CN103776365B - Aero-engine multiaxis rotor assembling method and device based on radial and axial datum - Google Patents

Aero-engine multiaxis rotor assembling method and device based on radial and axial datum Download PDF

Info

Publication number
CN103776365B
CN103776365B CN201410051756.9A CN201410051756A CN103776365B CN 103776365 B CN103776365 B CN 103776365B CN 201410051756 A CN201410051756 A CN 201410051756A CN 103776365 B CN103776365 B CN 103776365B
Authority
CN
China
Prior art keywords
rotor
floating axle
radial
assembling
engine
Prior art date
Application number
CN201410051756.9A
Other languages
Chinese (zh)
Other versions
CN103776365A (en
Inventor
赵勃
谭久彬
王雷
Original Assignee
哈尔滨工业大学
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 哈尔滨工业大学 filed Critical 哈尔滨工业大学
Priority to CN201410051756.9A priority Critical patent/CN103776365B/en
Publication of CN103776365A publication Critical patent/CN103776365A/en
Application granted granted Critical
Publication of CN103776365B publication Critical patent/CN103776365B/en

Links

Abstract

The invention relates to an aero-engine multiaxis rotor assembling method and device based on a radial and axial datum and belongs to the mechanical assembling technology. A measuring method and a measuring device of the aero-engine multiaxis rotor assembling method and device determine the rotation datum based on a magnetic levitation rotation shaft system; an optical-electricity encoder is used for determining angle positioning of a rotation platform; based on a four-measuring-head measuring device, the radial errors of a rotor radial assembling face and the inclination errors of a rotor axial assembling face are extracted to obtain the influence weight of a rotor on the coaxial degree of the assembled rotor is obtained; all rotors needed by assembly are measured respectively to obtain the influence weights on the coaxial degrees of the assembled rotors by all the rotors are obtained; the weights of all the rotors receive vector optimization to obtain the assembly angles of all the rotors. According to the aero-engine multiaxis rotor assembling method and device based on the radial and axial datum, the problem that the coaxial degrees of rotors are low after the rotors of an aero-engine are assembled is solved. The aero-engine multiaxis rotor assembling method and device based on the radial and axial datum have the advantages of being capable of relieving vibration, high in flexibility and capable of improving the performance of the engine and the coaxial degrees of the rotors after being assembled are high. The aero-engine multiaxis rotor assembling device is easy to install.

