CN103790649A - Assembling method and device for aero-engine rotors of movable double-stand-column structure - Google Patents
Assembling method and device for aero-engine rotors of movable double-stand-column structure Download PDFInfo
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- CN103790649A CN103790649A CN201410052236.XA CN201410052236A CN103790649A CN 103790649 A CN103790649 A CN 103790649A CN 201410052236 A CN201410052236 A CN 201410052236A CN 103790649 A CN103790649 A CN 103790649A
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Abstract
The invention relates to an assembling method and device for aero-engine rotors of a movable double-stand-column structure, and belongs to mechanical assembly technologies. A measuring method includes the steps that a slewing datum is determined based on a gas-magnetic combination; the angle location of a turntable is determined according to an optical-electricity encoder; the radial-direction error of the radial-direction assembling face and the inclination error of the axial assembling face of one rotor are extracted based on a four-measuring-head measuring device to obtain the influence weight on rotor coaxiality after assembly by the rotor; all the rotors needed by assembly are measured respectively to obtain the influence weights on rotor coaxiality after assembly by all the rotors; vector optimization is performed on the weights of all the rotors to obtain assembling angles of all the rotors. The assembling method and device can effectively solve the problem that the coaxiality is low after the aero-engine rotors are assembled and have the advantages that the coaxiality is high after the aero-engine rotors are assembled, vibration is reduced, the rotors are easy to install, flexibility is high, and performance of the engine is improved.
Description
Technical field
The invention belongs to mechanical assembly technique, relate generally to aeroengine rotor assembly method and the device of the two column structures of a kind of packaged type.
Background technique
Aeroengine assembling is the final tache in aeroengine manufacture process, is also one of of paramount importance manufacture link.Under existing Aeroengine Design scheme and processing technique level conditions, the quality of assembling and working efficiency have material impact for quality, performance and the manufacturing efficiency of motor.So will improve as much as possible the coaxality of rotor after installing in assembly process, and then reduce the vibration of aeroengine, improve the performance of aeroengine.But, in reality is produced, the assembling of aeroengine is complete hand assembled, the height of assembly precision and whether stablize the assembler's that places one's entire reliance upon operating experience and technical merit, lack a kind of method that high speed effectively instructs aeroengine rotor assembling, and then raising efficiency of assembling, reduce aeroengine vibration, improve the performance of aeroengine.
Along with aeroengine assembling measuring technology more and more comes into one's own, aeroengine assembling measuring technology more and more comes into one's own, and becomes the focus of research.Increasing researcher has carried out deep discussion for aeroengine rotor, and Rools-Royce proposes a kind of scheme (System and method for improving the damage tolerance of a rotor assembly.European Patent Publication No: EP2525049A2), main by each sub-test system being obtained to the stress signal of the each position of rotor, main system is analyzed the signal of each subtense angle collection, damage the impact of parameter analysis on assembling from the appearance of each rotor, and then improved the assembling of aeroengine rotor.The problem that the method exists is: do not analyze the geometric sense aspect of rotor to the impact of assembling, cannot improve the impact of geometric sense on assembling.
Xi'an Communications University proposes a kind of method for testing assembly performance of rotor of aircraft engine (a kind of method for testing assembly performance of rotor of aircraft engine.Publication number: CN101799354A).First the method adopts vibration exciter exciting aeroengine rotor, utilizes vibration transducer and signal acquiring system software to obtain the impulse response signal of the aeroengine rotor of a multicarrier coupling; Then the impulse response signal of the aeroengine rotor to obtained a multicarrier coupling adopts dual-tree complex wavelet transform method to analyze, and obtains the impulse response subsignal of the aeroengine rotor of eight single carriers; Finally the impulse response subsignal of the aeroengine rotor to eight obtained single carriers extracts average assembly performance index, if the average assembly performance desired value of gained is more than or equal to 10, judge that this aeroengine rotor assembling is qualified, if the mean value of gained is less than 10, judge defective, the rebuilding of need to doing over again.The problem that the method exists is: to aeroengine rotor, assembling is not instructed.
