CN108049921B - A kind of assembly method of aero-engine low-pressure turbine shaft-disk component - Google Patents
A kind of assembly method of aero-engine low-pressure turbine shaft-disk component Download PDFInfo
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- CN108049921B CN108049921B CN201711206654.XA CN201711206654A CN108049921B CN 108049921 B CN108049921 B CN 108049921B CN 201711206654 A CN201711206654 A CN 201711206654A CN 108049921 B CN108049921 B CN 108049921B
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- turbine
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- 238000000034 method Methods 0.000 title claims abstract description 32
- 238000003032 molecular docking Methods 0.000 claims abstract description 23
- 238000009434 installation Methods 0.000 claims abstract description 22
- 210000000078 claw Anatomy 0.000 claims description 26
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 17
- 230000008569 process Effects 0.000 claims description 10
- 230000008859 change Effects 0.000 claims description 6
- 230000007659 motor function Effects 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 6
- 230000008901 benefit Effects 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 241000283725 Bos Species 0.000 description 1
- 241000196324 Embryophyta Species 0.000 description 1
- 240000007594 Oryza sativa Species 0.000 description 1
- 235000007164 Oryza sativa Nutrition 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of assembly methods of aero-engine low-pressure turbine shaft-disk component, comprising the following steps: workpiece installation；The adjustment of turbine wheel shaft pose；Turbine wheel shaft docking prepackage；Indexing type tightening system is fed to front operation area；Tightening axle is tightened；Indexing type tightening system is retracted.The present invention uses low-pressure turbine shaft-disk axis level assembly method, convenient for the accurate adjustment of position and posture is carried out to the biggish low-pressure turbine shaft of length in docking operation, it realizes turbine wheel shaft correctly fitting closely to heart positioning calibration and end face with respect to terminal pad, improves Butt Assembling precision.Present invention application turbine wheel shaft pose adjusts platform, mechanically carries out quantitative pose adjustment to low-pressure turbine shaft, instead of empirical formulas methods such as traditional artificial operation suspenders, avoids artificial trial assembly repeatedly and correction, improves docking efficiency, meets component assembly coherence request.The present invention uses indexing type tightening system, reduces craftsmanship's requirement and labor intensity, and efficiency is tightened in raising.
Description
Technical field
The invention belongs to Automated assembly technical field, in particular to a kind of aero-engine low-pressure turbine shaft-disk component
Assembly method.
Background technique
In aero-engine, low-pressure turbine shaft passes through flange at tail end structure and low-pressure turbo unit body end portion terminal pad phase
The power transmitting of Low Pressure Turbine Rotor is realized in assembly.Outer as suffered by Low Pressure Turbine Rotor to carry greatly, axis-disk component is withstood up to
The driving torque of tens of tons of axial force and tens of thousands of oxen rice, and its coupling part belongs to abrupt change of cross-section key rapid wear position, therefore
Axis-disk component assembly performance is the important factor in order of engine operational reliability.
In low-pressure turbine shaft-disk component assembling process, low-pressure turbine shaft-disk need to carry out relative pose adjustment and calibration,
The two is fastened to docking cooperation is carried out along axial direction after just eventually by the circumferential bolt tightening way that is evenly distributed with.It is domestic at present main
Will be using artificial vertical assembly method, i.e. low-pressure turbine shaft-disk axis is mounting means along the vertical direction: by volume weight
It measures biggish low-pressure turbo unit body and carries out the vertical fixed installation of axis along the vertical direction, by turbine wheel shaft by the way of handling
It is moved to center position, reduces the height of suspender, by continuous trial assembly and calibration, it is opposite to complete turbine wheel shaft in the vertical direction
The docking of terminal pad is finally tightened to along the uniformly distributed bolt group of circumference.Above-mentioned assembly method has the disadvantage that
(1) be difficult to ensure merging precision: length is that about 2m specification turbine wheel shaft axial dimension is excessive, causes it in the way of vertical handling
Microspur is displaced alignment difficulties, influences component to heart precision；It is difficult to realize its posture by mechanical mechanism in vertical turbine wheel shaft
Adjustment cannot achieve the flexible assembly requirement for adapting to pairing contact surface type surface error, it is difficult to guarantee that contact surface is correctly close
Fitting；Worker's experience is largely relied in assembling process, causes each component assembly consistency poor；(2) tightening system feeding is difficult: by
Keep component whole height big in vertical assembly method, tightening system is difficult to the feeding of axial manner from top to bottom, and applies mechanical
Arm as the mode of tightening axle sideway feed mechanism there are at high cost, rigidity is low and low efficiency the problems such as；(3) subsequent general assembly operation
Difficult: the Low Pressure Turbine Rotor after assembly is in vertical, in including the subsequent engines total coating process such as itself and core engine assembly,
It is required that Low Pressure Turbine Rotor axis remains horizontal position, for big-block engine Low Pressure Turbine Rotor from vertically to level
Switching process performance difficulty, to plant and equipment require it is harsh；(4) existing assembly method operating efficiency is low: largely relying on people
Work carries out trial assembly and correction repeatedly, causes assembly efficiency low；The vertical assembly method of Low Pressure Turbine Rotor and subsequent multiple general assemblies
Axis horizontal requirement in process is inconsistent, influences whole assembly efficiency.
