CN103790653B - Based on the planer-type aeroengine rotor assembly apparatus of gas magnetic composite support - Google Patents
Based on the planer-type aeroengine rotor assembly apparatus of gas magnetic composite support Download PDFInfo
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- CN103790653B CN103790653B CN201410052259.0A CN201410052259A CN103790653B CN 103790653 B CN103790653 B CN 103790653B CN 201410052259 A CN201410052259 A CN 201410052259A CN 103790653 B CN103790653 B CN 103790653B
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Abstract
Mechanical assembly technique is belonged to based on the planer-type aeroengine rotor assembly method of gas magnetic composite support and device.Its method of measurement and device close rotary axis system determination rotative benchmark based on gas magnetic knot; According to the angular positioning of photoelectric encoder determination turntable; Based on four gauge head measuring devices, extract the radial error of rotor radial mating face and the tilt error of axial mating face, obtaining this rotor affects weights to rotor coaxial degree after assembling; Respectively measure assembling needed for whole rotors, obtain each rotor on assembling after rotor coaxial degree affect weights; The weights of each rotor are carried out vector optimization, obtains the angle of assembling of each rotor.The present invention effectively can solve the low problem of coaxality after aeroengine rotor assembling, after there is rotor assembling coaxality high, reduce vibration, be easy to install, flexibility ratio is high, the feature of improving engine performance.
Description
Technical field
The invention belongs to mechanical assembly technique, relate generally to a kind of planer-type aeroengine rotor assembly apparatus based on gas magnetic composite support.
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 the quality of motor, performance and manufacturing efficiency.So the coaxality of installing rear rotor will be improved in assembly process as much as possible, 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, height and operating experience and the technical merit of whether stablizing the assembler that places one's entire reliance upon of assembly precision, lack a kind of method that high speed effectively instructs aeroengine rotor to assemble, and then raising efficiency of assembling, reduce aeroplane engine machine 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 (Systemandmethodforimprovingthedamagetoleranceofarotorass embly.European Patent Publication No: EP2525049A2), mainly through each sub-test system being obtained the stress signal of rotor each position, the signal that each subtense angle gathers is analyzed by main system, damage the impact of Parameter analysis on assembling from the appearance of each rotor, and then improve the assembling of aeroengine rotor.The method Problems existing is: the impact of geometric sense on assembling, on the impact of assembling, cannot be improved in the geometric sense aspect not analyzing rotor.
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 adopt dual-tree complex wavelet transform method to analyze to the impulse response signal of the aeroengine rotor of obtained multicarrier coupling, obtain the impulse response subsignal of the aeroengine rotor of eight single carriers; Finally average assembly performance index is extracted to the impulse response subsignal of the aeroengine rotor of obtained eight single carriers, if the average assembly performance desired value of gained is more than or equal to 10, then judge that the assembling of this aeroengine rotor is qualified, if the mean value of gained is less than 10, then judge defective, need to do over again rebuilding.The method Problems existing is: do not instruct aeroengine rotor assembling.
Luoxin Precision Parts (shanghai) Co., Ltd. proposes a kind of coaxality of measuring and equips (a kind of axiality measuring apparatus.Publication number: CN202024752U).This device comprises the transmission main shaft that a pair of being arranged on apparatus subject is rotated by lazy-tongs synchronization control, and this transmission main shaft the inner respectively correspondence is provided with measuring head and positioning reference plane; Above position, there is transducer probe assembly between described measuring head.The coaxality that it mainly solves existing precision parts, the measurement of beating.The method Problems existing is: the coaxality only measuring measured piece, does not solve the problem of the rear coaxality difference 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 is fixed on blade by sensor, finally measures engine rotor blade tip radial clearance.The method Problems existing is: do not consider that in rotor assembly process, axial attachment face is on the impact after rotor assembling.
The tested object of aeroengine assembling is stators and rotor, and under the condition that component processing precision meets the demands, final inspection is by installing the Determines after coordinating, and the index of evaluation mainly assembles the coaxality parameter of rear rotor.Engine revolution produces high pressure, and its rotor is made up of multiple single part combined, ideal during the dead in line of the turning axle of each parts and whole motor.High Rotation Speed speed during high-performance enginer work is greater than 10000rpm, single part axis or radial deflection will inevitably cause turbine disk misalignment engine rotation axis, very large centrifugal force can be produced in such a situa-tion, cause the imbalance of rotor turns, cause engine luggine, thus ensure that the coaxality after the assembling of each parts is the Focal point and difficult point installed.