Description

Based on radial aeromotor multiaxis rotor assembling method with axial benchmark and device
Technical field
The invention belongs to mechanical assembly technique, relate generally to a kind of based on radial aeromotor multiaxis rotor assembling method with axial benchmark and device.
Background technology
Aeromotor assembling is the final tache in aeromotor manufacture process, is also one of of paramount importance manufacture link.Under existing Aeroengine Design scheme and process technology level conditions, the quality of assembling and work efficiency have material impact for the quality of engine, performance and production efficiency.So the right alignment of installing rear rotor will be improved in assembling process as much as possible, and then reduce the vibration of aeromotor, improve the performance of aeromotor.But, in reality is produced, the assembling of aeromotor is complete manual setting, 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 aeromotor.
Along with aeromotor assembling measuring technology more and more comes into one's own, aeromotor assembling measuring technology more and more comes into one's own, and becomes the focus of research.Increasing researchist 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), mainly through each sub-test macro being obtained the stress signal of rotor each position, the signal that each subsystem 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 vibrator 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 right alignment 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 synchronizing linkage synchro 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 right alignment that it mainly solves existing precision component, the measurement of beating.The method Problems existing is: the right alignment only measuring measured piece, does not solve the problem of the rear right alignment 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 measuring process is as follows, first assembles measuring system, calibration sensor, determines the relation between blade tip radial play and voltage, then is fixed on blade by sensor, finally measures engine rotor blade tip radial play.The method Problems existing is: do not consider that in rotor assembling process, axial installed surface is on the impact after rotor assembling.
The tested object of aeromotor 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 right alignment parameter of rear rotor.Engine rotation produces high pressure, and its rotor is made up of multiple single part combined, ideal during the dead in line of the revolving shaft of each parts and whole engine.High Rotation Speed speed during high-performance enginer work is greater than 10000rpm, single part axis or radial beat 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 right alignment after the assembling of each parts is the Focal point and difficult point installed.
A Model Mounting not using right alignment optimization method, the axis of all parts and radial due to machining precision 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 droop error of all parts below, and beat overall after causing assembling is huge with inclination, cause the non-constant of engine rotor right alignment, be difficult to meet request for utilization.
At present, domestic engine assembly still adopts traditional assembly method, tests manually based on clock gauge.According to assembled in sequence engine from top to bottom, measure after assembling parts, guarantee that the entirety after at every turn increasing parts can meet the threshold condition of right alignment, and then another parts are upwards installed.Each all using previous parts as benchmark, the right alignment 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 effectiveness is low, not easily install, and after assembling, right alignment is poor, affects engine performance.
Summary of the invention
For the deficiency that above-mentioned prior art exists, propose a kind of based on radial aeromotor multiaxis rotor assembling method with axial benchmark and device, the object assemble the low problem of rear right alignment to solve aeroengine rotor, after reaching rotor assembling, right alignment 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 is that magnetic floating axle system is nested on base central position based on radial direction and the structure of the aeromotor multiaxis rotor assembling apparatus of axial benchmark, described magnetic floating axle system is by Magnetic suspension spindle, worktable, platen on magnetic floating axle, magnetic floating axle pressing disc, photoelectric encoder, photoelectric encoder code-disc, upper permanent magnet, lower permanent magnet, upper coil and lower coil are formed, described worktable to be configured on magnetic floating axle on platen upper end, on magnetic floating axle, platen is configured on Magnetic suspension spindle upper end, Magnetic suspension spindle is configured on magnetic floating axle pressing disc upper end, photoelectric encoder code-disc is nested on magnetic floating 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, upper permanent magnet is enclosed within Magnetic suspension spindle outer shroud, and be fixed on platen bottom on magnetic floating axle, reach the standard grade snare on Magnetic suspension spindle outer shroud, and be fixed on base interior, 5-10cm place below upper permanent magnet, lower permanent magnet is enclosed within Magnetic suspension spindle outer shroud, and is fixed on magnetic floating axle pressing disc upper end, and lower coil is enclosed within Magnetic suspension spindle outer shroud, and is fixed on base interior, 5-10cm place above lower permanent magnet, aligning adjusts the worktable that inclines to be configured on magnetic floating axle system center, and three-jaw electric chuck is configured in aligning tune and inclines on worktable center, gate left column and gate right column are symmetrically distributed in the both sides of magnetic floating axle 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 web member and lower-left mast web member, the horizontal measuring staff horizontal nest in upper left is on the mast web member of upper left, the horizontal measuring staff of upper sensor adaptor and upper left is connected, and upper axial current vortex sensor and upper sensor adaptor are connected, the horizontal measuring staff horizontal nest in lower-left is on the mast web member of lower-left, and the horizontal measuring staff of lower sensor adaptor and lower-left is connected, lower axial current vortex sensor and lower sensor adaptor, removablely successively from top to bottom on gate right column be adjustably set with upper right mast web member and bottom right mast web member, the horizontal measuring staff horizontal nest of upper right is on upper right mast web member, and upper radial current vortex sensor is connected with upper right transverse direction measuring staff, the horizontal measuring staff horizontal nest in bottom right is on the mast web member of bottom right, and the horizontal measuring staff of lower radial current vortex sensor and bottom right is connected.