Summary of the invention
To solve the above-mentioned problems of the prior art, the present invention will provide a kind of aero-engine low-pressure turbine shaft-disk
The assembly method of component meets component high-precision docking and requires, has the characteristics that tightening system without interference feeding, facilitate carry out general assembly
Technique connects, and realizes aero-engine low-pressure turbine shaft-disk high-quality and high-efficiency assembly.
The technical scheme is that a kind of assembly method of aero-engine low-pressure turbine shaft-disk component, using aviation
Engine low-pressure turbine shaft-disk component assembly device is assembled, specifically includes the following steps:
A, workpiece is installed: turbine unit body is fixedly installed on turbine fixture, is horizontally oriented connection disk axis；Whirlpool
Wheel shaft is mounted on the turbine wheel shaft support rod I for being in vertical station and turbine wheel shaft support rod II, and turbine wheel shaft axis is made to be in water
Square to；
B, turbine wheel shaft pose adjusts: adjusting platform horizontal plane swinging motion, vertical plane pitching movement reality by turbine wheel shaft pose
Existing turbine wheel shaft adjusts platform horizontal shifting by turbine wheel shaft pose, vertical lifting realizes whirlpool with respect to the end face collimation of terminal pad
Concentric alignment of the wheel shaft with respect to terminal pad；
C, turbine wheel shaft docking prepackage: driving turbine wheel shaft is completed docking of the turbine wheel shaft with respect to terminal pad, is carried out along axial feed
Connect bolt prepackage；
D, indexing type tightening system is fed to front operation area: indexing type tightening system is fed to front end from turbine shaft tail end
During tightening operation area, tightening axle installs bearing and passes through turbine wheel shaft, and turbine wheel shaft support rod I, turbine wheel shaft support rod II successively change
Indexing is to avoid indexing type tightening system；Specifically, turbine wheel shaft support rod I rotates 90 ° to horizontal station, and turbine wheel shaft is by turbine
Bolt offer support is pre-installed at axis support rod II and terminal pad, indexing type tightening system is moved to turbine wheel shaft support rod I and turbine
Between axis support rod II, turbine wheel shaft support rod I rotates backward 90 ° and is back to vertical station, and turbine wheel shaft support rod II rotates 90 ° extremely
Horizontal station, turbine wheel shaft provide support by turbine wheel shaft support rod I and terminal pad prepackage bolt, and indexing type tightening system is moved to
Tighten workspace in turbine wheel shaft front end；
E, tightening axle is tightened: the single or multiple tightening axles on tightening axle installation bearing be indexed into it is corresponding tighten at bolt into
Row is tightened, and tightening axle is tightened by tightening sequential process requirements and be indexed into next or one group of bolt, and so on up to complete
Work is tightened at whole bolts；
F, indexing type tightening system is retracted: indexing type tightening system is retracted into tail end mistake from turbine wheel shaft front end tightening operation area
Cheng Zhong, turbine wheel shaft support rod I change station to avoid indexing type tightening system；Specifically, turbine wheel shaft support rod I rotates 90 ° extremely
Horizontal station, by terminal pad, fastening bolt provides support to turbine wheel shaft, and indexing type tightening system is retracted into turbine shaft tail end.
