CN108049921A - 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
CN108049921A
CN108049921A CN201711206654.XA CN201711206654A CN108049921A CN 108049921 A CN108049921 A CN 108049921A CN 201711206654 A CN201711206654 A CN 201711206654A CN 108049921 A CN108049921 A CN 108049921A
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China
Prior art keywords
wheel shaft
turbine wheel
supporting rod
tightening
turbine
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CN201711206654.XA
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CN108049921B (en
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高航
周天
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 reel component, comprise the following steps:Workpiece is installed;Turbine wheel shaft pose adjusts;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 the assembly method of low-pressure turbine shaft disk axis level, it is adjusted convenient for larger to length low-pressure turbine shaft in docking operation into row position and the accurate of posture, it realizes that turbine wheel shaft positions calibration with respect to terminal pad to the heart and end face correctly fits closely, improves Butt Assembling precision.The present invention adjusts platform using turbine wheel shaft pose, and quantitative pose adjustment is mechanically carried out to low-pressure turbine shaft, instead of empirical formulas methods such as traditional artificial operation suspenders, avoids manually trial assembly repeatedly and correction, improves docking efficiency, meets component assembling coherence request.The present invention reduces craftsmanship's requirement and labor intensity, efficiency is tightened in raising using indexing type tightening system.

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, more particularly to a kind of aero-engine low-pressure turbine shaft-disk component Assembly method.
Background technology
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 Assembling realizes that the power of Low Pressure Turbine Rotor transfers.It is carried greatly due to outer suffered by Low Pressure Turbine Rotor, axis-disk component is withstood up to The driving torque of tens of tons of axial force and tens thousand of oxen rice, and its coupling part belongs to abrupt change of cross-section key rapid wear position, therefore The assembly performance of axis-disk component 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 carrying out docking cooperation vertically after just eventually by the circumferential bolt tightening way that is evenly distributed with.It is domestic at present main Artificial vertical assembly method is used, i.e. the axis of low-pressure turbine shaft-disk is mounting means vertically:By volume weight It measures larger low-pressure turbo unit body and carries out the vertical fixed installation of axis vertically, by turbine wheel shaft by the way of handling Center position is moved to, 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, finally to being tightened along the uniformly distributed bolt group of circumference.Above-mentioned assembly method has the following disadvantages: (1) it is difficult to ensure that merging precision:Length is that about 2m specification turbine wheel shaft axial dimensions are excessive, it is caused using the mode of vertical handling Microspur displacement alignment difficulties influence component to heart precision;It is difficult to realize its posture by mechanical mechanism in vertical turbine wheel shaft Adjustment can not realize the flexible assembly requirement for adapting to pairing contact surface type surface error, it is difficult to ensure that contact surface is correctly close Fitting;Worker's experience is largely relied in assembling process, causes each component assembling uniformity poor;(2) tightening system feeding is difficult:By Make component whole height big in vertical assembly method, tightening system is difficult to axial manner feeding from top to bottom, and applies machinery Arm has that of high cost, rigidity is low low with efficiency etc. as the mode of tightening axle sideway feed mechanism;(3) follow-up general assembly operation It is difficult:Low Pressure Turbine Rotor after assembling is in vertical, including it with core engine assembling etc. in subsequent engines total coating process, It is required that Low Pressure Turbine Rotor axis remains horizontal level, 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 rely on people Work carries out trial assembly and correction repeatedly, causes efficiency of assembling low;The vertical assembly method of Low Pressure Turbine Rotor and follow-up multiple general assemblies Axis horizontal requirement in process is inconsistent, influences whole efficiency of assembling.
The content 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 requirement, has the characteristics that tightening system without interference feeding, facilitate carry out general assembly Technique continues, and realizes aero-engine low-pressure turbine shaft-disk high-quality and high-efficiency assembling.
