CN214578398U

CN214578398U - Aeroengine bearing inner race installation device

Info

Publication number: CN214578398U
Application number: CN202120863994.5U
Authority: CN
Inventors: 董永耀; 胡涛; 唐民锋; 杨帝思; 张蝶洪; 贺勃龙; 康酌; 马力; 李文瀚
Original assignee: Sichuan Chuanhang Aero Engine Maintenance Engineering Co ltd
Current assignee: Sichuan Chuanhang Aero Engine Maintenance Engineering Co ltd
Priority date: 2021-04-25
Filing date: 2021-04-25
Publication date: 2021-11-02
Anticipated expiration: 2031-04-25

Abstract

The utility model discloses an aeroengine bearing inner race installation device, including chassis, setting recess in the chassis, rotation setting rolling disc, a plurality of setting on the chassis and directional rolling disc rotation center's flexible arm recess and the flexible arm of slip setting in flexible arm recess of rotation center, the one end and the recess intercommunication of flexible arm recess, the other end of flexible arm recess and the external intercommunication on chassis, it has flexible arm connecting rod to articulate between rolling disc and the flexible arm. The utility model has the advantages that: this scheme can be used for the auxiliary bearing outer lane, and during the use, the staff need not contact the bearing inner race, can avoid the bearing inner race to leave sweat stain vestige to can prevent staff's burn.

Description

Aeroengine bearing inner race installation device

Technical Field

The utility model relates to an aeroengine bearing technical field, specific theory is an aeroengine bearing inner race installation device.

Background

An aero-engine (aero-engine), which is a highly complex and precise thermal machine, provides the aircraft with the power required for flight. For an aircraft engine, the most important is a rotating part, for example, a turboshaft engine, and the turbine speed of the aircraft engine exceeds 50000r/min under a normal working state. The bearing is a key component of an engine transmission system, and the high rotating speed, high load, high temperature and complex working condition of the turbine are that the bearing must keep a good state. The bearing is generally composed of four parts, namely an outer ring, an inner ring, rolling bodies and a retainer (see figure 1).

According to recent statistics on the failure of aeroengine bearings, the abnormal increase of the temperature inside the bearings under high-speed complex working conditions causes problems such as reduction of the viscosity of lubricating oil, reduction of the bearing capacity, tempering or burning of inner and outer ring channels and balls, and burning corrosion of guide surfaces of a retainer, so that the bearings are subjected to early fatigue failure. The overhigh temperature even causes the gluing and seizure of the bearing, leads to the aggravation of the vibration of the whole mechanical transmission system and seriously affects the service life and the reliability of the bearing. In addition to the factors such as design defects of the bearing and unreasonable assembly parameters, the failure is caused by the out-of-specification of an operator in the assembly process of the bearing assembly of the aircraft engine.

Aircraft engine body assembly involves the combination of multiple components so that the bearing assembly cannot be installed in a complete state. Taking the installation of the fourth pivot bearing of a certain type of aircraft engine as an example, because the bearing is generally in an interference state after being assembled, the bearing needs to be heated to more than 150 ℃ by using the principle of expansion with heat and contraction with cold and a high-temperature gun, and then an operator can quickly and accurately align and install the bearing. This process has the following difficulties: 1) an operator can not contact the bearing outer ring with bare hands, otherwise sweat stains are easily left on the bearing outer ring, and sweat stain marks cannot be eliminated after the bearing outer ring is subjected to high temperature; 2) generally, operators are required to wear silk cloth gloves to operate, sweat stain pollution can be prevented, but the silk cloth gloves have poor anti-skid performance due to the fact that a large amount of lubricating oil is smeared on the outer rings of the bearings, and accidents such as falling off hands and falling on the ground are easily caused. 3) The silk cloth gloves have poor heat insulation performance, and operators are easily scalded by high temperature at the installation position.

With the development of the aviation industry, the demand of an aero-engine is greatly increased, the concern on the safety of a bearing is also greatly improved, and therefore a device which is convenient, fast and safe to use is very necessary when the bearing is assembled.

SUMMERY OF THE UTILITY MODEL

For overcoming the not enough of prior art, the utility model aims to provide an aeroengine bearing inner race installation device.