Further, aero-engine low-pressure turbine shaft-disk component assembly device, including turbine fixture, whirlpool
Wheel shaft posture adjustment docking system, indexing type tightening system and lathe bed.
The turbine fixture includes prelocalization seat and rear positioning seat, and the leading edge and rear of turbine unit body are respectively by preceding fixed
Position seat and the limit of rear positioning seat, keep the axis of turbine unit body terminal pad in the horizontal direction, turbine unit body passes through bolt
It is affixed with prelocalization seat；
The turbine wheel shaft posture adjustment docking system is located in the middle part of lathe bed, by roller type claw I, turbine wheel shaft support rod I, support
Rod bearing I, roller type claw II, turbine wheel shaft support rod II, support rod bearing I I, turbine wheel shaft pose adjust platform, turbine wheel shaft pose
Adjust platform pedestal and linear rail system I composition；
The turbine wheel shaft support rod I is installed on turbine wheel shaft pose by support rod bearing I and adjusts platform tail end, realizes to prop up
Strut bearing I is that axle center carries out 90 ° of indexings, that is, has horizontal station and vertical station；
The turbine wheel shaft support rod II by support rod bearing I I be installed on turbine wheel shaft pose adjust platform front end, realize with
Support rod bearing I I is that axle center carries out 90 ° of indexings, that is, has horizontal station and vertical station；
The upper end turbine wheel shaft support rod I is equipped with claw I, realizes to turbine shaft tail end clamping；
The upper end turbine wheel shaft support rod II is equipped with claw II, realizes to turbine wheel shaft front-loading；
When the turbine wheel shaft support rod I and turbine wheel shaft support rod II is in vertical station together, the centering axis of claw I and
The centering axis of claw II is coaxial in the horizontal plane, realizes that turbine wheel shaft axis is in the installation of horizontality；
The turbine wheel shaft pose adjustment platform is located above turbine wheel shaft pose adjustment platform pedestal, has opposite turbine wheel shaft pose
Adjust the motor functions such as the rotation of platform pedestal horizontal plane, vertical plane pitching, horizontal shifting and vertical lifting；
The turbine wheel shaft pose adjustment platform pedestal is mounted on lathe bed by linear rail system I, linear rail system I
The direction of motion it is parallel with the axis of turbine unit body terminal pad, realize turbine wheel shaft with respect to terminal pad axial feed docking transport
It is dynamic；
The indexing type tightening system includes planer-type mobile station, tightening axle installation bearing and tightening axle；
The planer-type mobile station bottom end is mounted on lathe bed by linear rail system II, linear rail system II's
The direction of motion is parallel with the axis of turbine unit body terminal pad, realizes that tightening system is fed to front end from turbine shaft tail end and works
Area, and tighten work and be back to tail end from turbine wheel shaft front end after the completion；
When the planer-type mobile station is displaced along linear rail system II, makes somebody a mere figurehead partially pass through in water below
The turbine wheel shaft support rod I of flat station and turbine wheel shaft support rod II in horizontal station；
The tightening axle installation bearing is located above planer-type mobile station, rotation axis and turbine unit body terminal pad
Axis coaxle, when planer-type mobile station is displaced along linear rail system II, tightening axle install bearing inner ring pass through whirlpool
Wheel shaft；
The tightening axle is installed on tightening axle installation bearing, and quantity can be one or more, and tightening axle is by twisting
Mandrel installation axle is held be indexed into and tighten station after, respective bolt is tightened in realization.
Compared with prior art, the invention has the advantages that:
1, the present invention use low-pressure turbine shaft-disk axis level assembly method, be convenient in docking operation to length compared with
Big low-pressure turbine shaft carries out the accurate adjustment of position and posture, realizes that turbine wheel shaft positions calibration and end to the heart with respect to terminal pad
Face correctly fits closely, and improves Butt Assembling precision.
