CN109648288A - A kind of aero-engine low-pressure turbine mounting device - Google Patents
A kind of aero-engine low-pressure turbine mounting device Download PDFInfo
- Publication number
- CN109648288A CN109648288A CN201811550866.4A CN201811550866A CN109648288A CN 109648288 A CN109648288 A CN 109648288A CN 201811550866 A CN201811550866 A CN 201811550866A CN 109648288 A CN109648288 A CN 109648288A
- Authority
- CN
- China
- Prior art keywords
- guide shaft
- engine
- pressure turbine
- low
- section
- Prior art date
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
- B23P19/02—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for connecting objects by press fit or for detaching same
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
Abstract
This application discloses a kind of aero-engine low-pressure turbine mounting devices comprising: guide shaft, guide shaft one end and low-pressure turbine shaft are relatively fixed；Group section, group section is set to the other end of guide shaft, angularly fixed by connector；Centring means, centring means are fixed with rotor, and centring sleeve is equipped between centring means and guide shaft, and for being overlapped guide shaft axis with engine axis, centring sleeve and guide shaft can relatively move on engine axis；Ejection device is drawn, drawing ejection device includes the rotation section with guide shaft axial restraint and the mobile section that is threadedly engaged with centring means, axial restraint and is relatively rotatable to each other between rotation section and mobile section；Anti-twisted device, anti-twisted device are equipped with anti-twisted portion, and anti-twisted portion and mobile section cooperate the rotation for preventing mobile section, and anti-twisted device is relatively fixed to engine stator casing.The installation quality of four fulcrum roller of engine can be improved in the device of the application, improves the reliability of engine；Bearing damage is reduced, its service life is increased.
Description
Technical field
The application belongs to aero-engine mounting technology field, in particular to a kind of aero-engine low-pressure turbine installation dress
It sets.
Background technique
As shown in Figure 1, aero-engine includes usually fan 100, Middle casing 200,300 and of core engine along air flow direction
Low-pressure turbine 400, wherein fan 100, core engine 300 and low-pressure turbine 400 are rotating member, need to support it.
Currently, being usually that low pressure rotor uses 0-2-1 supporting form for the fulcrum layout of aero-engine, i.e. low pressure turns
Sub- front end is without fulcrum roller, and intermediate 2 fulcrum rollers (bearing is arranged in fulcrum Z1, Z2), (axis is arranged in fulcrum Z5 to the fulcrum of rear end 1
Hold), high pressure rotor uses the supporting form of 1 (bearing is arranged in fulcrum Z3) -0-1 (bearing is arranged in fulcrum Z4).Wherein, fulcrum Z4
Bearing is negative intermediary's stick roller bearing of clearance (roller and outer ring be interference fitted), between HP&LP Rotor, bearing internal external ring
It is belonging respectively to low-pressure turbo unit body and core engine, final assembly is completed while the installation of low-pressure turbo unit body.
Currently, being low-pressure turbine shaft 401 with bearing inner ring and roller linear insertion for dress/point method of low-pressure turbine
Outer race is extracted by straight line in outer ring.However for the intershaft bearing of negative clearance, in the whole process of single dress point
In, inevitable generation linear slide friction is caused bearing to scratch damage by roller with the specific angular position of outer ring, is damaged
Coefficient of friction increases afterwards, accelerates the abrasion in subsequent sliding process, roller diameter is caused to become smaller, and straight line flute mark occurs in outer ring surface,
The service life of bearing is reduced, simultaneously because changing the radial internal clearance of bearing to endanger the work belt of rotor.
Summary of the invention
There is provided a kind of aero-engine low-pressure turbine mounting devices for the purpose of the application, to solve any of the above-described ask
Topic.
The technical solution of the application is: a kind of aero-engine low-pressure turbine mounting device comprising: guide shaft, it is described to lead
Axis one end and low-pressure turbine shaft are relatively fixed；Group section, the group section is set to the other end of guide shaft, angular by connector
It is fixed；Centring means, the centring means are fixed with rotor, and centring sleeve is equipped between centring means and guide shaft, are led for making
Axis axis is overlapped with engine axis, and the centring sleeve and guide shaft can relatively move on engine axis；Draw ejection device, institute
Stating and drawing ejection device includes the rotation section with guide shaft axial restraint and the mobile section that is threadedly engaged with centring means, the rotation section with
It axial restraint and is relatively rotatable to each other between mobile section；Anti-twisted device, the anti-twisted device be equipped with anti-twisted portion, the anti-twisted portion with
The mobile section cooperates the rotation for preventing the mobile section, and the anti-twisted device is relatively fixed to engine stator casing.