Luoxin Precision Parts (shanghai) Co., Ltd. proposes a kind of coaxality equipment (a kind of axiality measuring apparatus of measuring.Publication number: CN202024752U).This device comprises a pair of transmission main shaft being rotated by lazy-tongs synchronization control being arranged on apparatus subject, and this transmission main shaft the inner respectively correspondence is provided with measuring head and positioning reference plane; Between described measuring head, top, position has transducer probe assembly.It mainly solves the coaxality of existing precision parts, the measurement of beating.The problem that the method exists is: only measure the coaxality of measured piece, do not solve the rear poor problem of coaxality of rotor assembling.
Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City proposes a kind of gap measuring method (non-contact measuring method for leaf apex radial clearance of engine rotor.Publication number: CN102175135A).The method adopts capacitance measurement technology, and measurement procedure is as follows, first assembles measuring system, calibration sensor, determines the relation between blade tip radial clearance and voltage, then sensor is fixed on blade, finally measures engine rotor blade tip radial clearance.The problem that the method exists is: do not consider in rotor assembly process the impact after axially attachment face is on rotor assembling.
The tested object of aeroengine assembling is stators and rotor, and under the condition meeting the demands in component processing precision, final inspection is by the Determines after coordinating is installed, and the index of evaluation is mainly the coaxality parameter of rotor after assembling.Engine revolution produces high pressure, and its rotor is made up of multiple single parts of combining, ideal when the turning axle of each parts and the dead in line of whole motor.High Rotation Speed speed when high-performance enginer work is greater than 10000rpm, single part axially or radial deflection will inevitably cause turbine disk misalignment engine rotation axis, under such condition, can produce very large centrifugal force, the imbalance that causes rotor to rotate, cause engine luggine, thereby guarantee that the coaxality after each parts assembling is the Focal point and difficult point of installing.
One does not use the Model Mounting of coaxality optimization method, axially and radially the beating because machining accuracy restriction exists of all parts, eccentric, inclination equal error.If directly assembled randomly, just may form the bending situation that is similar to " banana ", upper component has been accumulated bias or the tilt error of all parts below, causes the beat of the rear entirety of assembling and tilts huge, cause the non-constant of engine rotor coaxality, be difficult to meet usage requirement.
At present, domestic engine assembly still adopts traditional assembly method, tests manually as main take dial indicator.According to assembled in sequence motor from top to bottom, to assemble parts and measure afterwards, the entirety of guaranteeing at every turn to increase after parts can meet the threshold condition of coaxality, and then another parts are upwards installed.All using previous parts as benchmark, finally require overall coaxality within the specific limits at every turn.This method expends a large amount of time, and the possibility of doing over again is large, efficiency and one-time success rate that very impact is installed, and once successfully assembling needs 4 to 5 days conventionally.And, because be not optimum assembling position, conventionally need dismounting 4 to 5 times, also need workman to assemble with rich experiences, each assembling all needs to experience hot working and cold working.So current aeroengine assembly method installation efficiency is low, be difficult for installing, and after assembling, coaxality is poor, affects engine performance.
Summary of the invention
The deficiency existing for above-mentioned prior art, aeroengine rotor assembly method and the device of the two column structures of a kind of packaged type are proposed, to solve the low problem of coaxality after aeroengine rotor assembling, reach coaxality after rotor assembling high, reduce vibration, be easy to install, flexibility ratio is high, the object of improving engine performance.