The technical scheme is that:A kind of assembly method of aero-engine low-pressure turbine shaft-disk component, using aviation The assembling device of engine low-pressure turbine shaft-disk component is assembled, and specifically includes 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 and is on the turbine wheel shaft supporting rod I and turbine wheel shaft supporting rod II of vertical station, and turbine wheel shaft axis is made to be in water Square to;
B, turbine wheel shaft pose adjusts:Platform horizontal plane swinging motion, vertical plane elevating movement reality are adjusted by turbine wheel shaft pose Existing turbine wheel shaft adjusts platform horizontal shifting, vertical lifting realizes whirlpool with respect to the end face collimation of terminal pad by turbine wheel shaft pose Wheel shaft is with respect to the concentric alignment of terminal pad;
C, turbine wheel shaft docking prepackage:Driving turbine wheel shaft is fed vertically, is completed docking of the turbine wheel shaft with respect to terminal pad, is carried out 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, through turbine wheel shaft, turbine wheel shaft supporting rod I, turbine wheel shaft supporting rod II change tightening axle installation bearing successively Indexing is to avoid indexing type tightening system;Specifically, turbine wheel shaft supporting rod I rotates 90 ° to horizontal station, and turbine wheel shaft is by turbine Bolt offer support is pre-installed at axis supporting rod II and terminal pad, indexing type tightening system is moved to turbine wheel shaft supporting rod I and turbine Between axis supporting rod II, turbine wheel shaft supporting rod I rotates backward 90 ° and is back to vertical station, and turbine wheel shaft supporting rod II rotates 90 ° extremely Horizontal station, turbine wheel shaft provide support by turbine wheel shaft supporting 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: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 requirement and be indexed into next or one group of bolt, and so on up to complete Work is tightened into 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 supporting rod I change station to avoid indexing type tightening system;Specifically, turbine wheel shaft supporting 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, the assembling device of aero-engine low-pressure turbine shaft-disk component, 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 trailing edge of turbine unit body are respectively by preceding fixed Position seat and rear positioning seat /V make the axis of turbine unit body terminal pad keep in the horizontal direction, and 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 supporting rod I, support Rod bearing I, roller type claw II, turbine wheel shaft supporting rod II, supporting rod bearing I I, turbine wheel shaft pose adjustment platform, turbine wheel shaft pose Adjust platform pedestal and linear rail system I compositions;
The turbine wheel shaft supporting rod I is installed on turbine wheel shaft pose by supporting rod bearing I and adjusts platform tail end, realizes to prop up Strut bearing I carries out 90 ° of indexings for axle center, i.e., with horizontal station and vertical station;
The turbine wheel shaft supporting rod II is installed on turbine wheel shaft pose by supporting rod bearing I I and adjusts platform front end, realize with Supporting rod bearing I I carries out 90 ° of indexings for axle center, i.e., with horizontal station and vertical station;
The turbine wheel shaft supporting rod I upper ends are equipped with claw I, realize to turbine shaft tail end clamping;
The turbine wheel shaft supporting rod II upper ends are equipped with claw II, realize to turbine wheel shaft front-loading;
When the turbine wheel shaft supporting rod I and turbine wheel shaft supporting 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 by linear rail system I on lathe bed, 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 is mounted on by linear rail system II on lathe bed, 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 work from turbine shaft tail end It area and tightens and is back to tail end from turbine wheel shaft front end after the completion of work;
The planer-type mobile station makes somebody a mere figurehead partially pass through in water below along during linear rail system II progress displacements The turbine wheel shaft supporting rod I of the flat station and turbine wheel shaft supporting 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, planer-type mobile station along linear rail system II carry out displacement when, tightening axle installation 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, realize and respective bolt tightened.
Compared with prior art, the invention has the advantages that:
1st, the present invention use low-pressure turbine shaft-disk axis level assembly method, convenient in docking operation to length compared with Big low-pressure turbine shaft realizes that turbine wheel shaft positions calibration and end with respect to terminal pad to the heart into the accurate adjustment of row position and posture Face correctly fits closely, and improves Butt Assembling precision.
2nd, the present invention adjusts platform using turbine wheel shaft pose, and quantitative pose tune is mechanically carried out to low-pressure turbine shaft It is whole, instead of empirical formulas methods such as traditional artificial operation suspenders, trial assembly repeatedly and correction are avoided manually, docking efficiency is improved, meets Component assembles coherence request.
3rd, the present invention avoids mode successively using planer-type mobile station cooperation turbine wheel shaft supporting rod I, turbine wheel shaft supporting rod II, Solve the problems, such as movement interference during tightening system feeding, planer-type mobile station can ensure that tightening system possesses high rigidity characteristic.