Further, further includes: turn stator stationary fixture, it is described turn stator stationary fixture respectively with the rotor of low-pressure turbine
With the relatively fixed rotor for making low-pressure turbine of stator and the coincidence of stator axis and axial restraint；Rear housing suspender, the rear machine
Casket suspender is fixed on low-pressure turbine stator casing；Gravity-center adjustable suspender, the gravity-center adjustable suspender and rear housing suspender cooperate, and use
In the axial position for adjusting suspension centre the suspension centre is overlapped with the projection of low-pressure turbine center of gravity in the horizontal plane.
The installation quality of four fulcrum roller of engine can be improved in the device of the application, improves the reliability of engine；It reduces
Bearing damage increases its service life.
Detailed description of the invention
In order to illustrate more clearly of technical solution provided by the present application, attached drawing will be briefly described below.It is aobvious and easy
Insight, drawings discussed below are only some embodiments of the present application.
Fig. 1 is aero-engine structural schematic diagram.
Fig. 2 is that the mounting device of the application installs low-pressure turbine schematic diagram.
Fig. 3 is the mounting device structural schematic diagram of the application.
Fig. 4 is the mounting device side view of the application.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.
Damage is caused to solve current aerospace engine low-pressure turbine installation method to four fulcrum rollers, reduces bearing use
The problem of service life, this application provides a kind of aero-engine low-pressure turbines that can effectively reduce in installation process to damage of the bearing
Mounting device.
It in the installation and rotation of low-pressure turbine is pacified by the aero-engine low-pressure turbine of the application shown in Fig. 2 to Fig. 4
Assembling device is realized, while crane and torque wrench being cooperated to realize.
The aero-engine low-pressure turbine mounting device guide shaft 5 of the application, centring means 4, draws 3 and of ejection device at group section 2
Anti-twisted device 1.Guide shaft 5 is fixed on low-pressure turbine shaft 401, and axis is overlapped with low-pressure turbine axis, by low-pressure turbine shaft
Movement be transmitted to external engine.Centring means 4 and fan disk 101 are fixed, are connected by set tooth with fan shaft 102, internal diameter
Equipped with internal screw thread；It draws the rear portion outer diameter of ejection device 3 to be equipped with external screw thread and cooperatively forms screw-driven with centring means 4, filled with centering
The consistency being axially moved can be relatively rotated while guarantee by setting 4 front, and 3 front of ejection device is drawn to pass through Quick-release pin and 5 phase of guide shaft
Even；Anti-twisted device 1 is fixed on stator casing 6, and 3 posterior rotation of ejection device is drawn in limitation；Group section 2 passes through Quick-release pin and guide shaft 5
It is fixed, interface is provided for spanner or torque amplification.
It additionally include turning stator stationary fixture 8, rear housing suspender 9 and gravity-center adjustable suspender 7.Turn stator fixing tool 8
For realizing turn stator axial restraint, it is radially fixed at the same allow its around axis relatively rotate；Rear housing suspender 9 fixes low pressure whirlpool
Side is installed after wheel casing, and is connected with gravity-center adjustable suspender 7, by adjusting the hoisting point position of suspender, cooperation crane provides upward
Power F low whirlpool axis be adjusted to be overlapped with 300 axis of core engine.
The mounting device motion process of the application is as follows: rotating spanner drives spanner group section, is led by Quick-release pin drive
Axis；Guide shaft drives the rotation of push-pull device at fixed front by Quick-release pin, while low whirling being driven to rotate；Low whirlpool axis is driven by spline
Fan shaft rotates synchronously；Fan shaft passes through bolt driving fan disk；Centring means passes through fan shaft sleeve tooth and the company with fan disk
It connects and rotates synchronously；Due to drawing there is screw thread pair between ejection device and centring means, and the rear part angular position is anti-twisted arm and fixes,
Therefore it draws ejection device that will issue life in the collective effect of anti-twisted arm and centring means screw thread to move horizontally；It is fast because drawing ejection device to pass through
It unloads pin to fix with guide shaft, therefore guide shaft and low-pressure turbine will be driven to translate together, realize swivel feeding.