The object of the present invention is achieved like this:
An aeroengine rotor assembly method for the two column structures of packaged type, this method of measurement step is as follows:
Measured rotor is positioned over to aligning to be adjusted on the worktable that inclines fixing; By the axial datum clamp face of the axial electric vortex sensor measuring measured rotor of the axial datum clamp face of measurement, incline for adjusting; Measure the radially radially datum clamp face of radially electric vortex sensor measuring of datum clamp face, for aligning; Revolution turntable adjusts the worktable that inclines to drive measured rotor at the uniform velocity to rotate with the speed of 6～10r/min through aligning, the axial current vortex sensor of measuring axial datum clamp face carries out equal interval sampling on the axial datum clamp face of measured rotor, measures the radially radially current vortex sensor of datum clamp face and carry out equal interval sampling on the radially datum clamp face of measured rotor; Sampling number should meet 1000～2000 points of every circle; Sampled data on the radially datum clamp face of measured rotor, by Least Square Circle matching, is assessed to offset, the axial datum clamp face up-sampling data of measured rotor, by least square plane matching, are assessed to inclination amount; According to the size of offset and angle, regulate aligning to adjust the aligning knob of the worktable that inclines; According to the size of inclination amount and angle, regulate aligning to adjust the tune of worktable of the inclining knob that inclines, until aligning adjusts size that the worktable that inclines meets radial reference face offset within the scope of 0～3 μ m, axially the size of reference level inclination amount is 0～2 " in scope; Measurement is is axially installed and measured to the face that axially installs and measures of the axial electric vortex sensor measuring measured rotor of face, measure the face that radially installs and measures of the radially electric vortex sensor measuring measured rotor of the face that radially installs and measures; Revolution turntable at the uniform velocity rotates with the speed of 6～10r/min, measure the axial current vortex sensor that axially installs and measures face measured rotor axially install and measure equal interval sampling on face, the radially current vortex sensor of measuring the face that radially installs and measures is is radially installing and measuring equal interval sampling on face respectively; Sampling number should meet 1000～2000 points of every circle; By measure the radially current vortex sensor that radially installs and measures face in the data of the face that radially the installs and measures up-sampling of measured rotor by Least Square Circle matching and assess concentricity; By measure the axial current vortex sensor that axially installs and measures face in the data of the face that axially the installs and measures up-sampling of measured rotor by least square plane matching and assess perpendicularity; Combined axis, to radius and this measured rotor and final height difference of assembling rotor of the face of installing and measuring, obtains this rotor to assembling the weights that affect of rear rotor coaxial degree; Measure respectively the required whole rotors of assembling, obtain each rotor to assembling the weights that affect of rear rotor coaxial degree; Adopt genetic algorithm to carry out vector optimization the weights of each rotor, obtain the angle of assembling of each rotor, the calculation method that affects weights of rotor coaxial degree is:
in formula: C represents that measured rotor radially installs and measures the concentricity of face,
represent radially to install and measure the eccentric angle in the face matching center of circle, H represents measured rotor and final height difference of assembling rotor, R represents the radius of the face that axially installs and measures, P represents that measured rotor axially installs and measures the perpendicularity of face, and θ represents the angle at the fit Plane peak place of the face that axially installs and measures.
The structure of the aeroengine rotor assembly apparatus of the two column structures of a kind of packaged type is that rotary axis system is nested on pedestal central position, described rotary axis system is by rotary main shaft, worktable, platen on turning axle, turning axle pressing disc, grating ruler reading head, grating scale, permanent magnet and coil form, described worktable is configured on turning axle on platen upper end portion, on turning axle, platen is configured on rotary main shaft upper end portion, rotary main shaft is configured on turning axle pressing disc upper end portion, grating scale is nested on turning axle pressing disc outer shroud, grating ruler reading head fits over pedestal central position lower inside admittedly, and be positioned at grating scale outside, permanent magnet is enclosed within on rotary main shaft outer shroud, and be fixed on turning axle pressing disc upper end portion, coil is enclosed within on rotary main shaft outer shroud, and be fixed on base interior, apart from 5-10cm place, permanent magnet top, aligning adjusts the worktable that inclines to be configured on rotary axis system central position, and four paws pneumatic chuck is configured in aligning tune and inclines on worktable central position, left movement guide rail and right motion guide rail are symmetrically distributed on the pedestal of rotary axis system both sides, and left column is arranged on left movement guide rail, and right column is arranged on right motion guide rail, , on left column, be set with to removable adjusting successively from top to bottom upper left mast link and lower-left mast link, the horizontal measuring staff level in upper left is nested on the mast link of upper left, the horizontal measuring staff in upper sensor adaptor and upper left is connected, and upper axial current vortex sensor and upper sensor adaptor are connected, the horizontal measuring staff level in lower-left is nested on the mast link of lower-left, and the horizontal measuring staff in lower sensor adaptor and lower-left is connected, and lower axial current vortex sensor and lower sensor adaptor are connected, on right column, be set with to removable adjusting successively from top to bottom upper right mast link and bottom right mast link, the horizontal measuring staff level in upper right is nested on the mast link of upper right, on radially the horizontal measuring staff of current vortex sensor and upper right be connected, the horizontal measuring staff level in bottom right is nested on the mast link of bottom right, under radially the horizontal measuring staff of current vortex sensor and bottom right be connected.