Compared with prior art, feature of the present invention is:
The present invention can obtain the right alignment weights of each rotor by the concentricity and verticality measuring each rotor, again the right alignment weights of each rotor are carried out vector optimization, just can obtain instructing setting angle, save 40% set-up time and expense, the one-step installation success ratio 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 measurement mechanism structural representations
Fig. 2 is magnetic floating axle architecture schematic diagram
Piece number in figure: 1-pedestal, 2-magnetic floating axle system, 2a-Magnetic suspension spindle, 2b-worktable, platen on 2c-magnetic floating axle, 2d-magnetic floating axle pressing disc, 2e-photoelectric encoder, 2f-photoelectric encoder code-disc, 2g1-upper permanent magnet, 2g2-lower permanent magnet, 2h1-upper coil, 2h2-lower coil, 3-aligning adjusts the worktable that inclines, 4-three-jaw electric 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 web member, 7b-bottom right mast web member, 7c-upper left mast web member, 7d-upper right mast web member, 8a-lower axial current vortex sensor, 8b-upper axial current vortex sensor, 9a-lower radial current vortex sensor, 9b-upper radial current vortex sensor, 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 radial aeromotor multiaxis rotor assembling method with axial benchmark and a device, described method and apparatus is: three-jaw electric chuck 4 is configured in aligning and adjusts and incline on worktable 3 center.Gate left column 5a and gate right column 5b is symmetrically distributed in the both sides of magnetic floating axle 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 web member 7c and lower-left mast web member 7a, upper left horizontal measuring staff 6c horizontal nest is on the mast web member 7c of upper left, upper sensor adaptor 10b and the horizontal measuring staff 6c in upper left is connected, and upper axial current vortex sensor 8b and upper sensor adaptor 10b is connected; Lower-left horizontal measuring staff 6a horizontal nest is on the mast web member 7a of lower-left, and lower sensor adaptor 10a and the horizontal measuring staff 6a in lower-left is connected, lower axial current vortex sensor 8a and lower sensor adaptor 10a; On gate right column 5b from top to bottom successively removable be adjustably set with upper right mast web member 7d and bottom right mast web member 7b, upper right horizontal measuring staff 6d horizontal nest is on upper right mast web member 7d, and upper radial current vortex sensor 9b and the horizontal measuring staff 6d of upper right is connected; Bottom right horizontal measuring staff 6b horizontal nest is on the mast web member 7b of bottom right, and lower radial current vortex sensor 9a and the horizontal measuring staff 6b in bottom right is connected.Magnetic floating axle system 2 is nested on pedestal 1 center, described magnetic floating axle system 2 is by Magnetic suspension spindle 2a, worktable 2b, platen 2c on magnetic floating axle, magnetic floating axle pressing disc 2d, photoelectric encoder 2e, photoelectric encoder code-disc 2f, upper permanent magnet 2g1, lower permanent magnet 2g2, upper coil 2h1 and lower coil 2h2 is formed, described worktable 2b to be configured on magnetic floating axle on platen 2c upper end, on magnetic floating axle, platen 2c is configured on Magnetic suspension spindle 2a upper end, Magnetic suspension spindle 2a is configured on magnetic floating axle pressing disc 2d upper end, photoelectric encoder code-disc 2f is nested on magnetic floating axle pressing disc 2d outer shroud, photoelectric encoder 2e fits over pedestal 1 center lower inside admittedly, and it is outside to be positioned at photoelectric encoder code-disc 2f.Upper permanent magnet 2g1 is enclosed within Magnetic suspension spindle 2a outer shroud, and is fixed on platen 2c bottom on magnetic floating axle, and upper coil 2h1 is enclosed within Magnetic suspension spindle 2a outer shroud, and it is inner to be fixed on pedestal 1,5-10cm place below upper permanent magnet 2g1; Lower permanent magnet 2g2 is enclosed within Magnetic suspension spindle 2a outer shroud, and is fixed on magnetic floating axle pressing disc 2d upper end, and lower coil 2h2 is enclosed within Magnetic suspension spindle 2a outer shroud, and it is inner to be fixed on pedestal 1,5-10cm place above lower permanent magnet 2g2.Magnetic floating axle system 2 drive measured rotor at the uniform velocity rotates 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, lower radial current vortex sensor 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 tilt quantity, aligning adjusts the worktable 3 that inclines to be configured on magnetic floating axle system 2 center, 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 tilt quantity, regulate aligning to adjust to incline worktable 3 until the size meeting axial reference field tilt quantity is 0 ~ 2 " in scope, upper left mast web member 7c is vertically nested in the upside of gate left column 5a, upper left horizontal measuring staff 6c horizontal nest is on the mast web member 7c of upper left, upper sensor adaptor 10b and the horizontal measuring staff 6d in upper left is connected, upper axial current vortex sensor 8b and upper sensor adaptor 10b is connected, the axis that upper axial current vortex sensor 8b measures measured rotor is installed and measured face, upper right mast web member 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 web member 7d, upper radial current vortex sensor 9b and the horizontal measuring staff 6d of upper right is connected, the radial direction that upper radial current vortex sensor 9b measures measured rotor installs and measures face, magnetic floating axle system 2 at the uniform velocity rotates with the speed of 6 ~ 10r/min, and upper axial current vortex sensor 8b installs and measures equal interval sampling on face in the axis of measured rotor, and upper radial current vortex sensor 9b installs and measures equal interval sampling on face in the radial direction of measured rotor, sampling number should meet and often encloses 1000 ~ 2000 points, the data upper radial current vortex sensor 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 current vortex sensor 8b being installed and measured face up-sampling in the axis of measured rotor are by least square plane matching and assess verticality, combined axis is to the radius in the face of installing and measuring and this measured rotor and the difference in height 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 account form 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 difference in height of finally assembling rotor, R represents the radius axially installing and measuring face, P represents that measured rotor axially installs and measures the verticality in face, and θ represents the angle axially installing and measuring the fit Plane peak place in face.

