping effect is greatly improved, the problem that the existing intermediate reducer of the aero-engine is directly arranged inside the aero-engine is solved, a damping mechanism is not arranged, so that the reducer is easily damaged by vibration, the maintenance cost is high.

Description

Mechanism convenient for reducing vibration of intermediate speed reducer of aircraft engine

Technical Field

The utility model discloses aeroengine technical field, concretely relates to be convenient for alleviate mechanism for intermediate reduction gear vibration of aeroengine.

Background

An aero-engine (aero-engine) is a highly complex and precise thermal machine, is used as the heart of an airplane, is not only the power for flying the airplane, but also an important driving force for promoting the development of aviation industry, each important change in human aviation history is inseparable from the technical progress of the aero-engine, and a reducer is an important part of the aero-engine.

The speed reducer direct mount is inside the aeroengine in the middle of current aeroengine, is not equipped with damper, leads to the speed reducer to receive the condition emergence that vibrations lead to inside device to damage very easily, and cost of maintenance is high.

SUMMERY OF THE UTILITY MODEL

For solving the problem that proposes among the above-mentioned background art, the utility model provides a be convenient for alleviate mechanism for reduction gear vibration among aircraft engine has damper, can play buffering and absorbing effect, makes the reduction gear more stable, avoids the internal device to damage characteristics.

In order to achieve the above object, the utility model provides a following technical scheme: a mechanism convenient for reducing vibration of an intermediate speed reducer of an aircraft engine comprises an aircraft engine body, wherein a spray pipe is arranged on the right side of the aircraft engine body, a turbine is arranged on the right side inside the aircraft engine body, a compressor is arranged on the left side inside the aircraft engine body, an installation cavity is fixedly connected to the left side of the aircraft engine body, a speed reducer is arranged inside the installation cavity, a fixing plate is arranged inside the installation cavity, two sliding blocks are slidably connected to the upper end face of the fixing plate, two supporting seats are fixedly connected to the upper end faces of the two sliding blocks, clamping cylinders are fixedly connected to the upper end faces of the two supporting seats, the two clamping cylinders are symmetrically arranged, the outer wall of the speed reducer is abutted against the insides of the two clamping cylinders, two damping springs are fixedly connected to the lower end face of the fixing plate, and a bottom plate is fixedly connected to the lower end faces of the two damping springs, the lower terminal surface of bottom plate and the inside bottom fixed connection of installation cavity, two the equal fixedly connected with two connecting rods in the left and right sides of bottom plate lie in the other end fixedly connected with buffer spring with two connecting rods of one side, two buffer spring's the other end respectively with the inner wall left and right sides fixed connection of installation cavity.

In order to facilitate fixed two clamp section of thick bamboo, as the utility model relates to a be convenient for alleviate the intermediate reduction gear vibration of aeroengine is with mechanism optimization, two the equal fixedly connected with mounting panel of up end of clamp section of thick bamboo, two threaded connection has fixing bolt between the mounting panel.

In order to avoid damaging the reduction gear outer wall, as the utility model relates to a be convenient for alleviate reduction gear vibration in the middle of the aeroengine is preferred with mechanism, two the inner wall of pressing from both sides a section of thick bamboo all is provided with the blotter, the blotter is the rubber material.

For the convenient distance between two clamping barrels of adjustment, as the utility model relates to a be convenient for alleviate aircraft engine intermediate reduction gear vibration with mechanism preferred, the slider passes through the up end sliding connection of slide rail and fixed plate.

For the convenience adaptation reduction gear exterior structure, as the utility model relates to a be convenient for alleviate aircraft engine intermediate reduction gear vibration with mechanism preferred, two it is semi-annular structure to press from both sides a section of thick bamboo.

Compared with the prior art, the beneficial effects of the utility model are that:

the reduction gear assembly is located between two clamp barrels behind the installation cavity is inside, two sliders that slide drive the supporting seat and the clamp barrel removes, thereby make two clamp barrels press from both sides the reduction gear tight fixed, make the reduction gear more firm, firmly fix two clamp barrels through fixing bolt afterwards, when the reduction gear receives vibrations, two damping spring contractions of bottom, thereby absorb the buffering to the vibrations power of vertical direction, greatly reduced vibrations, when controlling when the reduction gear, the damping spring that is located the left and right sides contracts, thereby further absorb the vibrations power of horizontal direction, improve the shock attenuation effect greatly, thereby make the bumper shock absorber more stable, avoid inside device to receive vibrations damage.