Compared with prior art, feature of the present invention is:
The present invention can obtain the coaxality weights of each rotor by measuring the concentricity of each rotor and perpendicularity, again the coaxality weights of each rotor are carried out to vector optimization, just can obtain instructing setting angle, save 40% installation time and expense, 98% once mounting success rate, measurable installation progress, improve engine stabilization, reduce engine luggine, save motor fuel consumption, reduce CO
2discharge, reduces engine noise and pollutes.
Accompanying drawing explanation:
Fig. 1 is four gauge head measuring device structural representations
Fig. 2 is rotary axis system structural representation
Piece number in figure: 1-pedestal, 2-rotary axis system, 2a-rotary main shaft, 2b worktable, platen on 2c-turning axle, 2d-turning axle pressing disc, 2e-grating ruler reading head, 2f-grating scale, 2g-permanent magnet, 2h-coil, 3-aligning is adjusted the worktable that inclines, 4-four paws pneumatic chuck, 5a-left column, 5b-right column, the horizontal measuring staff in 6a-lower-left, the horizontal measuring staff in 6b-bottom right, the horizontal measuring staff in 6c-upper left, the horizontal measuring staff in 6d-upper right, 7a-lower-left mast link, 7b-bottom right mast link, 7c-upper left mast link, 7d-upper right mast link, axial current vortex sensor under 8a-, the upper axial current vortex sensor of 8b-, current vortex sensor radially under 9a-, current vortex sensor radially on 9b-, 10a-lower sensor adaptor, 10b-upper sensor adaptor, 11a-left movement guide rail, the right motion guide rail of 11b-.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail:
Aeroengine rotor assembly method and the device of the two column structures of packaged type, described method and apparatus is: four paws pneumatic chuck 4 is configured in aligning tune and inclines on worktable 3 central positions.Left movement guide rail 11a and right motion guide rail 11b are symmetrically distributed on the pedestal 1 of rotary axis system 2 both sides, and it is upper that left column 5a is arranged on left movement guide rail 11a, and right column 5b is arranged on right motion guide rail 11b; On left column 5a, be set with to removable adjusting successively from top to bottom upper left mast link 7c and lower-left mast link 7a, upper left horizontal measuring staff 6c level is nested on the mast link 7c of upper left, the horizontal measuring staff 6c in upper sensor adaptor 10b and upper left is connected, and upper axial current vortex sensor 8b and upper sensor adaptor 10b are connected; It is upper that lower-left horizontal measuring staff 6a level is nested in lower-left mast link 7a, and the horizontal measuring staff 6a in lower sensor adaptor 10a and lower-left is connected, and lower axial current vortex sensor 8a and lower sensor adaptor 10a are connected.On right column 5b, be set with to removable adjusting successively from top to bottom upper right mast link 7d and bottom right mast link 7b, it is upper that upper right horizontal measuring staff 6d level is nested in upper right mast link 7d, on radially current vortex sensor 9b and the horizontal measuring staff 6d in upper right are connected; It is upper that bottom right horizontal measuring staff 6b level is nested in bottom right mast link 7b, under radially current vortex sensor 9a and the horizontal measuring staff 6b in bottom right are connected.Rotary axis system 2 is nested on pedestal 1 central position, described rotary axis system 2 is by rotary main shaft 2a, worktable 2b, platen 2c on turning axle, turning axle pressing disc 2d, grating ruler reading head 2e, grating scale 2f, permanent magnet 2g and coil 2h form, described worktable 2b is configured on turning axle on platen 2c upper end portion, on turning axle, platen 2c is configured on rotary main shaft 2a upper end portion, rotary main shaft 2a is configured on turning axle pressing disc 2d upper end portion, grating scale 2f is nested on turning axle pressing disc 2d outer shroud, grating ruler reading head 2e fits over pedestal 1 central position