The application installs, in disassembly process in low-pressure turbine, when four fulcrum roller rollers are contacted with outer ring, makes low pressure whirlpool
Wheel is fed while rotating with four fulcrum inner ring, and the entire cylinder of four fulcrum roller rollers and outer ring is all uniform
Friction is participated in, to substantially shorten the Frictional Slipping distance of former frictional position, and then the degree of wear of former frictional position is reduced, mentions
The service life of high bearing.Application improves the installation quality of four fulcrum roller of engine, improves the reliability of engine；Reduce axis
Damage is held, its service life is increased.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (2)
1. a kind of aero-engine low-pressure turbine mounting device, which is characterized in that including
Guide shaft (5), described guide shaft (5) one end and low-pressure turbine shaft (401) are relatively fixed；
Group section (2), the group section (2) is set to the other end of guide shaft (5), angularly fixed by connector；
Centring means (4), the centring means (4) are fixed with rotor, and centering is equipped between centring means (4) and guide shaft (5)
Set, for being overlapped guide shaft axis with engine axis, the centring sleeve and guide shaft can relatively move on engine axis；
It draws ejection device (3), drawing ejection device (3) includes the rotation section (31) and and centring means with guide shaft (5) axial restraint
(4) mobile section (32) being threadedly engaged axial restraint and is relatively rotatable to each other between the rotation section (31) and mobile section (32)；
Anti-twisted device (1), the anti-twisted device (1) are equipped with anti-twisted portion (11), the anti-twisted portion (11) and the mobile section (32)
Cooperate the rotation for preventing the mobile section (32), the anti-twisted device (1) is relatively fixed to engine stator casing.
2. aero-engine low-pressure turbine mounting device as described in claim 1, which is characterized in that further include
Turn stator stationary fixture (8), described to turn stator stationary fixture (8) relatively fixed with the rotor of low-pressure turbine and stator respectively
So that the rotor and stator axis of low-pressure turbine are overlapped and axial restraint；
Rear housing suspender (9), the rear housing suspender (9) are fixed on low-pressure turbine stator casing (6)；
Gravity-center adjustable suspender (7), the gravity-center adjustable suspender (7) and rear housing suspender (9) cooperate, for adjusting the axial direction of suspension centre
Position is overlapped the suspension centre with the projection of low-pressure turbine center of gravity in the horizontal plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811550866.4A CN109648288B (en) | 2018-12-18 | 2018-12-18 | Aeroengine low pressure turbine installation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811550866.4A CN109648288B (en) | 2018-12-18 | 2018-12-18 | Aeroengine low pressure turbine installation device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109648288A true CN109648288A (en) | 2019-04-19 |
| CN109648288B CN109648288B (en) | 2021-03-12 |
Family
ID=66113326
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811550866.4A Active CN109648288B (en) | 2018-12-18 | 2018-12-18 | Aeroengine low pressure turbine installation device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109648288B (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111266861A (en) * | 2020-03-31 | 2020-06-12 | 中国航发动力股份有限公司 | Assembly fixture of low-pressure turbine of engine |
| CN111376016A (en) * | 2020-03-31 | 2020-07-07 | 中国航发动力股份有限公司 | Positioning and guiding tool for low-pressure turbine of engine |