Claims (1)

1. one kind based on the radial aeromotor multiaxis rotor assembling apparatus with axial benchmark, it is characterized in that magnetic floating axle system (2) is nested on pedestal (1) center, described magnetic floating axle system (2) is by Magnetic suspension spindle (2a), worktable (2b), platen (2c) on magnetic floating axle, magnetic floating axle pressing disc (2d), photoelectric encoder (2e), photoelectric encoder code-disc (2f), upper permanent magnet (2g1), lower permanent magnet (2g2), upper coil (2h1) and lower coil (2h2) are formed, described worktable (2b) to be configured on magnetic floating axle on platen (2c) upper end, on magnetic floating axle, platen (2c) is configured on Magnetic suspension spindle (2a) upper end, Magnetic suspension spindle (2a) is configured on magnetic floating axle pressing disc (2d) upper end, photoelectric encoder code-disc (2f) is nested on magnetic floating axle pressing disc (2d) outer shroud, photoelectric encoder (2e) fits over pedestal (1) center lower inside admittedly, and it is outside to be positioned at photoelectric encoder code-disc (2f), upper permanent magnet (2g1) is enclosed within Magnetic suspension spindle (2a) outer shroud, and be fixed on platen (2c) bottom on magnetic floating axle, upper coil (2h1) is enclosed within Magnetic suspension spindle (2a) outer shroud, and it is inner to be fixed on pedestal (1), apart from 5-10cm place, upper permanent magnet (2g1) below, lower permanent magnet (2g2) is enclosed within Magnetic suspension spindle (2a) outer shroud, and be fixed on magnetic floating axle pressing disc (2d) upper end, lower coil (2h2) is enclosed within Magnetic suspension spindle (2a) outer shroud, and it is inner to be fixed on pedestal (1), apart from 5-10cm place, lower permanent magnet (2g2) top, aligning adjusts the worktable (3) that inclines to be configured on magnetic floating axle system (2) center, and three-jaw electric chuck (4) is configured in aligning tune and inclines on worktable (3) center, gate left column (5a) and gate right column (5b) are symmetrically distributed in the both sides of magnetic floating axle system (2), and being packed on pedestal (1), 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 web member (7c) and lower-left mast web member (7a), horizontal measuring staff (6c) horizontal nest in upper left is on upper left mast web member (7c), upper sensor adaptor (10b) is connected with the horizontal measuring staff (6c) in upper left, and upper axial current vortex sensor (8b) and upper sensor adaptor (10b) are connected, horizontal measuring staff (6a) horizontal nest in lower-left is on lower-left mast web member (7a), lower sensor adaptor (10a) is connected with the horizontal measuring staff (6a) in lower-left, lower axial current vortex sensor (8a) and lower sensor adaptor (10a), removablely successively from top to bottom on gate right column (5b) be adjustably set with upper right mast web member (7d) and bottom right mast web member (7b), horizontal measuring staff (6d) horizontal nest of upper right is on upper right mast web member (7d), and upper radial current vortex sensor (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 web member (7b), and lower radial current vortex sensor (9a) is connected with the horizontal measuring staff (6b) in bottom right.
CN201410051756.9A 2014-02-14 2014-02-14 Aero-engine multiaxis rotor assembling method and device based on radial and axial datum CN103776365B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410051756.9A CN103776365B (en) 2014-02-14 2014-02-14 Aero-engine multiaxis rotor assembling method and device based on radial and axial datum

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201410051756.9A CN103776365B (en) 2014-02-14 2014-02-14 Aero-engine multiaxis rotor assembling method and device based on radial and axial datum

Publications (2)

Publication Number Publication Date
CN103776365A CN103776365A (en) 2014-05-07
CN103776365B true CN103776365B (en) 2015-06-17

Family

ID=50568896

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201410051756.9A CN103776365B (en) 2014-02-14 2014-02-14 Aero-engine multiaxis rotor assembling method and device based on radial and axial datum

Country Status (1)

Country Link
CN (1) CN103776365B (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103790645B (en) * 2014-02-14 2015-09-16 哈尔滨工业大学 Evaluate and the aeroengine rotor assembly method optimized and device based on concentricity and perpendicularity
CN105466332A (en) 2015-11-13 2016-04-06 珠海格力节能环保制冷技术研究中心有限公司 Angle sensor and angle measuring method
CN108089444B (en) * 2017-12-18 2020-07-14 哈尔滨工业大学 Double-shaft turntable synchronous control method based on corrected reference model
US20200320160A1 (en) * 2018-09-12 2020-10-08 Dalian University Of Technology Method for calculating axis deviation of rotor assembly based on end face runout measurement
WO2020051794A1 (en) * 2018-09-12 2020-03-19 大连理工大学 Method for calculating rotor assembly axis eccentricity based on radial run-out measurement

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1635589A (en) * 2004-10-22 2005-07-06 中国工程物理研究院应用电子学研究所 A concentric assembly method and device for regulating same
US20060112577A1 (en) * 2004-11-30 2006-06-01 Tennessee Valley Authority Vertical shaft alignment tool
US20090165273A1 (en) * 2007-12-27 2009-07-02 Bruce Calvert Gas turbine rotor assembly method
CN101799354A (en) * 2010-02-09 2010-08-11 西安交通大学 Method for testing assembly performance of rotor of aircraft engine
CN102121875A (en) * 2010-12-17 2011-07-13 大连理工大学 Dynamic loading comprehensive experimental table for gas bearing-rotor system
CN102175135A (en) * 2011-01-26 2011-09-07 沈阳黎明航空发动机(集团)有限责任公司 Non-contact measuring method for leaf apex radial clearance of engine rotor
CN202024752U (en) * 2011-04-01 2011-11-02 罗信精密零件(上海)有限公司 Coaxiality measuring instrument
EP2525049A2 (en) * 2011-05-17 2012-11-21 Rolls-Royce plc System and method for improving the damage tolerance of a rotor assembly

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1635589A (en) * 2004-10-22 2005-07-06 中国工程物理研究院应用电子学研究所 A concentric assembly method and device for regulating same
US20060112577A1 (en) * 2004-11-30 2006-06-01 Tennessee Valley Authority Vertical shaft alignment tool
US20090165273A1 (en) * 2007-12-27 2009-07-02 Bruce Calvert Gas turbine rotor assembly method
CN101799354A (en) * 2010-02-09 2010-08-11 西安交通大学 Method for testing assembly performance of rotor of aircraft engine
CN102121875A (en) * 2010-12-17 2011-07-13 大连理工大学 Dynamic loading comprehensive experimental table for gas bearing-rotor system
CN102175135A (en) * 2011-01-26 2011-09-07 沈阳黎明航空发动机(集团)有限责任公司 Non-contact measuring method for leaf apex radial clearance of engine rotor
CN202024752U (en) * 2011-04-01 2011-11-02 罗信精密零件(上海)有限公司 Coaxiality measuring instrument
EP2525049A2 (en) * 2011-05-17 2012-11-21 Rolls-Royce plc System and method for improving the damage tolerance of a rotor assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
航空发动机盘类转子柔性装配工装构型研究;李伟楠等;《沈阳航空航天大学学报》;20130630;第30卷(第3期);第6-9页 *

Also Published As

Publication number Publication date
CN103776365A (en) 2014-05-07

Similar Documents

Publication Publication Date Title
EP1568848B1 (en) A method and machine for rotor unbalance determination
DK1959127T3 (en) Method and device for indirect determination of a wind or installation hydro dynamic sizes
CN105424160B (en) The method for realizing the identification of blade synchronization vibration parameters
CN102890477B (en) On-line active dynamic balance measurement and control device and on-line active dynamic balance measurement and control method
CN105921996B (en) A kind of large-sized unit shaft coupling centralising device and centering method
CN103438845B (en) Cylindrical coordinate measuring machine
CN102175135A (en) Non-contact measuring method for leaf apex radial clearance of engine rotor
CN103364069A (en) Non-contact rotating vane vibration testing method based on positioning without rotating speed
CN105588718B (en) Machine tool chief axis combination property detection/monitoring test system and method
CN102171447B (en) Method and system for aligning a wind turbine component
CN103323233B (en) Device and method for testing dynamic characteristics of single-screw or double-screw rolling supporting linear feed system
CN103954210B (en) Measuring device and method of automatic non-contact hydro-generator rotor roundness
US20090324409A1 (en) Rotor blade monitoring
CN102539072A (en) Field dynamic balance measuring device and method for utility boiler side fan
CN104316290A (en) Combined type propeller thrust torque measurement device
CN103175679A (en) Comprehensive test system for characteristics of rotors of four-rotor aircrafts
CN103698128B (en) A kind of air gaps hybrid magnetic suspension bearing performance testing device
CN102430918B (en) Coaxiality guide and correction device and guide and correction method using same
CN101639395A (en) Improved holographic dynamic balancing method of high-speed main shaft
CN102175540B (en) Torsion testing device for torsional spring
CN102095574A (en) Joint surface dynamic characteristic parameter testing device of rolling guide rail and testing method thereof
CN105067106B (en) A kind of intershaft bearing vibration signals collecting method
CN105466329A (en) Non-contact engine turbine blade tip radial gap measurement method
CN108918066B (en) A kind of seam allowance connection structure rotor experiment table and test method
CN105115422B (en) Non-contact wheel multifunctional examining examining system

Legal Events

Date Code Title Description
PB01 Publication
C06 Publication
SE01 Entry into force of request for substantive examination
C10 Entry into substantive examination
GR01 Patent grant
C14 Grant of patent or utility model
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20150617

Termination date: 20200214

CF01 Termination of patent right due to non-payment of annual fee