CN114986443A - Assembly protection structure of aero-engine support assembly, use method and preparation method - Google Patents
Assembly protection structure of aero-engine support assembly, use method and preparation method Download PDFInfo
- Publication number
- CN114986443A CN114986443A CN202210497844.6A CN202210497844A CN114986443A CN 114986443 A CN114986443 A CN 114986443A CN 202210497844 A CN202210497844 A CN 202210497844A CN 114986443 A CN114986443 A CN 114986443A
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- CN
- China
- Prior art keywords
- tool
- protection
- bearing opening
- supporting component
- assembly
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/14—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for assembling objects other than by press fit or detaching same
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention relates to the field of maintenance of aero-engines, in particular to an assembling and protecting structure, a using method and a manufacturing method of an aero-engine supporting assembly, which are convenient, fast and effective to avoid damaging a two-fulcrum graphite ring and a bearing outer ring. The invention can effectively prevent the reworking repair of the two-fulcrum supporting assembly caused by collision, thereby preventing the repair and assembly period from being delayed and preventing the waste of resources. The invention is particularly suitable for being used when the ventilating duct in the two-fulcrum supporting component of the aircraft engine is installed.
Description
Technical Field
The invention relates to the field of maintenance of aero-engines, in particular to an assembling and protecting structure of an aero-engine supporting assembly, a using method and a manufacturing method.
Background
The assembly of aircraft engines is an important part of aircraft engine maintenance. When the ventilating duct in the two-fulcrum supporting assembly of a certain type engine is installed, an operator needs to stretch a tool into the central bevel gear box for operation, and the operation space is narrow, so that in the operation process, the hand of the operator and a tool in the hand are very easy to contact with the graphite ring on the two-fulcrum supporting assembly and the bearing outer ring, the two-fulcrum graphite ring and the bearing outer ring are damaged, the reworking repair of the two-fulcrum supporting assembly is caused, the repair and assembly period is delayed, and resources are wasted.
Disclosure of Invention
The invention aims to provide an aeroengine support component assembly protection structure, a use method and a preparation method, which are convenient, fast and effective and can avoid damaging a two-fulcrum graphite ring and a bearing outer ring.
The technical scheme adopted by the invention for solving the technical problems is as follows: aeroengine supporting component assembles protective structure, including the supporting component, the supporting component includes circular shape bearing opening, include with the protection frock that the bearing opening matches, the protection frock comprises frock open end and frock protection end, wherein, frock protection end sets up in the bearing opening, matches the laminating mutually between the outer wall of frock protection end and the inner wall of bearing opening, and the frock open end sets up in bearing open-ended outer edge.
Further, the use method of the protective structure for assembling the aircraft engine support assembly comprises the following steps: a. installing two fulcrum supporting components on the intermediary casing, and fixing the two fulcrum supporting components on the installation edge of the intermediary casing by using nuts; b. mounting a protection tool on an inner cavity of the bearing opening, and checking whether the tool is completely attached to the inner cavity; c. screwing the screws of the two sections of the vent pipes in the inner cavity of the bearing opening by using a spanner to meet the process requirement; d. and taking out the protection tool to complete the assembly operation.
Further, the preparation method of the aircraft engine support assembly assembling protection structure comprises the following steps: firstly, determining the shape and size parameters of the protection tool according to the bearing opening, and printing the protection tool in a 3D printing mode after the protection tool is determined.
The invention has the beneficial effects that: during the in-service use, the frock protection end of protection frock sets up in the bearing opening to implement the protection to the inner wall of bearing opening, let the frock in operating personnel's hand and the hand can't contact graphite ring and the bearing outer loop on two fulcrum supporting assemblies, thereby fundamentally prevents to appear damaging to graphite ring and bearing outer loop. The invention can effectively prevent the reworking repair of the two-fulcrum supporting assembly caused by collision, thereby preventing the repair and assembly period from being delayed and preventing the waste of resources. The invention is particularly suitable for being used when the ventilating duct in the two-fulcrum supporting component of the aircraft engine is installed.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Labeled as: protection frock 1, frock protection end 11, frock open end 12, frock mouth 13, supporting component 2, bearing opening 21.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
The aircraft engine supporting component assembly protection structure shown in fig. 1 comprises a supporting component 2, wherein the supporting component 2 comprises a circular bearing opening 21 and a protection tool 1 matched with the bearing opening 21, the protection tool 1 is composed of a tool opening end 12 and a tool protection end 11, the tool protection end 11 is arranged in the bearing opening 21, the outer wall of the tool protection end 11 and the inner wall of the bearing opening 21 are mutually matched and attached, and the tool opening end 12 is arranged at the outer edge of the bearing opening 21.