The utility model discloses a following technical scheme realizes: the utility model provides an aeroengine bearing inner race installation device, includes the chassis, sets up recess in the chassis, rotates the rolling disc, a plurality of setting that set up in the recess on the chassis and directional rolling disc rotation center's flexible arm recess and the flexible arm of slip setting in flexible arm recess, the one end and the recess intercommunication of flexible arm recess, the other end of flexible arm recess and the external intercommunication on chassis, articulated between rolling disc and the flexible arm have flexible arm connecting rod.

Further, for better realization the utility model discloses, the recess be the disc, the chassis is the disc, recess and the coaxial setting in chassis.

Further, for better realization the utility model discloses, the rolling disc be the disc type with the coaxial setting in chassis.

Further, for better realization the utility model discloses, the rolling disc on be provided with the rotation axis coaxial with the rolling disc.

Further, for better realization the utility model discloses, the rotation axis on be provided with the rotation axis handle, rotation axis handle and rotation axis form the T type.

Further, for better realization the utility model discloses, the chassis on be provided with the bottom plate handle.

Further, for better realization the utility model discloses, the free end of flexible arm be provided with bearing inner race retaining ring, the side that bearing inner race retaining ring and flexible arm are relative be the arc surface of evagination.

Further, for better realization the utility model discloses, bearing inner race retaining ring can dismantle with flexible arm and be connected.

The beneficial effect that this scheme obtained is: this scheme can be used for the auxiliary bearing outer lane, and during the use, the staff need not contact the bearing inner race, can avoid the bearing inner race to leave sweat stain vestige to can prevent staff's burn.

Drawings

FIG. 1 is a schematic structural diagram of the present embodiment;

the device comprises a base plate 1, a groove 2, a rotating disc 3, a rotating shaft 4, a telescopic arm connecting rod 5, a telescopic arm 6, a bearing outer ring retaining ring 7 and a bottom plate handle 8.

Detailed Description

The present invention will be described in further detail with reference to examples, but the present invention is not limited thereto.

Example 1:

as shown in fig. 1, in this embodiment, an aeroengine bearing inner race installation device includes chassis 1, the recess 2 of setting in chassis 1, the rolling disc 3 of rotation setting in recess 2, a plurality of setting on chassis 1 and directional rolling disc 3 rotation center's flexible arm recess and the flexible arm 6 of slip setting in flexible arm recess, the one end and the recess intercommunication of flexible arm recess, the other end and the chassis 1's of flexible arm recess external intercommunication, articulated between rolling disc 3 and the flexible arm 6 have flexible arm connecting rod 5.

When the bearing outer ring needs to be installed, the device is placed in an inner hole of the bearing outer ring, the rotating disc 3 is driven to rotate, the rotating disc 3 can drive the telescopic arms 6 to move through the telescopic arm connecting rods 5, the telescopic arms 6 move outwards until all the telescopic arms 6 are in contact with the bearing outer ring, the rotating disc 3 is locked, the telescopic arms 6 can be used for clamping the bearing outer ring, and therefore a worker does not need to directly contact the bearing outer ring.

Example 2:

on the basis of the above embodiment, in this embodiment, the groove 2 is a disk, the chassis 1 is a disk, and the groove 2 and the chassis 1 are coaxially arranged. Therefore, the chassis 1 is conveniently placed in the internal control of the outer ring of the bearing, and the interference condition is avoided.

In this embodiment, the rotating disk 3 is a disk-shaped disk coaxially disposed with the base plate 1. Therefore, the plurality of telescopic arm connecting rods 5 and the telescopic arms 6 can be conveniently and synchronously moved, and the control precision of the device can be effectively improved.

In this embodiment, three telescopic arms 6 are provided, and the three telescopic arms 6 are uniformly distributed at 120 °. Therefore, when the telescopic arm 6 is used for applying pressure to the bearing outer ring, the bearing outer ring is uniformly stressed, and the connection strength and the connection stability of the telescopic arm 6 and the bearing outer ring are improved.

Example 3:

in addition to the above embodiments, in the present embodiment, the rotating disc 3 is provided with the rotating shaft 4 coaxial with the rotating disc 3. The rotation axis 4 that the utilization was extended is convenient for control rolling disc 3 and is rotated for this scheme use is more convenient. The rotary shaft 4 and the rotary disk 3 may be arranged eccentrically.