To sum up, this kind of be convenient for alleviate mechanism for reduction gear vibration in middle of aeroengine has damper, can play buffering and absorbing effect, makes the reduction gear more stable, avoids inside device to damage characteristics.

Drawings

The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description serve to explain the invention and not to limit the invention. In the drawings:

FIG. 1 is a structural diagram of an aircraft engine body of the present invention;

FIG. 2 is a view showing the inner structure of the installation cavity of the present invention;

FIG. 3 is a schematic view of the clamping cylinder of the present invention in a fixed state;

in the figure, 1, an aircraft engine body; 2. a nozzle; 3. a turbine; 4. a compressor; 5. a mounting cavity; 6. a speed reducer; 7. a fixing plate; 8. a slider; 9. a supporting seat; 10. a clamping cylinder; 11. a damping spring; 12. a base plate; 13. a connecting rod; 14. a buffer spring; 15. mounting a plate; 16. and (5) fixing the bolt.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. In addition, in the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.

Referring to fig. 1-3, the present invention provides the following technical solutions: a mechanism convenient for reducing vibration of an intermediate speed reducer of an aircraft engine comprises an aircraft engine body 1, a spray pipe 2 is arranged on the right side of the aircraft engine body 1, a turbine 3 is arranged on the right side inside the aircraft engine body 1, a compressor 4 is arranged on the left side inside the aircraft engine body 1, a mounting cavity 5 is fixedly connected to the left side of the aircraft engine body 1, a speed reducer 6 is arranged inside the mounting cavity 5, a fixing plate 7 is arranged inside the mounting cavity 5, two sliding blocks 8 are slidably connected to the upper end face of the fixing plate 7, two supporting seats 9 are fixedly connected to the upper end faces of the two sliding blocks 8, clamping cylinders 10 are fixedly connected to the upper end faces of the two supporting seats 9, the two clamping cylinders 10 are symmetrically arranged, the outer wall of the speed reducer 6 is abutted against the insides of the two clamping cylinders 10, two damping springs 11 are fixedly connected to the lower end face of the fixing plate 7, and a bottom plate 12 is fixedly connected to the lower end faces of the two damping springs 11, the lower terminal surface of bottom plate 12 and the inside bottom fixed connection of installation cavity 5, two connecting rods 13 of the equal fixedly connected with in the left and right sides of two bottom plates 12, lie in the other end fixedly connected with buffer spring 14 of two connecting rods 13 with one side, two buffer spring 14's the other end respectively with the inner wall left and right sides fixed connection of installation cavity 5.

In this embodiment: the assembly of reduction gear 6 is located between two clamp section of thick bamboo 10 behind installation cavity 5 is inside, two sliders 8 that slide drive supporting seat 9 and the clamp section of thick bamboo 10 removes, thereby make two clamp section of thick bamboo 10 press from both sides reduction gear 6 tight fixed, make reduction gear 6 more firm, it is firmly fixed with two clamp section of thick bamboo 10 through fixing bolt 16 afterwards, when reduction gear 6 receives vibrations, two damping spring 11 shrink of bottom, thereby absorb the buffering to the shaking force of vertical direction, greatly reduced vibrations, when controlling when reduction gear 6, the buffer spring 14 that is located the left and right sides shrink, thereby further absorb the shaking force of horizontal direction, improve the shock attenuation effect greatly, thereby make reduction gear 6 more stable, avoid inside device to receive vibrations and damage.

As a technical optimization scheme of the utility model, the equal fixedly connected with mounting panel 15 of up end of two cartridge 10, threaded connection has fixing bolt 16 between two mounting panels 15.

In this embodiment: the two clamping cylinders 10 clamp the speed reducer 6 to fix the speed reducer 6 more firmly, and then the two clamping cylinders 10 are firmly fixed by the fixing bolts 16.

As a technical optimization scheme of the utility model, the inner wall of two double-layered section of thick bamboo 10 all is provided with the blotter, and the blotter is the rubber material.

In this embodiment: through setting up the blotter, the blotter is the rubber material, and the texture is softer, plays the buffering effect, avoids reduction gear 6 direct and presss from both sides 10 inner wall contacts to lead to damaging 6 outer walls of reduction gear.