2, the present invention adjusts platform using turbine wheel shaft pose, mechanically carries out quantitative pose tune to low-pressure turbine shaft
It is whole, instead of empirical formulas methods such as traditional artificial operation suspenders, artificial trial assembly repeatedly and correction are avoided, docking efficiency is improved, meets
Component assembles coherence request.
3, the present invention successively avoids mode using planer-type mobile station cooperation turbine wheel shaft support rod I, turbine wheel shaft support rod II,
Solve the problems, such as movement interference during tightening system feeding, planer-type mobile station can ensure that tightening system has high rigidity characteristic.
4, the present invention uses indexing type tightening system, is rotated single or multiple tightening axles to station, is removed from
Manual operation tightens utensil process, reduces craftsmanship's requirement and labor intensity, and efficiency is tightened in raising.
5, the Low Pressure Turbine Rotor that present invention assembly is completed is in horizontal state, is suitable for subsequent engine total coating process
In to assembly axis horizontal requirement, facilitate the efficient connecting of subsequent technique.
6, the present invention is suitable for plurality of specifications model aero-engine low-pressure turbine shaft-disk component assembly, especially to substantially
The rotor assembly of the vertical assembly difficulty of product model has advantage, and the method for the present invention is equally applicable to other similar structures forms
Axis-disk component assembly, has compared with high scalability.
Detailed description of the invention
Fig. 1 is the schematic diagram of workpiece installation.
Fig. 2 is the schematic diagram of turbine wheel shaft pose adjustment.
Fig. 3 is the schematic diagram of turbine wheel shaft docking prepackage.
Fig. 4 is the schematic diagram that indexing type tightening system is fed to the front operation area first step.
Fig. 5 is the schematic diagram that indexing type tightening system is fed to front operation area second step and tightening axle is tightened.
The schematic diagram that Fig. 6 indexing type tightening system is retracted.
In figure: 1, turbine unit body, 2, turbine fixture, 3, terminal pad, 4, turbine wheel shaft, 5, claw I, 6, turbine wheel shaft support rod
I, 7, claw II, 8, turbine wheel shaft support rod II, 9, turbine wheel shaft pose adjust platform, 10, turbine wheel shaft pose adjust platform pedestal, 11, straight
Line guide track system I, 12, indexing type tightening system, 13, tightening axle installation bearing, 14, support rod bearing I, 15, planer-type movement
Platform, 16, linear rail system II, 17, support rod bearing I I, 18, tightening axle, 19, prelocalization seat, 20, rear positioning seat, 21, bed
Body.
Specific embodiment
A specific embodiment of the invention is described in detail below in conjunction with technical solution and attached drawing.
A kind of aero-engine low-pressure turbine shaft-disk component assembly method, as shown in figures 1 to 6, comprising the following steps:
(1) workpiece is installed: as shown in Figure 1, turbine unit body 1 is fixedly installed on turbine fixture 2,3 axis of terminal pad
It is horizontally oriented；4 tail end of turbine wheel shaft is mounted on the turbine wheel shaft support rod I6 in vertical station by claw I5, the other end
End is mounted on the turbine wheel shaft support rod II8 in vertical station by claw II7, and 4 axis of turbine wheel shaft is horizontally oriented；
(2) 4 pose of turbine wheel shaft adjusts: as shown in Fig. 2, being positioned by the connection for observing and measuring turbine wheel shaft 4 and terminal pad 3
The faces parallel deviation and axle center deviation of contact surface carry out turbine wheel shaft pose and adjust 9 motion work of platform, pass through turbine wheel shaft pose
Adjust 9 horizontal plane rotation of platform (B shaft), end face parallel school of the turbine wheel shaft 4 with respect to terminal pad 3 is realized in vertical plane pitching (A shaft)
Standard adjusts the horizontal shifting (Y linear axis) of platform 9 by turbine wheel shaft pose, vertical lifting (Z linear axis) realizes that turbine wheel shaft 4 is opposite
The concentric alignment of terminal pad 3；
