CN202964557U - Aircraft bearing installation compression device - Google Patents
Aircraft bearing installation compression device Download PDFInfo
- Publication number
- CN202964557U CN202964557U CN 201220575422 CN201220575422U CN202964557U CN 202964557 U CN202964557 U CN 202964557U CN 201220575422 CN201220575422 CN 201220575422 CN 201220575422 U CN201220575422 U CN 201220575422U CN 202964557 U CN202964557 U CN 202964557U
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- Prior art keywords
- bearing
- aircraft
- engine
- compression device
- assembly
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- Expired - Fee Related
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- Mounting Of Bearings Or Others (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The utility model relates to an aircraft bearing installation compression device which is characterized by comprising a base, a fixed seat, a threaded shaft, a pressure plate, thrust ball bearings and a sleeve seat, wherein an engine bearing assembly is arranged in a spigot of the base; the base is connected with the fixed seat; the threaded shaft and the pressure plate are connected by two thrust ball bearings; the threaded shaft is in threaded connection with the fixed seat; and the sleeve seat is fixedly connected with the threaded shaft. The aircraft bearing installation compression device has the advantages that according to the aircraft bearing installation compression device disclosed by the utility model, the continuous axial loading and compressing operation of an aircraft rolling bearing installed in a heating manner on a hot charged inner ring in the cooling process is implemented, the size of a compression force can be accurately controlled, correct assembly of the bearing is ensured, the installation accuracy of the engine bearing and the reliability of work operation of the engine bearing are ensured and the bearing is prevented from losing efficacy due to improper assembly of the bearing; and moreover, the axial compression mechanism can also be adopted in the field of assembly of an engine wheel disk.
Description
Technical field
The utility model relates to mechanical field as a result, particularly a kind of aircraft bearing hold down gag is installed.
Background technology
Rolling bearing is support component commonly used in Aeroengine Power Transmission System, usually adopts the version of inner ring interference fit.And for internal diameter greater than 70mm or coordinate the installation of the larger rolling bearing of interference, generally adopt heating, brearing bore is expanded.After bearing was installed, its hot charging inner ring can shrink to some extent at width in cooling procedure, and is not tight for preventing the applying of cooling rear inner ring end face and the shaft shoulder, needs to apply certain pressure in cooling procedure inner ring is continued the axial compression operation to the shaft shoulder.
Existing compression mode about bearing, do not have isolated plant to realize compressing operation, the free-hand installation engine bearing clamp nut of general employing compresses, although this kind mode can satisfy the compression of bearing, but clamp nut is easily because of conduction effect generation screw thread gummed, during decomposition, the easy damaged screw thread, affect parts life-span, and the thrust size is uncertain.
The utility model content
The purpose of this utility model is in order effectively to realize the correct assembling of bearing, and the operational reliability of bearing when guaranteeing engine operation avoids causing because assembling is improper that bearing failure, spy provide a kind of aircraft bearing that hold down gag is installed.
The utility model provides a kind of aircraft bearing that hold down gag is installed, and it is characterized in that: described aircraft bearing is installed hold down gag, comprises pedestal 1, holder 2, thread spindle 3, platen 4, thrust ball bearing 5, block set 6;
Wherein: the engine shaft bearing assembly is arranged in the seam of pedestal 1, realize the radial location of engine shaft bearing assembly, pedestal 1 is connected with holder 2, thread spindle 3 connects by two thrust ball bearings 5 with platen 4, thread spindle 3 is threaded with holder 2, adopts thrust ball bearing structure can make in thread spindle 3 axial-rotation moving process, and 4 of the platen assemblies that connects with it move axially compression, rather than the spin friction loading, block set 6 is fixedly connected with thread spindle 3.
On described pedestal 1 with installing hole.
After the engine bearing heating is installed, pushing mechanism is connected with supporting mechanism by the screw thread on pedestal 1, the outer face of platen 4 is contacted with engine bearing inner ring shoulder, drive thread spindle 3 rotations by the standard torque wrench by the square toes on block set 6 again, it is moved axially, thereby realize axial loading that continue of bearing compressed by platen 4 transmitting thrusts that connect with thread spindle 3, after temperature of engine bearings is returned to room temperature, the dismounting pushing mechanism.
Advantage of the present utility model:
Aircraft bearing described in the utility model is installed hold down gag, realized that the aviation rolling bearing that heating is installed continues axially to load the compression operation to the hot charging inner ring in cooling procedure, and the large I of thrust realizes accurately controlling, guaranteed the correct assembling of bearing, installation accuracy and the work reliability of operation of engine bearing have been guaranteed, avoided causing bearing failure because bearing assemble is improper, in addition, also can use for reference this kind axial compression mechanism in the assembling field of turbine engine disk.
Description of drawings
Below in conjunction with drawings and the embodiments, the utility model is described in further detail:
Fig. 1 is the side view cutaway drawing that this aircraft bearing is installed hold down gag;
Fig. 2 is the schematic top plan view that this aircraft bearing is installed hold down gag.