lower inside admittedly, and be positioned at grating scale 2f outside, permanent magnet 2g is enclosed within on rotary main shaft 2a outer shroud, and be fixed on turning axle pressing disc 2d upper end portion, coil 2h is enclosed within on rotary main shaft 2a outer shroud, and be fixed on pedestal 1 inside, apart from 5-10cm place, permanent magnet 2g top, rotary axis system 2 drives measured rotor at the uniform velocity to rotate with the speed of 6～10r/min, lower axial current vortex sensor 8a carries out equal interval sampling on the axial datum clamp face of measured rotor, under radially current vortex sensor 9a on the radially datum clamp face of measured rotor, carry out equal interval sampling, sampling number should meet 1000～2000 points of every circle, sampled data on the radially datum clamp face of measured rotor is passed through to Least Square Circle matching, assess offset, the axial datum clamp face up-sampling data of measured rotor are passed through to least square plane matching, assess inclination amount, aligning adjusts the worktable 3 that inclines to be configured on rotary axis system 2 central positions, according to the size of offset and angle, regulate aligning to adjust to incline worktable 3 until the size that meets radial reference face offset within the scope of 0～3 μ m, according to the size of inclination amount and angle, regulate aligning to adjust to incline worktable 3 until the size that meets axial reference level inclination amount 0～2 " in scope, upper right mast link 7d is vertically nested in the upside of right column 5b, upper right horizontal measuring staff 6d level is nested on the mast link 7d of upper right, on radially current vortex sensor 9b and the horizontal measuring staff 6d in upper right are connected, upper radially current vortex sensor 9b is measured to the face that radially installs and measures of measured rotor, upper left mast link 7c is vertically nested in the upside of left column 5a, upper left horizontal measuring staff 6c level is nested on the mast link 7c of upper left, upper axial current vortex sensor 8b and upper sensor adaptor 10b are connected, upper axial current vortex sensor 8b measures the face that axially installs and measures of measured rotor, rotary axis system 2 at the uniform velocity rotates with the speed of 6～10r/min, on radially current vortex sensor 9b measured rotor radially install and measure equal interval sampling on face, upper axial current vortex sensor 8b axially installs and measures equal interval sampling on face measured rotor, sampling number should meet 1000～2000 points of every circle, by upper radially current vortex sensor 9b in the data of the face that radially the installs and measures up-sampling of measured rotor by Least Square Circle matching and assess concentricity, by upper axial current vortex sensor 8b in the data of the face that axially the installs and measures up-sampling of measured rotor by least square plane matching and assess perpendicularity, combined axis, to radius and this measured rotor and final height difference of assembling rotor of the face of installing and measuring, obtains this rotor to assembling the weights that affect of rear rotor coaxial degree, measure respectively the required whole rotors of assembling, obtain each rotor to assembling the weights that affect of rear rotor coaxial degree, adopt genetic algorithm to carry out vector optimization the weights of each rotor, obtain the angle of assembling of each rotor, the calculation method that affects weights of rotor coaxial degree is:
in formula: C represents that measured rotor radially installs and measures the concentricity of face,
represent radially to install and measure the eccentric angle in the face matching center of circle, H represents measured rotor and final height difference of assembling rotor, R represents the radius of the face that axially installs and measures, P represents that measured rotor axially installs and measures the perpendicularity of face, and θ represents the angle at the fit Plane peak place of the face that axially installs and measures.