A Model Mounting not using coaxality optimization method, the axis of all parts and radial due to machining accuracy restriction existence beat, eccentric, inclination equal error.If directly assembled randomly, just may form the bending situation being similar to " banana ", namely upper component have accumulated bias or the tilt error of all parts below, and beat overall after causing assembling is huge with inclination, 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 based on dial indicator.According to assembled in sequence motor from top to bottom, measure after assembling parts, guarantee that the entirety after at every turn increasing parts can meet the threshold condition of coaxality, and then another parts are upwards installed.Each all using previous parts as benchmark, the coaxality of final requirement entirety within the specific limits.The time of this method at substantial, and the possibility of doing over again is large, affects very much efficiency and the one-time success rate of installation, usually once successfully assembles needs 4 to 5 days.And because be not optimum assembling position, usually need dismounting 4 to 5 times, also need workman to assemble with rich experiences, each assembling all needs experience hot working and cold working.So current aerospace engine assembly method installation efficiency is low, not easily install, and after assembling, coaxality is poor, affects engine performance.
Summary of the invention
For the deficiency that above-mentioned prior art exists, a kind of planer-type aeroengine rotor assembly apparatus based on gas magnetic composite support is proposed, the object assemble the low problem of rear coaxality to solve aeroengine rotor, after reaching rotor assembling, coaxality is high, reduction is vibrated, be easy to installation, flexibility ratio is high, improved engine performance.
The object of the present invention is achieved like this:
A kind of structure of the planer-type aeroengine rotor assembly apparatus based on gas magnetic composite support is that rotary axis system is nested on base central position, described rotary axis system is by rotary main shaft, worktable, platen on turning axle, turning axle pressing disc, photoelectric encoder, photoelectric encoder code-disc, permanent magnet and coil are formed, described worktable to be 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, photoelectric encoder code-disc is nested on turning axle pressing disc outer shroud, photoelectric encoder fits over base central position lower inside admittedly, and it is outside to be positioned at photoelectric encoder code-disc, permanent magnet is enclosed within rotary main shaft outer shroud, and be fixed on turning axle pressing disc upper end portion, coil is enclosed within rotary main shaft outer shroud, and be fixed on base interior, 5-10cm place above permanent magnet, aligning adjusts the worktable that inclines to be configured on rotary axis system central position, and three-jaw fluid-pressure chuck is configured in aligning tune and inclines on worktable central position, gate left column and gate right column are symmetrically distributed in the both sides of rotary axis system and are packed on pedestal, and gate crossbeam two ends and gate left column upper end and gate right column upper end are connected, removablely successively from top to bottom on gate left column be adjustably set with upper left mast link and lower-left mast link, the horizontal measuring staff horizontal nest in upper left is on the mast link of upper left, the horizontal measuring staff of upper sensor adaptor and upper left is connected, and upper axial capacitive transducer and upper sensor adaptor are connected, the horizontal measuring staff horizontal nest in lower-left is on the mast link of lower-left, and the horizontal measuring staff of lower sensor adaptor and lower-left is connected, and lower axial capacitive transducer and lower sensor adaptor are connected, removablely successively from top to bottom on gate right column be adjustably set with upper right mast link and bottom right mast link, the horizontal measuring staff horizontal nest of upper right is on upper right mast link, and upper radial capacitive transducer is connected with upper right transverse direction measuring staff, the horizontal measuring staff horizontal nest in bottom right is on the mast link of bottom right, and the horizontal measuring staff of lower radial capacitive transducer and bottom right is connected.
Compared with prior art, feature of the present invention is:
The present invention can obtain the coaxality weights of each rotor by the concentricity and perpendicularity measuring each rotor, again the coaxality weights of each rotor are carried out vector optimization, just can obtain instructing setting angle, save 40% installation time and expense, the once mounting success rate of 98%, measurable installation progress, improve engine stabilization, reduce engine luggine, save motor fuel consumption, reduce CO
2discharge, reduces engine noise and pollutes.