| CN111408918A (en) * | 2020-03-31 | 2020-07-14 | 中国航发动力股份有限公司 | Traction tool for low-pressure turbine of engine |
| CN111761556A (en) * | 2020-07-06 | 2020-10-13 | 中国航发沈阳发动机研究所 | Air inlet casing disassembling tool |
| CN111775109A (en) * | 2020-05-29 | 2020-10-16 | 中国航发南方工业有限公司 | Mounting tool and method for sliding bearing |
| CN112378369A (en) * | 2020-12-01 | 2021-02-19 | 中国航发沈阳发动机研究所 | Electronic type aeroengine adjustable stator blade interstage angle measuring device |
| CN112548526A (en) * | 2020-12-02 | 2021-03-26 | 安徽江淮汽车集团股份有限公司 | Lifting appliance and knuckle press-mounting device |
| CN112935788A (en) * | 2019-12-10 | 2021-06-11 | 中国航发商用航空发动机有限责任公司 | Butt joint guiding device of unit body with long shaft and technological method |
| CN113580053A (en) * | 2021-08-19 | 2021-11-02 | 中国航发沈阳黎明航空发动机有限责任公司 | Engine turbine assembly horizontal assembling device and using method thereof |
| CN113858105A (en) * | 2021-09-24 | 2021-12-31 | 中国航发南方工业有限公司 | Aeroengine guiding assembly mechanism and assembly method |
| CN114714081A (en) * | 2022-04-19 | 2022-07-08 | 中国航发动力股份有限公司 | Tool and method for disassembling front bearing seat casing |
| CN117697692A (en) * | 2024-02-06 | 2024-03-15 | 成都中科翼能科技有限公司 | Special loading and unloading tool for gas turbine locking connection device |
| CN117697692B (en) * | 2024-02-06 | 2024-04-23 | 成都中科翼能科技有限公司 | Special loading and unloading tool for gas turbine locking connection device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103620185A (en) * | 2011-06-08 | 2014-03-05 | 三菱重工业株式会社 | Motor rotor structure for electric turbocharger, and method for installing same |
| US20160376927A1 (en) * | 2013-11-25 | 2016-12-29 | General Electric Company | System for positioning of equipment |
| US20170182643A1 (en) * | 2015-12-23 | 2017-06-29 | Airbus Operations (S.A.S.) | Method for aligning a first hole of a first part with a second hole of a second part and kit for its implementation |
| CN108080885A (en) * | 2017-12-07 | 2018-05-29 | 滨州博海精工机械有限公司 | Piston cold charge copper sheathing lathe |
| CN108098304A (en) * | 2018-01-29 | 2018-06-01 | 厦门攸信信息技术有限公司 | A kind of rotation press-in cam gear and rotation press-in workbench |
| US10125556B1 (en) * | 2013-07-02 | 2018-11-13 | Abe B Erdman, Jr. | Pipe fitting assembly apparatus |
-
2018
- 2018-12-18 CN CN201811550866.4A patent/CN109648288B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103620185A (en) * | 2011-06-08 | 2014-03-05 | 三菱重工业株式会社 | Motor rotor structure for electric turbocharger, and method for installing same |
| US10125556B1 (en) * | 2013-07-02 | 2018-11-13 | Abe B Erdman, Jr. | Pipe fitting assembly apparatus |
| US20160376927A1 (en) * | 2013-11-25 | 2016-12-29 | General Electric Company | System for positioning of equipment |
| US20170182643A1 (en) * | 2015-12-23 | 2017-06-29 | Airbus Operations (S.A.S.) | Method for aligning a first hole of a first part with a second hole of a second part and kit for its implementation |
| CN108080885A (en) * | 2017-12-07 | 2018-05-29 | 滨州博海精工机械有限公司 | Piston cold charge copper sheathing lathe |
| CN108098304A (en) * | 2018-01-29 | 2018-06-01 | 厦门攸信信息技术有限公司 | A kind of rotation press-in cam gear and rotation press-in workbench |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112935788A (en) * | 2019-12-10 | 2021-06-11 | 中国航发商用航空发动机有限责任公司 | Butt joint guiding device of unit body with long shaft and technological method |
| CN111376016B (en) * | 2020-03-31 | 2021-03-02 | 中国航发动力股份有限公司 | Positioning and guiding tool for low-pressure turbine of engine |
| CN111376016A (en) * | 2020-03-31 | 2020-07-07 | 中国航发动力股份有限公司 | Positioning and guiding tool for low-pressure turbine of engine |
| CN111408918A (en) * | 2020-03-31 | 2020-07-14 | 中国航发动力股份有限公司 | Traction tool for low-pressure turbine of engine |
| CN111266861A (en) * | 2020-03-31 | 2020-06-12 | 中国航发动力股份有限公司 | Assembly fixture of low-pressure turbine of engine |