4th, the present invention is rotated to station single or multiple tightening axles, removed from using indexing type tightening system Manual operation tightens utensil process, reduces craftsmanship's requirement and labor intensity, and efficiency is tightened in raising.
5th, the Low Pressure Turbine Rotor that present invention assembling is completed is in horizontal state, suitable for subsequent engine total coating process In to assemble axis horizontal requirement, facilitate subsequent technique efficiently continue.
6th, the present invention is suitable for plurality of specifications model aero-engine low-pressure turbine shaft-disk component assembling, especially to substantially The rotor assembly of the vertical assembling difficulty of product model possesses advantage, and the method for the present invention is equally applicable to other similar structures forms Axis-disk component assembling, possesses compared with high scalability.
Description of the drawings
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 systems are retracted.
In figure:1st, turbine unit body, 2, turbine fixture, 3, terminal pad, 4, turbine wheel shaft, 5, claw I, 6, turbine wheel shaft supporting rod I, 7, claw II, 8, turbine wheel shaft supporting rod II, 9, turbine wheel shaft pose adjustment platform, 10, turbine wheel shaft pose adjustment platform pedestal, 11, straight Line guide track system I, 12, indexing type tightening system, 13, tightening axle installation bearing, 14, supporting rod bearing I, 15, planer-type movement Platform, 16, linear rail system II, 17, supporting rod bearing I I, 18, tightening axle, 19, prelocalization seat, 20, rear positioning seat, 21, bed Body.
Specific embodiment
Describe the specific embodiment of the present invention 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, comprises 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 by claw I5 on the turbine wheel shaft supporting rod I6 in vertical station, the other end End is mounted on by claw II7 on the turbine wheel shaft supporting rod II8 in vertical station, and 4 axis of turbine wheel shaft is horizontally oriented;
(2) 4 pose of turbine wheel shaft adjusts:As shown in Fig. 2, it is positioned by observing and measuring turbine wheel shaft 4 and the connection of terminal pad 3 The faces parallel deviation of contact surface and axle center deviation carry out turbine wheel shaft pose adjustment 9 motion work of platform, pass through turbine wheel shaft pose Adjust 9 horizontal plane rotation of platform (B shafts), end face parallel school of the turbine wheel shaft 4 with respect to terminal pad 3 is realized in vertical plane pitching (A shafts) 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 adjusts platform pedestal 10 along linear rail system Docking of the turbine wheel shaft 4 with respect to terminal pad 3 is completed in I11 feed motions (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 installation bearing 13 passes through turbine wheel shaft 4, turbine wheel shaft supporting rod I6, turbine wheel shaft supporting rod II8 change station to avoid indexing type tightening system 12 successively;Specifically, claw I5 unclamps, turbine wheel shaft Supporting rod I6 is around 14 90 ° of indexing of supporting rod bearing I extremely horizontal station, and turbine wheel shaft 4 is by turbine wheel shaft supporting 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 displacements (X linear axis) to turbine wheel shaft supporting rod Between I6 and turbine wheel shaft supporting rod II8, turbine wheel shaft supporting rod I6 is back to vertical work for 90 ° around 14 reverse indexing of supporting rod bearing I Position, claw I5 are clamped;Claw II7 unclamps, turbine wheel shaft supporting rod II8 around 90 ° of supporting rod bearing I I17 indexings to horizontal station, whirlpool Wheel shaft 4 pre-installs bolt by turbine wheel shaft supporting rod I6 and terminal pad 3 and provides support, and planer-type mobile station 15 is along linear rail system II16 displacements (X linear axis) tighten workspace to 4 front end of turbine wheel shaft;
(5) 18 indexing type operation of tightening axle:As shown in figure 5, it is installed on 15 upper end tightening axle installation axle of planer-type mobile station Single or multiple tightening axles 18 indexable (C shafts) to corresponding tighten held on 13 is tightened at bolt, tightening axle installation bearing 13 driving tightening axles 18 are tightened by sequential process indexable (C shafts) 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 supporting rod I6 changes station to avoid indexing type tightening system 12;Specifically, claw I5 unclamps, and turbine wheel shaft supporting rod I6 rotates 90 ° to horizontal stations around supporting 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 displacements (X linear axis) End.