In this scheme, protection frock 1 skids the graphite ring and the outer steel bushing of two fulcrum bearing that harm two fulcrum supporting component the inside because of the instrument when having avoided the assembly to effectual spare part consumption that has reduced practices thrift because of the time of doing over again extravagant, improves assembly quality and efficiency. Specifically, considering from the structural characteristics of the engine, the two fulcrums are arranged on the intermediary casing to form a closed cavity only with the two-fulcrum bearing opening, when the vent pipe inside the two fulcrums is arranged, an operator needs to stretch a tool into the central bevel gear box for operation, and the hand of the operator and the tool in the hand are very easy to contact with the graphite ring and the bearing outer ring on the two-fulcrum supporting component in the operation process due to the narrow operation space, so that the two-fulcrum graphite ring and the bearing outer ring are damaged, the rework repair of the two-fulcrum supporting component is caused, the repair assembly period is delayed, and resources are wasted.
When the tool is actually used, the using method of the tool comprises the following steps: a. installing a two-fulcrum supporting component 2 on the intermediary case, and fixing the two-fulcrum supporting component 2 on the installation edge of the intermediary case by using a nut; b. the protection tool 1 is arranged on an inner cavity of the bearing opening 21, and whether the tool is completely attached to the inner cavity or not is checked; c. screwing the screws of the two sections of the vent pipes in the inner cavity of the bearing opening 21 by using a spanner to meet the process requirement; d. and taking out the protection tool 1 to finish the assembly operation. In order to realize the preparation of the protection tool 1, the following steps are preferred: firstly, determining the shape and size parameters of the protection tool 1 according to the bearing opening 21, and after the protection tool 1 is determined, printing the protection tool 1 in a 3D printing mode.
Claims (3)
1. Aeroengine supporting component assembles protective structure, including supporting component (2), supporting component (2) include circular shape bearing opening (21), its characterized in that: the protection tool comprises a protection tool (1) matched with a bearing opening (21), wherein the protection tool (1) is composed of a tool opening end (12) and a tool protection end (11), the tool protection end (11) is arranged in the bearing opening (21), the outer wall of the tool protection end (11) and the inner wall of the bearing opening (21) are mutually matched and attached, and the tool opening end (12) is arranged at the outer edge of the bearing opening (21).
2. Use of a method for assembling a protective structure from an aircraft engine support assembly according to claim 1, characterized in that it comprises the following steps:
a. installing a two-fulcrum supporting component (2) on the intermediary case, and fixing the two-fulcrum supporting component (2) on the installation edge of the intermediary case by using a nut;
b. the protection tool (1) is arranged on an inner cavity of the bearing opening (21), and whether the tool is completely attached to the inner cavity or not is checked;
c. screwing screws of two sections of vent pipes in the inner cavity of the bearing opening (21) by using a spanner to meet the process requirement;
d. and taking out the protection tool (1) to finish the assembly operation.
