WO2016065717A1 - 航空发动机转静子装配/测量五自由度调整定位方法与装置 - Google Patents

航空发动机转静子装配/测量五自由度调整定位方法与装置 Download PDF

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Publication number
WO2016065717A1
WO2016065717A1 PCT/CN2014/095125 CN2014095125W WO2016065717A1 WO 2016065717 A1 WO2016065717 A1 WO 2016065717A1 CN 2014095125 W CN2014095125 W CN 2014095125W WO 2016065717 A1 WO2016065717 A1 WO 2016065717A1
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WIPO (PCT)
Prior art keywords
axis
test piece
motion
drive system
adjustment
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PCT/CN2014/095125
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English (en)
French (fr)
Inventor
谭久彬
黄景志
谷伟
温众普
Original Assignee
哈尔滨工业大学
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Application filed by 哈尔滨工业大学 filed Critical 哈尔滨工业大学
Priority to GB1703633.6A priority Critical patent/GB2546190B/en
Priority to US15/304,238 priority patent/US9695707B2/en
Publication of WO2016065717A1 publication Critical patent/WO2016065717A1/zh

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
    • B23P19/001—Article feeders for assembling machines
    • B23P19/002—Article feeders for assembling machines orientating the articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
    • B23P19/10—Aligning parts to be fitted together
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
    • B23Q1/00—Members which are comprised in the general build-up of a form of machine, particularly relatively large fixed members
    • B23Q1/25—Movable or adjustable work or tool supports
    • B23Q1/44—Movable or adjustable work or tool supports using particular mechanisms
    • B23Q1/50—Movable or adjustable work or tool supports using particular mechanisms with rotating pairs only, the rotating pairs being the first two elements of the mechanism
    • B23Q1/54—Movable or adjustable work or tool supports using particular mechanisms with rotating pairs only, the rotating pairs being the first two elements of the mechanism two rotating pairs only
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/35—Arrangement of components rotated
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/83—Testing, e.g. methods, components or tools therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention belongs to the technical field of aircraft engine assembly measurement, and particularly relates to a method and device for adjusting and positioning a five-degree-of-freedom of aero-engine static sub-assembly/measurement.
  • Engine vibration is an important factor affecting aircraft safety and an important indicator of engine performance.
  • the engine's turbine components have high speed and high mass and are a major source of vibration for the engine.
  • the assembly process In order to reduce this effect, in addition to being eliminated during the engine dynamic balance test, the assembly process must be strictly controlled, because the engine assembly is the previous step of dynamic balancing, and the vibration is amplified at high speed when the assembly is unreasonable 100-1000. Times, good assembly can greatly reduce the pressure of dynamic balance. Therefore, as a key technology to improve the performance of aero-engines, aero-engine assembly testing technology has received more and more attention and has become a research hotspot.
  • the aero-engine consists of a complex turbine stator and rotor.
  • the stator and rotor need to be highly concentric after assembly.
  • the high-pressure turbine rotor is a cantilever structure, so slight imbalances and disturbances can cause large vibration reactions.
  • the test object of the aero-engine assembly is the turbine stator and the rotor. Under the condition that the machining accuracy of the component meets the requirements, the final inspection is controlled by the guarantee of the installation fitting precision and the concentricity.
  • Engine rotation The high pressure is generated, and its static rotor is composed of a plurality of single components stacked together, and the rotary shaft of each component is ideally coincident with the axis of the entire engine.
  • the high-speed rotation speed of a large engine is greater than 10,000 rpm, the axial or radial deflection of a single component will inevitably cause the center of the turbine disk to deviate from the axis of rotation of the engine. Under such conditions, a very large centrifugal force will be generated, resulting in an imbalance of rotor rotation. This causes engine vibration, thus ensuring the concentricity of the components is the focus and difficulty of installation.
  • the British Taylor Hobson Company has developed a three-point method to adjust the tilting workbench.
  • the worktable is supported by three fulcrums A, B, and P constituting an equilateral triangle, wherein the P point is fixed, and the other A and B points are equipped with a driving mechanism to realize micro movement in the vertical direction, thereby
  • the adjustment of the inclination of the workpiece is achieved (AB Barnaby, MW Mills, HRLane, General apparatus workpiece position controller-automatically centres and levels by computer using surface data from transducer with transverse compensation after tilting. EP240150-A2.1987: 2-8).
  • the workbench uses a drive mechanism to directly carry the load, and all the weight of the load falls on the three fulcrums, which requires the drive mechanism to have a large driving force, and the workbench cannot be used in the case of a large load.