Accompanying drawing illustrates:
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-photoelectric encoder, 2f-photoelectric encoder code-disc, 2g-permanent magnet, 2h-coil, 3-aligning adjusts the worktable that inclines, 4-three-jaw fluid-pressure chuck, 5a-gate left column, 5b-gate right column, 5c-gate crossbeam, 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 of 6d-upper right, 7a-lower-left mast link, 7b-bottom right mast link, 7c-upper left mast link, 7d-upper right mast link, 8a-lower axial capacitive transducer, 8b-upper axial capacitive transducer, 9a-lower radial capacitive transducer, 9b-upper radial capacitive transducer, 10a-lower sensor adaptor, 10b-upper sensor adaptor.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail:
Based on a planer-type aeroengine rotor assembly apparatus for gas magnetic composite support, described method and apparatus is: three-jaw fluid-pressure chuck 4 is configured in aligning tune and inclines on worktable 3 central position.Gate left column 5a and gate right column 5b is symmetrically distributed in the both sides of rotary axis system 2 and is packed on pedestal 1, and gate crossbeam 5c two ends and gate left column 5a upper end and gate right column 5b upper end are connected.On gate left column 5a from top to bottom successively removable be adjustably set with upper left mast link 7c and lower-left mast link 7a, upper left horizontal measuring staff 6c horizontal nest is on the mast link 7c of upper left, upper sensor adaptor 10b and the horizontal measuring staff 6c in upper left is connected, and upper axial capacitive transducer 8b and upper sensor adaptor 10b is connected; Lower-left horizontal measuring staff 6a horizontal nest is on the mast link 7a of lower-left, and lower sensor adaptor 10a and the horizontal measuring staff 6a in lower-left is connected, and lower axial capacitive transducer 8a and lower sensor adaptor 10a is connected.On gate right column 5b from top to bottom successively removable be adjustably set with upper right mast link 7d and bottom right mast link 7b, upper right horizontal measuring staff 6d horizontal nest is on upper right mast link 7d, and upper radial capacitive transducer 9b and the horizontal measuring staff 6d of upper right is connected; Bottom right horizontal measuring staff 6b horizontal nest is on the mast link 7b of bottom right, and lower radial capacitive transducer 9a and the horizontal measuring staff 6b in bottom right is 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, photoelectric encoder 2e, photoelectric encoder code-disc 2f, permanent magnet 2g and coil 2h is formed, described worktable 2b to be 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, photoelectric encoder code-disc 2f is nested on turning axle pressing disc 2d outer shroud, photoelectric encoder 2e fits over pedestal 1 central position lower inside admittedly, and it is outside to be positioned at photoelectric encoder code-disc 2f, permanent magnet 2g is enclosed within rotary main shaft 2a outer shroud, and be fixed on turning axle pressing disc 2d upper end portion, coil 2h is enclosed within rotary main shaft 2a outer shroud, and it is inner to be fixed on pedestal 1, 5-10cm place above permanent magnet 2g, rotary axis system 2 drives measured rotor at the uniform velocity to rotate with the speed of 6 ~ 10r/min, lower axial capacitive transducer 8a carries out equal interval sampling on the axial datum clamp face of measured rotor, lower radial capacitive transducer 9a carries out equal interval sampling on the radial datum clamp face of measured rotor, sampling number should meet and often encloses 1000 ~ 2000 points, by the sampled data on the radial datum clamp face of measured rotor by Least Square Circle matching, assess offset, by the axial datum clamp face up-sampling data of measured rotor by least square plane matching, assess inclination amount, aligning adjusts the worktable 3 that inclines to be configured on rotary axis system 2 central position, according to size and the angle of offset, regulates aligning to adjust to incline worktable 3 until the size meeting radial reference face offset is within the scope of 0 ~ 3 μm, according to size and the angle of inclination amount, regulate aligning to adjust to incline worktable 3 until the size meeting axial reference level inclination amount is 0 ~ 2 " in scope, upper right mast link 7d is vertically nested in the upside of gate right column 5b, upper right horizontal measuring staff 6d horizontal nest is on upper right mast link 7d, upper radial capacitive transducer 9b and the horizontal measuring staff 6d of upper right is connected, the radial direction that upper radial capacitive transducer 9b measures measured rotor is installed and measured face, upper left mast link 7c is vertically nested in the upside of gate left column 5a, upper left horizontal measuring staff 6c horizontal nest is on the mast link 7c of upper left, upper axial capacitive transducer 8b and upper sensor adaptor 10b is connected, the axis that upper axial capacitive transducer 8b measures measured rotor installs and measures face, rotary axis system 2 at the uniform velocity rotates with the speed of 6 ~ 10r/min, and upper radial capacitive