3. A method for manufacturing an aircraft engine support assembly shielding structure according to claim 1, comprising the steps of: firstly, determining the shape and size parameters of the protection tool (1) according to the bearing opening (21), and after the protection tool (1) is determined, printing the protection tool (1) in a 3D printing mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210497844.6A CN114986443A (en) | 2022-05-09 | 2022-05-09 | Assembly protection structure of aero-engine support assembly, use method and preparation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210497844.6A CN114986443A (en) | 2022-05-09 | 2022-05-09 | Assembly protection structure of aero-engine support assembly, use method and preparation method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114986443A true CN114986443A (en) | 2022-09-02 |
Family
ID=83025967
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210497844.6A Pending CN114986443A (en) | 2022-05-09 | 2022-05-09 | Assembly protection structure of aero-engine support assembly, use method and preparation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114986443A (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013142419A (en) * | 2012-01-10 | 2013-07-22 | Jtekt Corp | Protective cover and vehicular rolling bearing device mounted with the same |
| CN203395028U (en) * | 2013-07-12 | 2014-01-15 | 浙江正大轴承有限公司 | End surface sealing bearing |
| CN104141700A (en) * | 2014-08-15 | 2014-11-12 | 洛阳轴研科技股份有限公司 | Auxiliary device and method for assembling double-column cylindrical roller bearing |
| CN207848235U (en) * | 2018-02-06 | 2018-09-11 | 泉州永春中大机械技术有限公司 | A kind of mining machinery split bearing |
| CN109622542A (en) * | 2018-12-06 | 2019-04-16 | 中国航发贵州黎阳航空动力有限公司 | Fanjet bearing case bearing insert processes protective device and method |
| CN210265551U (en) * | 2019-07-31 | 2020-04-07 | 北轴(洛阳)轴承制造有限公司 | Plastic protective sleeve capable of separating cylindrical bearing |
| CN210938276U (en) * | 2019-10-14 | 2020-07-07 | 江苏德纳精工轴承有限公司 | Centering shaft for supporting bearing inner ring during super-finishing |
| CN213013252U (en) * | 2020-07-14 | 2021-04-20 | 江阴市源仁纺织有限公司 | Yarn guide wheel for textile processing |
| CN213541102U (en) * | 2020-09-27 | 2021-06-25 | 湖州银轴智能装备有限公司 | Roller bearing end part combination structure |
| CN214331203U (en) * | 2021-03-17 | 2021-10-01 | 山东欧冶轴承有限公司 | Special self-aligning roller bearing for continuous casting machine |
| CN214518727U (en) * | 2021-03-01 | 2021-10-29 | 哈尔滨哈飞工业有限责任公司 | High-speed wire rod machine bevel gear case shafting assembly auxiliary fixtures |
-
2022
- 2022-05-09 CN CN202210497844.6A patent/CN114986443A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013142419A (en) * | 2012-01-10 | 2013-07-22 | Jtekt Corp | Protective cover and vehicular rolling bearing device mounted with the same |
| CN203395028U (en) * | 2013-07-12 | 2014-01-15 | 浙江正大轴承有限公司 | End surface sealing bearing |
| CN104141700A (en) * | 2014-08-15 | 2014-11-12 | 洛阳轴研科技股份有限公司 | Auxiliary device and method for assembling double-column cylindrical roller bearing |
| CN207848235U (en) * | 2018-02-06 | 2018-09-11 | 泉州永春中大机械技术有限公司 | A kind of mining machinery split bearing |
| CN109622542A (en) * | 2018-12-06 | 2019-04-16 | 中国航发贵州黎阳航空动力有限公司 | Fanjet bearing case bearing insert processes protective device and method |
| CN210265551U (en) * | 2019-07-31 | 2020-04-07 | 北轴(洛阳)轴承制造有限公司 | Plastic protective sleeve capable of separating cylindrical bearing |
| CN210938276U (en) * | 2019-10-14 | 2020-07-07 | 江苏德纳精工轴承有限公司 | Centering shaft for supporting bearing inner ring during super-finishing |
| CN213013252U (en) * | 2020-07-14 | 2021-04-20 | 江阴市源仁纺织有限公司 | Yarn guide wheel for textile processing |
| CN213541102U (en) * | 2020-09-27 | 2021-06-25 | 湖州银轴智能装备有限公司 | Roller bearing end part combination structure |
| CN214518727U (en) * | 2021-03-01 | 2021-10-29 | 哈尔滨哈飞工业有限责任公司 | High-speed wire rod machine bevel gear case shafting assembly auxiliary fixtures |
| CN214331203U (en) * | 2021-03-17 | 2021-10-01 | 山东欧冶轴承有限公司 | Special self-aligning roller bearing for continuous casting machine |
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