Further, the assembling device of aero-engine low-pressure turbine shaft-disk component, 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 trailing edge of turbine unit body 1 are distinguished By 20 /V of prelocalization seat 19 and rear positioning seat, the axis of 1 terminal pad 3 of turbine unit body is made to keep 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 supporting rod I6, Supporting rod bearing I 14, roller type claw II7, turbine wheel shaft supporting rod II8, supporting rod bearing I I17, turbine wheel shaft pose adjustment platform 9, Turbine wheel shaft pose adjustment platform pedestal 10 and linear rail system I11 compositions;
The turbine wheel shaft supporting rod I6 is installed on turbine wheel shaft pose by supporting rod bearing I 14 and adjusts 9 tail end of platform, realizes 90 ° of indexings are carried out for axle center with supporting rod bearing I 14, i.e., with horizontal station and vertical station;
The turbine wheel shaft supporting rod II8 is installed on turbine wheel shaft pose by supporting rod bearing I I17 and adjusts 9 front end of platform, real 90 ° of indexings now are carried out by axle center of supporting rod bearing I I17, i.e., with horizontal station and vertical station;
The turbine wheel shaft supporting rod I6 upper ends are equipped with claw I5, realize to 4 tail end clamping of turbine wheel shaft;
The turbine wheel shaft supporting rod II8 upper ends are equipped with claw II7, realize to 4 front-loading of turbine wheel shaft;
When the turbine wheel shaft supporting rod I6 and turbine wheel shaft supporting 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 The motor functions such as the 10 horizontal plane rotation of pose adjustment platform pedestal, vertical plane pitching, horizontal shifting and vertical lifting;
The turbine wheel shaft pose adjustment platform pedestal 10 is mounted on by linear rail system I11 on lathe bed 21, and straight line is led The direction of motion of rail system I11 is parallel with 3 axis of terminal pad of turbine unit body 1, realizes 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 of planer-type mobile station is mounted on by linear rail system II16 on lathe bed 21, line slideway 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 is back to tail end from 4 front end of turbine wheel shaft after finishing;
The planer-type mobile station 15 is maked somebody a mere figurehead part and be may pass through below along during linear rail system II16 progress displacements Turbine wheel shaft supporting rod I6 in the horizontal station and turbine wheel shaft supporting 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, planer-type mobile station 15 along linear rail system II16 carry out displacement when, tightening axle installation 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, realizes and respective bolt is tightened.
The present invention is not limited to the present embodiment, any equivalent concepts in the technical scope of present disclosure or changes Become, be 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:Using aero-engine low pressure The assembling device of turbine wheel shaft-disk component is assembled, and specifically includes 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 and is on the turbine wheel shaft supporting rod I (6) and turbine wheel shaft supporting rod II (8) of vertical station, makes whirlpool Wheel shaft (4) axis is horizontally oriented;
B, turbine wheel shaft (4) pose adjusts:Platform (9) horizontal plane swinging motion, vertical plane elevating movement are adjusted by turbine wheel shaft pose Realize end face collimation of the turbine wheel shaft (4) with respect to terminal pad (3), by turbine wheel shaft pose adjustment platform (9) horizontal shifting, vertically Concentric alignment of the 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) is fed vertically, completes turbine wheel shaft (4) with respect to terminal pad (3) 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 installation bearing (13) is through turbine wheel shaft (4), turbine wheel shaft supporting rod I (6), whirlpool Wheel shaft supporting rod II (8) changes station to avoid indexing type tightening system (12) successively;Specifically, turbine wheel shaft supporting rod I (6) turns Dynamic 90 ° extremely horizontal station, turbine wheel shafts (4) provide support by turbine wheel shaft supporting rod II (8) and terminal pad (3) prepackage bolt, turn Position formula tightening system (12) is moved between turbine wheel shaft supporting rod I (6) and turbine wheel shaft supporting rod II (8), turbine wheel shaft supporting rod I (6) 90 ° are rotated backward and is back to vertical station, turbine wheel shaft supporting rod II (8) rotates 90 ° to horizontal station, and turbine wheel shaft (4) is by whirlpool Bolt offer support is pre-installed at wheel shaft supporting rod I (6) and terminal pad (3), indexing type tightening system (12) is moved to turbine wheel shaft (4) Tighten workspace in front end;