Claims (2)
1. an aeroengine rotor assembly method for the two column structures of packaged type, is characterized in that this method of measurement is: measured rotor is positioned over to aligning and adjusts on the worktable that inclines fixing; By the axial datum clamp face of the axial electric vortex sensor measuring measured rotor of the axial datum clamp face of measurement, incline for adjusting; Measure the radially radially datum clamp face of radially electric vortex sensor measuring of datum clamp face, for aligning; Revolution turntable adjusts the worktable that inclines to drive measured rotor at the uniform velocity to rotate with the speed of 6～10r/min through aligning, the axial current vortex sensor of measuring axial datum clamp face carries out equal interval sampling on the axial datum clamp face of measured rotor, measures the radially radially current vortex sensor of datum clamp face and carry out equal interval sampling on the radially datum clamp face of measured rotor; Sampling number should meet 1000～2000 points of every circle; Sampled data on the radially datum clamp face of measured rotor, by Least Square Circle matching, is assessed to offset, the axial datum clamp face up-sampling data of measured rotor, by least square plane matching, are assessed to inclination amount; According to the size of offset and angle, regulate aligning to adjust the aligning knob of the worktable that inclines; According to the size of inclination amount and angle, regulate aligning to adjust the tune of worktable of the inclining knob that inclines, until aligning adjusts size that the worktable that inclines meets radial reference face offset within the scope of 0～3 μ m, axially the size of reference level inclination amount is 0～2 " in scope; Measurement is is axially installed and measured to the face that axially installs and measures of the axial electric vortex sensor measuring measured rotor of face, measure the face that radially installs and measures of the radially electric vortex sensor measuring measured rotor of the face that radially installs and measures; Revolution turntable at the uniform velocity rotates with the speed of 6～10r/min, measure the axial current vortex sensor that axially installs and measures face measured rotor axially install and measure equal interval sampling on face, the radially current vortex sensor of measuring the face that radially installs and measures is is radially installing and measuring equal interval sampling on face respectively; Sampling number should meet 1000～2000 points of every circle; By measure the radially current vortex sensor that radially installs and measures face in the data of the face that radially the installs and measures up-sampling of measured rotor by Least Square Circle matching and assess concentricity; By measure the axial current vortex sensor that axially installs and measures face in the data of the face that axially the installs and measures up-sampling of measured rotor by least square plane matching and assess perpendicularity; Combined axis, to radius and this measured rotor and final height difference of assembling rotor of the face of installing and measuring, obtains this rotor to assembling the weights that affect of rear rotor coaxial degree; Measure respectively the required whole rotors of assembling, obtain each rotor to assembling the weights that affect of rear rotor coaxial degree; Adopt genetic algorithm to carry out vector optimization the weights of each rotor, obtain the angle of assembling of each rotor, the calculation method that affects weights of rotor coaxial degree is:
in formula: C represents that measured rotor radially installs and measures the concentricity of face,
represent radially to install and measure the eccentric angle in the face matching center of circle, H represents measured rotor and final height difference of assembling rotor, R represents the radius of the face that axially installs and measures, P represents that measured rotor axially installs and measures the perpendicularity of face, and θ represents the angle at the fit Plane peak place of the face that axially installs and measures.
2. the aeroengine rotor assembly apparatus of the two column structures of packaged type, it is characterized in that rotary axis system (2) is nested on pedestal (1) central position, described rotary axis system (2) is by rotary main shaft (2a), worktable (2b), platen on turning axle (2c), turning axle pressing disc (2d), grating ruler reading head (2e), grating scale (2f), permanent magnet (2g) and coil (2h) form, described worktable (2b) is configured on platen on turning axle (2c) upper end portion, platen on turning axle (2c) is configured on rotary main shaft (2a) upper end portion, rotary main shaft (2a) is configured on turning axle pressing disc (2d) upper end portion, grating scale (2f) is nested on turning axle pressing disc (2d) outer shroud, grating ruler reading head (2e) fits over pedestal (1) central position lower inside admittedly, and be positioned at grating scale (2f) outside, permanent magnet (2g) is enclosed within on rotary main shaft (2a) outer shroud, and be fixed on turning axle pressing disc (2d) upper end portion, coil (2h) is enclosed within on rotary main shaft (2a) outer shroud, and be fixed on pedestal (1) inside, apart from 5-10cm place, permanent magnet (2g) top, aligning adjusts the worktable (3) that inclines to be configured on rotary axis system (2) central position, and four paws pneumatic chuck (4) is configured in aligning tune and inclines on worktable (3) central position, left movement guide rail (11a) and right motion guide rail (11b) are symmetrically distributed on the pedestal (1) of rotary axis system (2) both sides, it is upper that left column (5a) is arranged on left movement guide rail (11a), and right column (5b) is arranged on right motion guide rail (11b), on left column (5a), removable adjusting ground is set with upper left mast link (7c) and lower-left mast link (7a) successively from top to bottom, the horizontal measuring staff in upper left (6c) level is nested on upper left mast link (7c), upper sensor adaptor (10b) is connected with upper left horizontal measuring staff (6c), and upper axial current vortex sensor (8b) is connected with upper sensor adaptor (10b), the horizontal measuring staff in lower-left (6a) level is nested on lower-left mast link (7a), lower sensor adaptor (10a) is connected with lower-left horizontal measuring staff (6a), and lower axial current vortex sensor (8a) is connected with lower sensor adaptor (10a), on right column (5b), removable adjusting ground is set with upper right mast link (7d) and bottom right mast link (7b) successively from top to bottom, it is upper that the horizontal measuring staff in upper right (6d) level is nested in upper right mast link (7d), on radially current vortex sensor (9b) be connected with upper right horizontal measuring staff (6d), it is upper that the horizontal measuring staff in bottom right (6b) level is nested in bottom right mast link (7b), under radially current vortex sensor (9a) be connected with bottom right horizontal measuring staff (6b).