In this embodiment, the rotating shaft 4 is provided with a rotating shaft handle, and the rotating shaft handle and the rotating shaft 4 form a T shape. Utilize the rotation axis handle to be convenient for to the rotation axis application of force for this scheme facilitates the use more.

In this embodiment, the chassis 1 is provided with a bottom plate handle 8. The chassis 1 can be kept stable by grabbing the bottom plate handle 8, after the outer ring of the bearing is locked by the telescopic arm 6, the relative position of the chassis 1 and the rotating disc 3 is kept fixed conveniently, and the chassis 1 and the rotating disc 3 are prevented from rotating relatively to cause the telescopic arm 6 to loosen.

Example 4:

on the basis of the above embodiments, in this embodiment, the free end of the telescopic arm 6 is provided with the bearing outer ring retaining ring 7, and the side surface of the bearing outer ring retaining ring 7 opposite to the telescopic arm 6 is a convex arc surface. The bearing outer ring retaining ring 7 is arranged to increase the pressure bearing area of the bearing outer ring and increase the static friction force at the pressure bearing part of the bearing outer ring, so that the improvement of the connection strength between the bearing outer ring and the telescopic arm 6 and the stability of the bearing outer ring are facilitated.

Example 5:

on the basis of the above embodiment, in the present embodiment, the bearing outer ring retaining ring 7 is detachably connected to the telescopic arm 6. The bearing outer ring retaining ring 7 with different sizes is replaced conveniently, the bearing outer ring with different inner diameter sizes is required to be arranged at the moment, and the application range of the scheme is widened.

Example 6:

on the basis of the above embodiments, in this embodiment, the telescopic arm groove can be replaced by a through hole, so as to increase the stability and the moving precision of the telescopic arm 6 and avoid the telescopic arm from departing from the range of the base plate 1.

In this embodiment, other undescribed contents are the same as those in the above embodiment, and thus are not described again.

The above is only the preferred embodiment of the present invention, not to the limitation of the present invention in any form, all the technical matters of the present invention all fall into the protection scope of the present invention to any simple modification and equivalent change of the above embodiments.

Claims

1. The utility model provides an aeroengine bearing inner race installation device which characterized in that: including chassis (1), setting recess (2) in chassis (1), rotating the rolling disc (3) that set up in recess (2), a plurality of setting on chassis (1) and directional rolling disc (3) rotation center's flexible arm recess and the flexible arm (6) of slip setting in flexible arm recess, the one end and the recess intercommunication of flexible arm recess, the other end of flexible arm recess and the external intercommunication of chassis (1), articulated between rolling disc (3) and flexible arm (6) have flexible arm connecting rod (5).

2. An aircraft engine bearing cup mounting arrangement according to claim 1, wherein: the groove (2) is disc-shaped, the chassis (1) is disc-shaped, and the groove (2) and the chassis (1) are coaxially arranged.

3. An aircraft engine bearing cup mounting arrangement according to claim 2, wherein: the rotating disc (3) is a disc type which is coaxial with the chassis (1).

4. An aircraft engine bearing cup mounting arrangement according to claim 3, wherein: the rotating disc (3) is provided with a rotating shaft (4) which is coaxial with the rotating disc (3).

5. An aircraft engine bearing cup mounting arrangement according to claim 4, wherein: the rotary shaft (4) is provided with a rotary shaft handle, and the rotary shaft handle and the rotary shaft (4) form a T shape.

6. An aircraft engine bearing cup mounting arrangement according to claim 5, wherein: the chassis (1) is provided with a bottom plate handle (8).

7. An aircraft engine bearing cup mounting arrangement according to any one of claims 1 to 6, wherein: the free end of the telescopic arm (6) is provided with a bearing outer ring retaining ring (7), and the side surface of the bearing outer ring retaining ring (7) opposite to the telescopic arm (6) is a convex arc surface.

8. An aircraft engine bearing cup mounting arrangement according to claim 7, wherein: the bearing outer ring retaining ring (7) is detachably connected with the telescopic arm (6).