(3) docking of turbine wheel shaft 4 prepackage: as shown in figure 3, driving turbine wheel shaft pose adjustment platform pedestal 10 is along linear rail system
Docking of the turbine wheel shaft 4 with respect to terminal pad 3 is completed in I11 feed motion (X linear axis), is attached bolt prepackage；
(4) indexing type tightening system 12 is fed to front operation area: as illustrated in figures 4-5, indexing type tightening system 12 is from whirlpool
4 tail end of wheel shaft is fed to during the tightening operation area of front end, and tightening axle installs bearing 13 and passes through turbine wheel shaft 4, turbine wheel shaft support rod
I6, turbine wheel shaft support rod II8 change station successively to avoid indexing type tightening system 12；Specifically, claw I5 unclamps, turbine wheel shaft
Support rod I6 is around 14 90 ° of the indexing of support rod bearing I to horizontal station, and turbine wheel shaft 4 is by turbine wheel shaft support rod II8 and terminal pad 3
It pre-installs bolt and support is provided, planer-type mobile station 15 is along linear rail system II16 displacement (X linear axis) to turbine wheel shaft support rod
Between I6 and turbine wheel shaft support rod II8, turbine wheel shaft support rod I6 is back to vertical work for 90 ° around 14 reverse indexing of support rod bearing I
Position, claw I5 are clamped；Claw II7 unclamps, and turbine wheel shaft support rod II8 is around 90 ° of support rod bearing I I17 indexing to horizontal station, whirlpool
Wheel shaft 4 pre-installs bolt by turbine wheel shaft support rod I6 and terminal pad 3 and provides support, and planer-type mobile station 15 is along linear rail system
II16 is displaced (X linear axis) and tightens workspace to 4 front end of turbine wheel shaft；
(5) 18 indexing type operation of tightening axle: as shown in figure 5, being installed on 15 upper end tightening axle installation axle of planer-type mobile station
Single or multiple tightening axles 18 indexable (C shaft) to corresponding tighten held on 13 is tightened at bolt, and tightening axle installs bearing
13 driving tightening axles 18 are tightened by sequential process indexable (C shaft) to next or one group of bolt is tightened, and so on it is straight
Work is tightened to whole bolts are completed.
(6) indexing type tightening system 12 is retracted: as shown in fig. 6, indexing type tightening system 12 tightens work from 4 front end of turbine wheel shaft
Industry area is retracted into tail end process, and turbine wheel shaft support rod I6 changes station to avoid indexing type tightening system 12；Specifically, claw
I5 unclamps, and turbine wheel shaft support rod I6 rotates 90 ° to horizontal station around support rod bearing I 14, turbine wheel shaft 4 by terminal pad 3 tightly
Fixing bolt provides support, and planer-type mobile station 15 is retracted into 4 tail of turbine wheel shaft along linear rail system II16 displacement (X linear axis)
End.
Further, aero-engine low-pressure turbine shaft-disk component assembly device, including turbine fixture 2, whirlpool
Wheel shaft posture adjustment docking system, indexing type tightening system 12 and lathe bed 21.
The turbine fixture 2 includes prelocalization seat 19 and rear positioning seat 20, and the leading edge and rear of turbine unit body 1 are distinguished
It is limited by prelocalization seat 19 and rear positioning seat 20, keeps the axis of 1 terminal pad 3 of turbine unit body in the horizontal direction, turbine list
First body 1 is affixed by bolt and prelocalization seat 19；
The turbine wheel shaft posture adjustment docking system is located at the middle part of lathe bed 21, by roller type claw I5, turbine wheel shaft support rod I6,
Support rod bearing I 14, roller type claw II7, turbine wheel shaft support rod II8, support rod bearing I I17, turbine wheel shaft pose adjustment platform 9,
Turbine wheel shaft pose adjusts platform pedestal 10 and linear rail system I11 composition；
The turbine wheel shaft support rod I6 is installed on turbine wheel shaft pose by support rod bearing I 14 and adjusts 9 tail end of platform, realizes
It is that axle center carries out 90 ° of indexings with support rod bearing I 14, that is, there is horizontal station and vertical station；
The turbine wheel shaft support rod II8 is installed on turbine wheel shaft pose by support rod bearing I I17 and adjusts 9 front end of platform, real