The specific embodiment
Embodiment
The present embodiment provides a kind of aircraft bearing that hold down gag is installed, and it is characterized in that: described aircraft bearing is installed hold down gag, comprises pedestal 1, holder 2, thread spindle 3, platen 4, thrust ball bearing 5, block set 6;
Wherein: the engine shaft bearing assembly is arranged in the seam of pedestal 1, realize the radial location of engine shaft bearing assembly, pedestal 1 is connected with holder 2, thread spindle 3 connects by two thrust ball bearings 5 with platen 4, thread spindle 3 is threaded with holder 2, adopts thrust ball bearing structure can make in thread spindle 3 axial-rotation moving process, and 4 of the platen assemblies that connects with it move axially compression, rather than the spin friction loading, block set 6 is fixedly connected with thread spindle 3.
On described pedestal 1 with installing hole.
After the engine bearing heating is installed, pushing mechanism is connected with supporting mechanism by the screw thread on pedestal 1, the outer face of platen 4 is contacted with engine bearing inner ring shoulder, drive thread spindle 3 rotations by the standard torque wrench by the square toes on block set 6 again, it is moved axially, thereby realize axial loading that continue of bearing compressed by platen 4 transmitting thrusts that connect with thread spindle 3, after temperature of engine bearings is returned to room temperature, the dismounting pushing mechanism.
Claims (2)
1. an aircraft bearing is installed hold down gag, it is characterized in that: described aircraft bearing is installed hold down gag, comprises pedestal (1), holder (2), thread spindle (3), platen (4), thrust ball bearing (5), block set (6);
Wherein: the engine shaft bearing assembly is arranged in the seam of pedestal (1), pedestal (1) is connected with holder (2), thread spindle (3) connects by two thrust ball bearings (5) with platen (4), thread spindle (3) is threaded with holder (2), and block set (6) is fixedly connected with thread spindle (3).
2. according to aircraft bearing claimed in claim 1, hold down gag is installed, is it is characterized in that: described pedestal (1) is upper with installing hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220575422 CN202964557U (en) | 2012-11-05 | 2012-11-05 | Aircraft bearing installation compression device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220575422 CN202964557U (en) | 2012-11-05 | 2012-11-05 | Aircraft bearing installation compression device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202964557U true CN202964557U (en) | 2013-06-05 |
Family
ID=48505685
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220575422 Expired - Fee Related CN202964557U (en) | 2012-11-05 | 2012-11-05 | Aircraft bearing installation compression device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202964557U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103592125A (en) * | 2013-10-08 | 2014-02-19 | 东北大学 | Method for measuring radial dynamic flexibility of rolling bearing |
| CN104400743A (en) * | 2014-10-24 | 2015-03-11 | 河南平高电气股份有限公司 | Portable bearing installation tool |
| CN113977518A (en) * | 2021-11-12 | 2022-01-28 | 中国航发贵州黎阳航空动力有限公司 | Precise assembly fixture and assembly method for bearing bush of supporting casing |
| CN114029695A (en) * | 2021-09-16 | 2022-02-11 | 国营芜湖机械厂 | Replacement method of graphite bearing of aircraft fuel pump |
| CN114346959A (en) * | 2021-12-20 | 2022-04-15 | 广东明阳新能源科技有限公司 | Slip ring bearing assembling device and slip ring bearing assembling method |
-
2012
- 2012-11-05 CN CN 201220575422 patent/CN202964557U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103592125A (en) * | 2013-10-08 | 2014-02-19 | 东北大学 | Method for measuring radial dynamic flexibility of rolling bearing |
| CN103592125B (en) * | 2013-10-08 | 2016-03-16 | 东北大学 | A kind of method measuring the radial dynamic flexibility of rolling bearing |
| CN104400743A (en) * | 2014-10-24 | 2015-03-11 | 河南平高电气股份有限公司 | Portable bearing installation tool |
| CN104400743B (en) * | 2014-10-24 | 2017-01-18 | 河南平高电气股份有限公司 | Portable bearing installation tool |
| CN114029695A (en) * | 2021-09-16 | 2022-02-11 | 国营芜湖机械厂 | Replacement method of graphite bearing of aircraft fuel pump |
| CN113977518A (en) * | 2021-11-12 | 2022-01-28 | 中国航发贵州黎阳航空动力有限公司 | Precise assembly fixture and assembly method for bearing bush of supporting casing |
| CN113977518B (en) * | 2021-11-12 | 2023-08-04 | 中国航发贵州黎阳航空动力有限公司 | Precise assembly fixture and assembly method for bearing sleeve of supporting casing |
| CN114346959A (en) * | 2021-12-20 | 2022-04-15 | 广东明阳新能源科技有限公司 | Slip ring bearing assembling device and slip ring bearing assembling method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130605 Termination date: 20181105 |