  • Tokyo Precision Co., Ltd. designed a table that can perform eccentricity and tilt adjustment in two orthogonal directions, and gave a tilt adjustment method using multiple measurement sections to obtain the axial direction of the workpiece (Katamachi, Shouzou .Roundness Measurement Apparatus.US20080154540.2008: 1 ⁇ 5).
  • Patent CN201110450087 “A large-scale three-dimensional adjustment platform for multi-function measuring instruments” proposes a large-scale three-dimensional adjustment platform for multi-function measuring instruments.
  • Two telescopic motors distributed in the platform can push the intermediate platform to rotate along the rotating components and drive The upper platform rotates together to realize the adjustment of the tilting swing of the workpiece in the Z direction.
  • the tilt adjustment of the platform can only rotate around a rotating component, and the tilt adjustment capability is limited and the precision is not high.
  • the patent CN98229568.5 "high-precision fast automatic leveling mechanism” proposes a high-precision fast leveling mechanism.
  • the working principle is as follows: the motor drives the eccentric wheel to rotate, and the spring in the base makes the thimble and the eccentric wheel lean against each other to drive the positioning.
  • the nail and the calibration plate move up and down along the bearing sleeve.
  • the calibration plate is an air-floating thrust bearing, and the end faces are evenly distributed with a plurality of throttle micro-holes; the bearing table is connected with the hemisphere, and when the hemisphere and the hemisphere seat are connected with pressurized air When the bearing table can rotate around the center of the hemisphere seat, the rising cylinder drives the bearing table to move up and down.
  • a gas film is formed and the workpiece is leveled indirectly.
  • the object of the present invention is to solve the problems of the prior art mentioned above, and propose a 360° rotary motion about the Z axis, a plane motion along the X axis, a plane motion along the Y axis, a rotary motion around the X axis, and a wrap around the Y.
  • the five-degree-of-freedom adjustment method of the rotary motion of the shaft, the planar motion and the rotation adjustment of the tested component by the composite motion of five degrees of freedom; the present invention also provides an aero-engine static subassembly/measurement five degrees of freedom Adjust the positioning device.
  • An aero-engine static subassembly/measurement five-degree-of-freedom adjustment positioning method which comprises 360° rotary motion around a Z-axis, planar motion along an X-axis, and planar motion along the Y-axis, and rotational motion around the X-axis
  • the yaw motion of the Y-axis is five degrees of freedom
  • the X-axis and the Y-axis are orthogonal to each other, and the Z-axis is perpendicular to the plane defined by the X-axis and the Y-axis
  • the test piece is performed by a composite motion of five degrees of freedom
  • the adjustment of the plane motion and rotation, the specific adjustment process is:
  • Plane motion adjustment 1) Firstly, the test piece is rotated 360° by the Z-axis, and the radial error of the specified section on the tested piece is measured by the sensor to obtain the eccentricity ⁇ x of the tested part on the X-axis and the Y-axis.
  • the eccentricity ⁇ y; 2) according to ⁇ x adjusts the test piece to move along the X axis, the displacement of the motion is ⁇ x; according to ⁇ y, the test piece moves along the Y axis, the displacement of the motion is ⁇ y; 3) Repeat steps 1) ⁇ 2 The adjustment of the planar motion is stopped until the eccentricity ⁇ x of the test piece on the X-axis is less than the set value ⁇ x 0 and the eccentricity ⁇ y on the Y-axis is less than the set value ⁇ y 0 .
  • Rotation adjustment 1) The Z-axis is rotated 360° around the test piece, and the measured cross-section 1 on the test piece is measured using a sensor to obtain the spatial coordinates (x 1 , y 1 , z 1 ) of the center of the cross-section 1 fit.
  • the Z-axis is driven to rotate the test piece 360° for the whole week, and the measuring section 2 specified on the test piece is measured by using the sensor to obtain the spatial coordinate (x 2 , y 2 , z 2 ) of the center of the fitting of the section 2; Calculating the spatial position of the geometric axis of the test piece from (x 1 , y 1 , z 1 ) and (x 2 , y 2 , z 2 ), and obtaining the angle ⁇ between the geometric axis along the X-axis direction and the Z-axis x , the angle ⁇ y along the Y axis along the Y axis; 4) adjust the rotation of the test piece around the Y axis according to ⁇ x , the angle of the rotary motion is ⁇ x ; adjust the rotation of the test piece around the X axis according to ⁇ y The angle of the rotary motion is ⁇ y , so that the geometric axis of the test piece is adjusted to coincide with the
  • An aero-engine rotary subassembly/measurement five-degree-of-freedom adjustment positioning device includes a clamping mechanism, a rotating table component, a translational table component, and a rotary table component.