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103790652A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Aircraft engine rotor air floating assembling method and device based on optical-electricity encoder angle measuring |
| CN103790653A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Method and device for assembling gantry type aero-engine rotors based on gas and magnetism combined support |
| CN103790650A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Method and device for assembling magnetic suspension type aero-engine rotors based on concentricity optimization |
| CN103790647A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Hydraulic capturing and clamping type aircraft engine rotor assembling method and device based on inductance sensing |
| CN103790646A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Aircraft engine rotor electric driving magnetic levitation assembling method and device based on optical-electricity encoder angle measuring |
| CN103806958A (en) * | 2014-02-14 | 2014-05-21 | 哈尔滨工业大学 | Hydraulic grasping clamping type aircraft engine rotor assembly method and device based on inductosyn |
| CN103790650B (en) * | 2014-02-14 | 2016-11-30 | 哈尔滨工业大学 | The electromagnetic levitation type aeroengine rotor assembling device optimized based on concentricity |
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| CN103790652A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Aircraft engine rotor air floating assembling method and device based on optical-electricity encoder angle measuring |
| CN103790647A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Hydraulic capturing and clamping type aircraft engine rotor assembling method and device based on inductance sensing |
| CN103790653A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Method and device for assembling gantry type aero-engine rotors based on gas and magnetism combined support |
| CN103790646A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Aircraft engine rotor electric driving magnetic levitation assembling method and device based on optical-electricity encoder angle measuring |
| CN103790650A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Method and device for assembling magnetic suspension type aero-engine rotors based on concentricity optimization |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103790652A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Aircraft engine rotor air floating assembling method and device based on optical-electricity encoder angle measuring |
| CN103790653A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Method and device for assembling gantry type aero-engine rotors based on gas and magnetism combined support |
| CN103790650A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Method and device for assembling magnetic suspension type aero-engine rotors based on concentricity optimization |
| CN103790647A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Hydraulic capturing and clamping type aircraft engine rotor assembling method and device based on inductance sensing |
| CN103790646A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Aircraft engine rotor electric driving magnetic levitation assembling method and device based on optical-electricity encoder angle measuring |
| CN103806958A (en) * | 2014-02-14 | 2014-05-21 | 哈尔滨工业大学 | Hydraulic grasping clamping type aircraft engine rotor assembly method and device based on inductosyn |
| CN103790646B (en) * | 2014-02-14 | 2015-12-09 | 哈尔滨工业大学 | Aeroengine rotor electric drive magnetic based on photoelectric encoder angle measurement floats assembly apparatus |
| CN103790647B (en) * | 2014-02-14 | 2015-12-30 | 哈尔滨工业大学 | Hydraulic pressure based on inductance sensing grabs cassette aeroengine rotor assembly apparatus |
| CN103790652B (en) * | 2014-02-14 | 2015-12-30 | 哈尔滨工业大学 | Based on the aeroengine rotor air supporting assembly apparatus of photoelectric encoder angle measurement |
| CN103790653B (en) * | 2014-02-14 | 2015-12-30 | 哈尔滨工业大学 | Based on the planer-type aeroengine rotor assembly apparatus of gas magnetic composite support |
| CN103806958B (en) * | 2014-02-14 | 2015-12-30 | 哈尔滨工业大学 | Hydraulic pressure based on inductosyn grabs cassette aeroengine rotor assembly apparatus |
| CN103790650B (en) * | 2014-02-14 | 2016-11-30 | 哈尔滨工业大学 | The electromagnetic levitation type aeroengine rotor assembling device optimized based on concentricity |
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