As a technical optimization scheme of the utility model, slider 8 passes through the slide rail and the up end sliding connection of fixed plate 7.

In this embodiment: the slide block 8 is connected with the upper end surface of the fixed plate 7 in a sliding way through a slide rail, so that the distance between the two clamping cylinders 10 can be conveniently adjusted, and the speed reducer 6 can be conveniently installed and clamped and fixed.

As a technical optimization scheme of the present invention, the two clamping cylinders 10 are semi-annular structures.

In this embodiment: the two clamping cylinders 10 are of a semi-annular structure, so that the external structure of the speed reducer 6 is convenient to arrange, and the fixing is firmer.

The utility model discloses a theory of operation and use flow: the assembly of reduction gear 6 is located between two clamp section of thick bamboo 10 behind installation cavity 5 is inside, two sliders 8 that slide drive supporting seat 9 and the clamp section of thick bamboo 10 removes, thereby make two clamp section of thick bamboo 10 press from both sides reduction gear 6 tight fixed, make reduction gear 6 more firm, it is firmly fixed with two clamp section of thick bamboo 10 through fixing bolt 16 afterwards, when reduction gear 6 receives vibrations, two damping spring 11 shrink of bottom, thereby absorb the buffering to the shaking force of vertical direction, greatly reduced vibrations, when controlling when reduction gear 6, the buffer spring 14 that is located the left and right sides shrink, thereby further absorb the shaking force of horizontal direction, improve the shock attenuation effect greatly, thereby make reduction gear 6 more stable, avoid inside device to receive vibrations and damage.

The above description is only exemplary of the present invention and should not be construed as limiting the present invention, and any modifications, equivalents and improvements made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.

Claims

1. The utility model provides a mechanism for intermediate reduction gear vibration convenient to alleviate aeroengine, includes aeroengine body (1), its characterized in that: the right side of the aircraft engine body (1) is provided with a spray pipe (2), the right side inside the aircraft engine body (1) is provided with a turbine (3), the left side inside the aircraft engine body (1) is provided with a gas compressor (4), the left side of the aircraft engine body (1) is fixedly connected with an installation cavity (5), the inside of the installation cavity (5) is provided with a speed reducer (6), the inside of the installation cavity (5) is provided with a fixed plate (7), the upper end face of the fixed plate (7) is in sliding connection with two sliding blocks (8), the upper end faces of the two sliding blocks (8) are fixedly connected with two supporting seats (9), the upper end faces of the two supporting seats (9) are both fixedly connected with clamping cylinders (10), the two clamping cylinders (10) are symmetrically arranged, the outer wall of the speed reducer (6) is abutted to the insides of the two clamping cylinders (10), two damping spring (11) of lower terminal surface fixedly connected with of fixed plate (7), two damping spring (11)'s lower terminal surface fixedly connected with bottom plate (12), the lower terminal surface of bottom plate (12) and the inside bottom fixed connection of installation cavity (5), two equal fixedly connected with two connecting rods (13) in the left and right sides of bottom plate (12), lie in other end fixedly connected with buffer spring (14) with two connecting rods (13) of one side, two buffer spring (14)'s the other end respectively with the inner wall left and right sides fixed connection of installation cavity (5).

2. A mechanism for facilitating the mitigation of vibration in an intermediate speed reducer of an aircraft engine as defined in claim 1, wherein: the upper end face of the two clamping cylinders (10) is fixedly connected with mounting plates (15), and fixing bolts (16) are connected between the mounting plates (15) in a threaded mode.

3. A mechanism for facilitating the mitigation of vibration in an intermediate speed reducer of an aircraft engine as defined in claim 1, wherein: the inner walls of the two clamping cylinders (10) are provided with cushion pads, and the cushion pads are made of rubber materials.

4. A mechanism for facilitating the mitigation of vibration in an intermediate speed reducer of an aircraft engine as defined in claim 1, wherein: the sliding block (8) is connected with the upper end face of the fixed plate (7) in a sliding mode through a sliding rail.

5. A mechanism for facilitating the mitigation of vibration in an intermediate speed reducer of an aircraft engine as defined in claim 1, wherein: the two clamping cylinders (10) are of a semi-annular structure.