  • the rotating table component comprises a table top and a base, and the table top is placed on the base; a toroidal convex ball bowl is arranged on the table top, and a circular concave spherical seat is arranged on the base, the annular concave ball A retainer is fixedly mounted on the seat, and a circular hole uniformly distributed in the circumferential direction is arranged on the retainer, and a spherical rolling body g 1 having an equal spherical diameter is embedded in the circular hole; the concave concave spherical seat on the base Supporting the annular convex ball bowl on the table by the spherical rolling body g 1 ; an elastic limit support column and a driving system Q 1 are arranged along the X axis on the base, and the elastic limit support column and the configuration stopper on the table close contact with a stopper for preventing relative rotation between the table and the base; in the table attached to the transmission member of the drive system P 1 Q 1 and arranged to drive
  • the driving system Q 1 is arranged adjacent to the driving system Q 2 , and the elastic limiting support columns are arranged adjacent to the elastic guiding columns.
  • the clamping mechanism is fixed to the table top of the rotating table member.
  • the translation table member is disposed below the rotating table member to drive the rotating table member to move along the X axis and the Y axis;
  • the translation table member includes a bottom plate and a guiding layer, and the guiding layer is disposed in the circumferential direction a weight reducing groove, wherein a sleeve plate is disposed in the weight reducing groove;
  • a through hole is densely arranged on the sleeve plate, and a spherical rolling body g 2 having an equal spherical diameter is embedded in the through hole;
  • the sleeve plate passes through the spherical rolling body g 2 providing support for the base on the rotating table member;
  • a drive system Q 3 is disposed at a diameter opposite to the drive system Q 2 for driving the guide layer to move along the Y axis; and is disposed at a diameter opposite to the drive system Q 1
  • the drive system Q 4 is configured to drive the base on the rotating table member to move along the X axi
  • the rotary table component comprises an air floating sleeve, an air floating shaft and a rotary drive system Q 5 , wherein the air floating shaft is fitted in the air floating sleeve, and the upper end of the air floating shaft and the bottom plate of the translation unit At the lower end of the air-floating shaft, a rotary drive system Q 5 is arranged to drive the air-floating shaft to rotate.
  • the spherical rolling body g 1 embedded in the circular hole has the same spherical diameter as the spherical rolling body g 2 embedded in the through hole, or the spherical diameter is different.
  • the X axis and the Y axis are orthogonal to each other, and the axis of rotation of the air floating axis is perpendicular to a plane defined by the X axis and the Y axis.
  • the degree of freedom adjustment and positioning device makes full use of the characteristics of spherical guiding and rolling reduction, as well as the high-precision characteristics of gas lubrication, and achieves excellent characteristics of high displacement sensitivity and high stability under large load conditions, and satisfies the aeroengine rotation. Static precision adjustment and measurement needs;
  • the rotating table member is placed on the spherical rolling body g 2 of the bottom plate, and the frictional force between the rotating table member and the base is changed into rolling friction, thereby reducing the friction force, thereby ensuring the device under the condition of large load.
  • the sleeve plate of the device of the invention adopts a lightweight material, which reduces the resistance of the rolling element g 2 rolling in the weight reduction groove, and improves the movement sensitivity of the translational member moving along the X-axis direction.
  • the method and device of the invention are particularly suitable for the aero-engine static sub-assembly measurement occasion, and solve the problem of accurately adjusting and positioning the assembled/measured test piece under the condition of large load or large load.
  • Figure 1 is a coordinate system diagram of a five-degree-of-freedom adjustment method for aero-engine static subassembly/measurement
  • FIG. 2 is a schematic structural view of an aero-engine static subassembly/measurement five-degree-of-freedom adjustment positioning device
  • FIG. 3 is a schematic view showing the structure of a table of a five-degree-of-freedom adjustment and positioning device for aero-engine rotary subassembly/measurement;
  • FIG. 4 is a schematic structural view of a base of an aero-engine rotary subassembly/measurement five-degree-of-freedom adjustment positioning device
  • Fig. 5 is a schematic view showing the structure of the guiding layer of the aero-engine static sub-assembly/measurement five-degree-of-freedom adjusting and positioning device.
  • A rotating table components
  • B translation table components
  • C rotary table components
  • 1, clamping mechanism 2, table top; 3, base
  • 8, elastic limit support column 9, drive system Q 1 ; 10 limit stop; 11, transmission components P 1 ; 12, elastic guide column; 13, drive system Q 2 ;14, guiding block; 15, transmission part P 2 ; 16, bottom plate; 17, guiding layer; 18, weight reducing groove; 19, sleeve plate; 20, through hole; 21, drive system Q 3 ; System Q 4 ; 23, air-floating sleeve; 24, air-floating shaft; 25, slewing drive system Q 5 ; L, geometric axis of the tested piece.