90 ° of indexings now are carried out by axle center of support rod bearing I I17, that is, there is horizontal station and vertical station；
The upper end turbine wheel shaft support rod I6 is equipped with claw I5, realizes to 4 tail end clamping of turbine wheel shaft；
The upper end turbine wheel shaft support rod II8 is equipped with claw II7, realizes to 4 front-loading of turbine wheel shaft；
When the turbine wheel shaft support rod I6 and turbine wheel shaft support rod II8 are in vertical station together, the centering axis of claw I5
It is coaxial in the horizontal plane with the centering axis of claw II7, realize that 4 axis of turbine wheel shaft is in the installation of horizontality；
The turbine wheel shaft pose adjustment platform 9 is located at 10 top of turbine wheel shaft pose adjustment platform pedestal, has opposite turbine wheel shaft
Pose adjusts the motor functions such as the 10 horizontal plane rotation of platform pedestal, vertical plane pitching, horizontal shifting and vertical lifting；
The turbine wheel shaft pose adjustment platform pedestal 10 is mounted on lathe bed 21 by linear rail system I11, and straight line is led
The direction of motion of rail system I11 and 3 axis of terminal pad of turbine unit body 1 are parallel, realize axis of the turbine wheel shaft 4 with respect to terminal pad 3
To feeding docking movement；
The indexing type tightening system 12 includes planer-type mobile station 15, tightening axle installation bearing 13 and tightening axle 18；
15 bottom end of planer-type mobile station is mounted on lathe bed 21 by linear rail system II16, linear guide system
The direction of motion of system II16 is parallel with 3 axis of terminal pad of turbine unit body 1, realizes indexing type tightening system 12 from turbine wheel shaft 4
Tail end is fed to front end workspace, and tightens work and be back to tail end from 4 front end of turbine wheel shaft after the completion；
When the planer-type mobile station 15 is displaced along linear rail system II16, making somebody a mere figurehead part below be may pass through
Turbine wheel shaft support rod I6 in the horizontal station and turbine wheel shaft support rod II8 in horizontal station；
The tightening axle installation bearing 13 is located at 15 top of planer-type mobile station, rotation axis and turbine unit body 1
3 axis coaxle of terminal pad, when planer-type mobile station 15 is displaced along linear rail system II16, tightening axle install bearing 13
Inner ring may pass through turbine wheel shaft 4；
The tightening axle 18 is installed on tightening axle installation bearing 13, and quantity can be one or more, tightening axle 18
It is indexed by tightening axle installation bearing 13 after tightening station, respective bolt is tightened in realization.
The present invention is not limited to the present embodiment, any equivalent concepts within the technical scope of the present disclosure or changes
Become, is classified as protection scope of the present invention.
Claims (2)
1. a kind of assembly method of aero-engine low-pressure turbine shaft-disk component, it is characterised in that: use aero-engine low pressure
Turbine wheel shaft-disk component assembly device is assembled, specifically includes the following steps:
A, workpiece is installed: turbine unit body (1) is fixedly installed on turbine fixture (2), and terminal pad (3) axis is made to be in level side
To；Turbine wheel shaft (4) is mounted on the turbine wheel shaft support rod I(6 for being in vertical station) and turbine wheel shaft support rod II(8) on, make whirlpool
Wheel shaft (4) axis is horizontally oriented；
B, turbine wheel shaft (4) pose adjusts: adjusting platform (9) horizontal plane swinging motion, vertical plane pitching movement by turbine wheel shaft pose
Realize the end face collimation of turbine wheel shaft (4) with respect to terminal pad (3), by turbine wheel shaft pose adjustment platform (9) horizontal shifting, vertically
The concentric alignment of turbine wheel shaft (4) with respect to terminal pad (3) is realized in lifting；
C, turbine wheel shaft (4) docking prepackage: driving turbine wheel shaft (4) completes turbine wheel shaft (4) with respect to terminal pad (3) along axial feed
Docking is attached bolt prepackage；
D, indexing type tightening system (12) is fed to front operation area: indexing type tightening system (12) from turbine wheel shaft (4) tail end into
To during the tightening operation area of front end, tightening axle installs bearing (13) and passes through turbine wheel shaft (4), turbine wheel shaft support rod I(6), whirlpool
Wheel shaft support rod II(8) change station successively to avoid indexing type tightening system (12)；Specifically, turbine wheel shaft support rod I(6) turn
90 ° are moved to horizontal station, turbine wheel shaft (4) is by turbine wheel shaft support rod II(8) and terminal pad (3) prepackage bolt offer support, turn
Position formula tightening system (12) is moved to turbine wheel shaft support rod I(6) and turbine wheel shaft support rod II(8) between, turbine wheel shaft support rod I
(6) 90 ° are rotated backward and is back to vertical station, turbine wheel shaft support rod II(8) 90 ° of rotation is to horizontal station, and turbine wheel shaft (4) is by whirlpool
Wheel shaft support rod I(6) and terminal pad (3) at prepackage bolt support is provided, indexing type tightening system (12) is moved to turbine wheel shaft (4)
Tighten workspace in front end；
E, tightening axle (18) is tightened: the single or multiple tightening axles (18) in tightening axle installation bearing (13) are indexed into correspondence and tighten
It is tightened at bolt, tightening axle (18) is tightened by tightening sequential process requirement and be indexed into next or one group of bolt, with
This analogizes until completing whole bolts tightens work；
F, indexing type tightening system (12) is retracted: indexing type tightening system (12) is retracted from turbine wheel shaft (4) front end tightening operation area
Into tail end process, turbine wheel shaft support rod I(6) change station to avoid indexing type tightening system (12)；Specifically, turbine wheel shaft branch
Strut I(6) 90 ° are rotated to horizontal station, by terminal pad (3), fastening bolt provides support to turbine wheel shaft (4), and indexing type is tightened
System (12) is retracted into turbine wheel shaft (4) tail end.
2. a kind of assembly method of aero-engine low-pressure turbine shaft-disk component according to claim 1, feature exist
In: aero-engine low-pressure turbine shaft (4)-disk component assembly device, including turbine fixture (2), turbine wheel shaft posture adjustment
Docking system, indexing type tightening system (12) and lathe bed (21)；
The turbine fixture (2) includes prelocalization seat (19) and rear positioning seat (20), the leading edge and rear of turbine unit body (1)
It is limited respectively by prelocalization seat (19) and rear positioning seat (20), is maintained at the axis of the terminal pad (3) in turbine unit body (1)
Horizontal direction, turbine unit body (1) are affixed by bolt and prelocalization seat (19)；
The turbine wheel shaft posture adjustment docking system is located in the middle part of lathe bed (21), by claw I(5), turbine wheel shaft support rod I(6), support
Rod bearing I(14), claw II(7), turbine wheel shaft support rod II(8), support rod bearing I I(17), turbine wheel shaft pose adjustment platform (9),
Turbine wheel shaft pose adjusts platform pedestal (10) and linear rail system I(11) composition；
The turbine wheel shaft support rod I(6) turbine wheel shaft pose is installed on by support rod bearing I (14) adjusts platform (9) tail end, it is real
It is now that axle center carries out 90 ° of indexings with support rod bearing I (14), that is, there is horizontal station and vertical station；
The turbine wheel shaft support rod II(8) pass through support rod bearing I I(17) it is installed on turbine wheel shaft pose adjustment platform (9) front end,
Realize with support rod bearing I I(17) it is that axle center carries out 90 ° of indexings, that is, there is horizontal station and vertical station；
The turbine wheel shaft support rod I(6) upper end is equipped with claw I(5), it realizes to turbine wheel shaft (4) tail end clamping；
The turbine wheel shaft support rod II(8) upper end is equipped with claw II(7), it realizes to turbine wheel shaft (4) front-loading；
The turbine wheel shaft support rod I(6) and turbine wheel shaft support rod II(8) when being in vertical station together, claw I(5) centering
Axis and claw II(7) centering axis it is coaxial in the horizontal plane, realize that turbine wheel shaft (4) axis is in the installation of horizontality；
Turbine wheel shaft pose adjustment platform (9) is located above turbine wheel shaft pose adjustment platform pedestal (10), has opposite turbine wheel shaft
Pose adjusts platform pedestal (10) horizontal plane rotation, vertical plane pitching, horizontal shifting and vertical lifting motor function；
Turbine wheel shaft pose adjustment platform pedestal (10) passes through linear rail system I(11) it is mounted on lathe bed (21), straight line
Guide track system I(11) the direction of motion it is parallel with the axis of terminal pad (3) in turbine unit body (1), realize turbine wheel shaft (4) phase
Movement is docked to the axial feed of terminal pad (3)；
The indexing type tightening system (12) includes planer-type mobile station (15), tightening axle installation bearing (13) and tightening axle
(18)；
Planer-type mobile station (15) bottom end passes through linear rail system II(16) it is mounted on lathe bed (21), linear guide
System II(16) the direction of motion it is parallel with the axis of terminal pad (3) in turbine unit body (1), realize tightening system from turbine
Axis (4) tail end is fed to front end workspace, and tightens work and be back to tail end from turbine wheel shaft (4) front end after the completion；
When the planer-type mobile station (15) is displaced along linear rail system II(16), makes somebody a mere figurehead partially pass through place below
In the turbine wheel shaft support rod I(6 of horizontal station) and turbine wheel shaft support rod II(8 in horizontal station)；
Tightening axle installation bearing (13) is located above planer-type mobile station (15), rotation axis and turbine unit body
(1) axis coaxle of the terminal pad (3) in when planer-type mobile station (15) is displaced along linear rail system II(16), is twisted
The inner ring that mandrel installs bearing (13) passes through turbine wheel shaft (4)；
The tightening axle is installed in tightening axle installation bearing (13), and the quantity of tightening axle is one or more, tightening axle
(18) it is indexed by tightening axle installation bearing (13) after tightening station, respective bolt is tightened in realization.
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| CN201711206654.XA CN108049921B (en) | 2017-11-27 | 2017-11-27 | A kind of assembly method of aero-engine low-pressure turbine shaft-disk component |
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| CN108049921A CN108049921A (en) | 2018-05-18 |
| CN108049921B true CN108049921B (en) | 2019-07-16 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109048255B (en) * | 2018-09-04 | 2020-02-07 | 中国航发南方工业有限公司 | Aircraft engine simulation piece assembly quality |
| CN109339869B (en) * | 2018-11-30 | 2021-04-02 | 中国航发沈阳黎明航空发动机有限责任公司 | Aeroengine high-pressure turbine rotor centering device and use method thereof |
| CN112177692B (en) * | 2019-07-03 | 2022-12-27 | 中国航发商用航空发动机有限责任公司 | Assembling tool and assembling method for low-pressure turbine rotor |
| CN111975337B (en) * | 2020-06-30 | 2021-08-06 | 中国航发南方工业有限公司 | Assembly vehicle for high-speed dynamic balance assembly of power turbine |
| CN114161358A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | General assembly platform for test piece of compression part of aero-engine and adjusting method thereof |
| CN114166152B (en) * | 2021-11-11 | 2024-04-26 | 西北工业大学 | Automatic assembly centering measuring device for aero-engine and using method thereof |
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| DE10311996B4 (en) * | 2003-03-19 | 2005-02-24 | Mtu Friedrichshafen Gmbh | Arrangement of an exhaust gas turbocharger with a carrier housing |
| CN2875716Y (en) * | 2006-02-27 | 2007-03-07 | 徐州海伦哲工程机械有限公司 | Device of assembling composite casing bush |
| DE602006006452D1 (en) * | 2006-09-25 | 2009-06-04 | Siemens Ag | Turbine rotor with closure plates and corresponding assembly process |
| GB2478501B (en) * | 2008-12-18 | 2013-05-01 | Nelson Stud Welding Inc | Turbine wheel and shaft joining processes |
| CN201815851U (en) * | 2010-08-23 | 2011-05-04 | 青岛迈特动力部件有限公司 | Assembly tool for automobile crankshaft oil shifting disc |
| US8776347B2 (en) * | 2012-06-29 | 2014-07-15 | United Technologies Corporation | Tool for rotor assembly and disassembly |
| DE102014210297A1 (en) * | 2014-05-30 | 2015-12-03 | Lufthansa Technik Ag | Dismantling process for a gas turbine |
| CN206484253U (en) * | 2017-02-28 | 2017-09-12 | 中机中联工程有限公司 | Main shaft twists bolt device with speed increaser automatic butt and automatically |
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