transducer 9b installs and measures equal interval sampling on face in the radial direction of measured rotor, and upper axial capacitive transducer 8b installs and measures equal interval sampling on face in the axis of measured rotor, sampling number should meet and often encloses 1000 ~ 2000 points, the data upper radial capacitive transducer 9b being installed and measured face up-sampling in the radial direction of measured rotor are by Least Square Circle matching and assess concentricity, the data upper axial capacitive transducer 8b being installed and measured face up-sampling in the axis of measured rotor are by least square plane matching and assess perpendicularity, combined axis is to the radius in the face of installing and measuring and this measured rotor and the height difference of finally assemble rotor, and obtaining this rotor affects weights to the rear rotor coaxial degree of assembling, respectively measure assembling needed for whole rotors, obtain each rotor on assembling after rotor coaxial degree affect weights, adopt genetic algorithm to carry out vector optimization the weights of each rotor, obtain the angle of assembling of each rotor, the calculation method affecting weights of rotor coaxial degree is:
in formula: C represents that measured rotor radial direction installs and measures the concentricity in face,
represent the radial eccentric angle installing and measuring the matching center of circle, face, H represents measured rotor and the height difference of finally assembling rotor, R represents the radius axially installing and measuring face, P represents that measured rotor axially installs and measures the perpendicularity in face, and θ represents the angle axially installing and measuring the fit Plane peak place in face.
Claims (1)
1. the planer-type aeroengine rotor assembly apparatus based on gas magnetic composite support, 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 (2c) on turning axle, turning axle pressing disc (2d), photoelectric encoder (2e), photoelectric encoder code-disc (2f), permanent magnet (2g) and coil (2h) are formed, described worktable (2b) is configured on platen on turning axle (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, photoelectric encoder code-disc (2f) is nested on turning axle pressing disc (2d) outer shroud, photoelectric encoder (2e) fits over pedestal (1) central position lower inside admittedly, and it is outside to be positioned at photoelectric encoder code-disc (2f), permanent magnet (2g) is enclosed within rotary main shaft (2a) outer shroud, and be fixed on turning axle pressing disc (2d) upper end portion, coil (2h) is enclosed within rotary main shaft (2a) outer shroud, and it is inner to be fixed on pedestal (1), 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 three-jaw fluid-pressure chuck (4) is configured in aligning tune and inclines on worktable (3) central position, gate left column (5a) and gate right column (5b) are symmetrically distributed in the both sides of rotary axis system (2) and are packed on pedestal (1), and gate crossbeam (5c) two ends and gate left column (5a) upper end and gate right column (5b) upper end are connected, removablely successively from top to bottom on gate left column (5a) be adjustably set with upper left mast link (7c) and lower-left mast link (7a), horizontal measuring staff (6c) horizontal nest in upper left is on upper left mast link (7c), upper sensor adaptor (10b) is connected with the horizontal measuring staff (6c) in upper left, and upper axial capacitive transducer (8b) and upper sensor adaptor (10b) are connected, horizontal measuring staff (6a) horizontal nest in lower-left is on lower-left mast link (7a), lower sensor adaptor (10a) is connected with the horizontal measuring staff (6a) in lower-left, and lower axial capacitive transducer (8a) and lower sensor adaptor (10a) are connected, removablely successively from top to bottom on gate right column (5b) be adjustably set with upper right mast link (7d) and bottom right mast link (7b), horizontal measuring staff (6d) horizontal nest of upper right is on upper right mast link (7d), and upper radial capacitive transducer (9b) is connected with the horizontal measuring staff (6d) of upper right, horizontal measuring staff (6b) horizontal nest in bottom right is on bottom right mast link (7b), and lower radial capacitive transducer (9a) is connected with the horizontal measuring staff (6b) in bottom right.
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103790649B (en) * | 2014-02-14 | 2015-12-09 | 哈尔滨工业大学 | The aeroengine rotor assembly apparatus of the two column structure of packaged type |
| 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 |
| 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 |
| 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 |
| 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 |
| CN112903155A (en) * | 2019-12-03 | 2021-06-04 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment assembly tensile stress measuring device based on energy dissipation |
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| 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 |
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