E, tightening axle (18) is tightened:Single or multiple tightening axles (18) on 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 supporting rod I (6) changes station to avoid indexing type tightening system (12);Specifically, turbine wheel shaft branch Strut I (6) rotates 90 ° to horizontal station, and 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:The assembling device of aero-engine low-pressure turbine shaft (the 4)-disk component, 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 trailing edge of turbine unit body (1) Respectively by prelocalization seat (19) and rear positioning seat (20) /V, the axis of turbine unit body (1) terminal pad (3) is made to be maintained at 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 roller type claw I (5), turbine wheel shaft supporting rod I (6), supporting rod bearing I (14), roller type claw II (7), turbine wheel shaft supporting rod II (8), supporting rod bearing I I (17), turbine wheel shaft Pose adjustment platform (9), turbine wheel shaft pose adjustment platform pedestal (10) and linear rail system I (11) compositions;
The turbine wheel shaft supporting rod I (6) is installed on turbine wheel shaft pose by supporting rod bearing I (14) and adjusts platform (9) tail end, real 90 ° of indexings are now carried out for axle center with supporting rod bearing I (14), i.e., with horizontal station and vertical station;
The turbine wheel shaft supporting rod II (8) is installed on turbine wheel shaft pose by supporting rod bearing I I (17) and adjusts platform (9) front end, It realizes and 90 ° of indexings is carried out for axle center with supporting rod bearing I I (17), i.e., with horizontal station and vertical station;
Described turbine wheel shaft supporting rod I (6) upper end is equipped with claw I (5), realizes to turbine wheel shaft (4) tail end clamping;
Described turbine wheel shaft supporting rod II (8) upper end is equipped with claw II (7), realizes to turbine wheel shaft (4) front-loading;
When the turbine wheel shaft supporting rod I (6) and turbine wheel shaft supporting rod II (8) is in vertical station together, the centering of claw I (5) The centering axis of axis and claw II (7) are coaxial in the horizontal plane, realize that turbine wheel shaft (4) axis is in the installation of horizontality;
The turbine wheel shaft pose adjustment platform (9) is located above turbine wheel shaft pose adjustment platform pedestal (10), has opposite turbine wheel shaft The motor functions such as pose adjustment platform pedestal (10) horizontal plane rotation, vertical plane pitching, horizontal shifting and vertical lifting;
The turbine wheel shaft pose adjustment platform pedestal (10) is mounted on by linear rail system I (11) on lathe bed (21), straight line The direction of motion of guide track system I (11) is parallel with the axis of turbine unit body (1) terminal pad (3), realizes that turbine wheel shaft (4) is opposite and connects Connect the axial feed docking movement of disk (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 is mounted on by linear rail system II (16) on lathe bed (21), line slideway The direction of motion of system II (16) is parallel with the axis of turbine unit body (1) terminal pad (3), realizes tightening system from turbine wheel shaft (4) tail end is fed to front end workspace and tightens work is back to tail end from turbine wheel shaft (4) front end after finishing;
The planer-type mobile station (15) makes somebody a mere figurehead partially pass through place below along during linear rail system II (16) progress displacements In the turbine wheel shaft supporting rod I (6) of horizontal station and turbine wheel shaft supporting rod II (8) in horizontal station;
The tightening axle installation bearing (13) is located above planer-type mobile station (15), rotation axis and turbine unit body (1) axis coaxle of terminal pad (3), planer-type mobile station (15) along linear rail system II (16) carry out displacement when, tightening axle The inner ring for installing bearing (13) passes through turbine wheel shaft (4);
The tightening axle is installed on tightening axle installation bearing (13), and quantity can be one or more, and tightening axle (18) is logical It crosses after tightening axle installation bearing (13) is indexed into and tightens station, realizes and respective bolt is tightened.
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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CN109339869A (en) * 2018-11-30 2019-02-15 中国航发沈阳黎明航空发动机有限责任公司 A kind of aero-engine High Pressure Turbine Rotor centring means and its application method
CN111975337A (en) * 2020-06-30 2020-11-24 中国航发南方工业有限公司 Assembly vehicle for high-speed dynamic balance assembly of power turbine

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CN109048255A (en) * 2018-09-04 2018-12-21 中国航发南方工业有限公司 Aero-engine simulating piece assembles device
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CN111975337A (en) * 2020-06-30 2020-11-24 中国航发南方工业有限公司 Assembly vehicle for high-speed dynamic balance assembly of power turbine

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