| CN111266861B (en) * | 2020-03-31 | 2021-04-20 | 中国航发动力股份有限公司 | Assembly fixture of low-pressure turbine of engine |
| CN111775109A (en) * | 2020-05-29 | 2020-10-16 | 中国航发南方工业有限公司 | Mounting tool and method for sliding bearing |
| CN111761556A (en) * | 2020-07-06 | 2020-10-13 | 中国航发沈阳发动机研究所 | Air inlet casing disassembling tool |
| CN111761556B (en) * | 2020-07-06 | 2022-12-16 | 中国航发沈阳发动机研究所 | Air inlet casing disassembling tool |
| CN112378369A (en) * | 2020-12-01 | 2021-02-19 | 中国航发沈阳发动机研究所 | Electronic type aeroengine adjustable stator blade interstage angle measuring device |
| CN112548526A (en) * | 2020-12-02 | 2021-03-26 | 安徽江淮汽车集团股份有限公司 | Lifting appliance and knuckle press-mounting device |
| CN112548526B (en) * | 2020-12-02 | 2021-12-07 | 安徽江淮汽车集团股份有限公司 | Lifting appliance and knuckle press-mounting device |
| CN113580053A (en) * | 2021-08-19 | 2021-11-02 | 中国航发沈阳黎明航空发动机有限责任公司 | Engine turbine assembly horizontal assembling device and using method thereof |
| CN113858105A (en) * | 2021-09-24 | 2021-12-31 | 中国航发南方工业有限公司 | Aeroengine guiding assembly mechanism and assembly method |
| CN113858105B (en) * | 2021-09-24 | 2023-10-03 | 中国航发南方工业有限公司 | Aeroengine guiding assembly mechanism and assembly method |
| CN114714081A (en) * | 2022-04-19 | 2022-07-08 | 中国航发动力股份有限公司 | Tool and method for disassembling front bearing seat casing |
| CN117697692A (en) * | 2024-02-06 | 2024-03-15 | 成都中科翼能科技有限公司 | Special loading and unloading tool for gas turbine locking connection device |
| CN117697692B (en) * | 2024-02-06 | 2024-04-23 | 成都中科翼能科技有限公司 | Special loading and unloading tool for gas turbine locking connection device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109648288B (en) | 2021-03-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109648288A (en) | A kind of aero-engine low-pressure turbine mounting device | |
| CN104015161A (en) | Assembly and disassembly device for electric spindle bearing | |
| CN103953644A (en) | Radially adjustable tiltable pad bearing | |
| CN206241786U (en) | Interior single-unit sleeve grinder | |
| CN205898455U (en) | Radial loading assembly of wheel hub bearing testing machine | |
| CN103291766A (en) | Shaft end supporting device with convenient disassembly and assembly, and rubber roller rice huller having same | |
| CN206221505U (en) | High-speed magnetic levitation bearing pneumatic main shaft | |
| CN201201181Y (en) | Grinding head apparatus of chamfering machine | |
| CN109253260A (en) | A kind of oil sealing arrangement of the gas turbine with flag-shaped slot rotating ring | |
| CN202225070U (en) | Telescopic spindle rotary device and processing equipment | |
| CN103397913B (en) | A kind of low-pressure turbine band stator counterbalanced procedure | |
| WO2020125061A1 (en) | Electric spindle and motor | |
| JP2013141720A (en) | Chuck device for machine tool | |
| CN208713688U (en) | Detachable spindle assemblies and polishing machine | |
| KR101149015B1 (en) | Rotor turning apparatus | |
| CN208434347U (en) | Cotton picker takes off cotton disk regulating device | |
| CN205166562U (en) | Bent axle lapping machine | |
| CN205325351U (en) | Bent axle grinds mechanism | |
| CN205552020U (en) | A electronic centre frame for slender axles precision finishing | |
| CN205863395U (en) | A kind of large-scale half turntable antenna with high-precision attitude adjusting apparatus | |
| CN107336035A (en) | A kind of bearing inner race fixture of not easy damaged bearing inner race inner hole wall | |
| CN107745329A (en) | A kind of sphere grinder | |
| CN104525981B (en) | High-speed air floatation electro spindle | |
| CN218582100U (en) | Gap adjusting mechanism of magnetic suspension bearing testing machine | |
| CN108561578A (en) | A kind of sphere and its processing method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |