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 PDF

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Publication number
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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wheel shaft
turbine wheel
support rod
turbine
tightening
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CN108049921A (en
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高航
周天一
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Dalian University of Technology
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Dalian University of Technology
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28Supporting or mounting arrangements, e.g. for turbine casing
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00Manufacture
    • F05D2230/60Assembly methods
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00Manufacture
    • F05D2230/60Assembly methods
    • F05D2230/64Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644Assembly 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

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

A kind of assembly method of aero-engine low-pressure turbine shaft-disk component
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.
CN201711206654.XA 2017-11-27 2017-11-27 A kind of assembly method of aero-engine low-pressure turbine shaft-disk component Active CN108049921B (en)

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