  • an aero-engine rotary subassembly/measurement five-degree-of-freedom adjustment positioning device includes a clamping mechanism 1, a rotary table member A, a translational table member B, and a rotary table member C.
  • the rotating table member A includes a table top 2 and a base 3, and the table top 2 is placed on the base 3.
  • a toroidal convex bowl 4 is disposed, and the base 3 is provided with a concave concave ball.
  • a retaining frame 6 is fixed to the annular concave spherical seat 5, and a circular hole 7 uniformly distributed in the circumferential direction is arranged on the retaining frame 6, and a spherical rolling body having an equal spherical diameter is embedded in the circular hole 7.
  • the annular concave ball seat 5 on the base 3 provides support for the annular convex ball bowl 4 on the table 2 by the spherical rolling body g 1 ;
  • the elastic is arranged along the X axis on the base 3
  • the limit support post 8 and the drive system Q 1 9 , the elastic limit support post 8 and the limit stop 10 disposed on the table 2 are in close contact with each other to prevent relative rotation between the table 2 and the base 3;
  • the drive system Q 1 9 is connected to the transmission member P 1 11 disposed on the table 2 for driving the table 2 to rotate about the Y axis; on the base 3, the elastic guide column 12 and the drive system Q 2 13 are disposed along the Y axis.
  • the elastic guide post 12 is in contact with the guide block 14 disposed on the table 2 for guiding the table 2 to rotate about the X axis; the drive system Q 2 13 is disposed at The transmission members P 2 15 on the table top 2 are connected to drive the table 2 to rotate about the X axis.
  • the drive system Q 1 9 is arranged orthogonally adjacent to the drive system Q 2 13 , and the elastic limit support columns 8 are arranged adjacent to the elastic guide columns 12 orthogonally.
  • the chucking mechanism 1 is fixed to the table top 2 of the turntable member A.
  • the translation table member B is placed below the rotary table member A to drive the rotary table member A to move along the X-axis and the Y-axis;
  • the translation table member B includes a bottom plate 16 and a guiding layer 17 at the guiding layer A weight reducing groove 18 is disposed in the circumferential direction, and a sleeve 19 is disposed in the weight reducing groove 18;
  • a through hole 20 is disposed in the sleeve 19, and a spherical diameter is embedded in the through hole 20.
  • the spherical rolling body g 2 ; the cover plate 19 provides support for the base 3 on the rotary table member A by the spherical rolling body g 2 ; a drive system Q 3 21 is disposed at a diameter opposite to the drive system Q 2 13 for driving the guide The layer 17 is moved along the Y-axis; a drive system Q 4 22 is disposed at a counter-diameter to the drive system Q 1 9 for driving the base 3 on the rotary table member A to move along the X-axis.
  • the rotary table member C includes an air floating sleeve 23, an air floating shaft 24 and a swing drive system Q 5 25, and the air floating shaft 24 is fitted in the air floating sleeve 23, and the upper end of the air floating shaft 24 is
  • the bottom plate 16 of the paddle member B is fixedly connected, and the lower end of the air floating shaft 24 is provided with a swing drive system Q 5 25 for driving the air floating shaft 24 to rotate.
  • the spherical rolling element g 1 embedded in the circular hole 7 has the same spherical diameter as the spherical rolling element g 2 embedded in the through hole 20, or has a different spherical diameter.
  • the X axis and the Y axis are orthogonal to each other, and the axis of rotation of the air floating shaft 24 is perpendicular to a plane defined by the X axis and the Y axis.
  • the aero-engine static sub-assembly/measurement five-degree-of-freedom adjustment positioning method uses the slewing drive system Q 5 25 to drive the air-floating shaft 24 to form a 360° rotary motion around the Z-axis in the air-floating sleeve 23, which is driven by the drive system Q 4 22
  • the base 3 on the table member A moves along the X axis
  • the drive system Q 3 21 drives the guide layer 17 to move along the Y axis, causing the load to also move along the Y axis.
  • the plane motion adjustment process is as follows: 1) Firstly, the test piece is rotated 360° by the air floating shaft 24, and the radial error of the specified section on the tested piece is measured by the sensor to obtain the eccentricity ⁇ x of the tested part on the X axis and The eccentricity ⁇ y on the Y-axis; 2) according to ⁇ x, the drive system Q 4 22 drives the base 3 on the rotary table member A to move along the X-axis, and adjusts the test piece to move along the X-axis, and the displacement of the movement is ⁇ x; ⁇ y drive system Q 3 21 drives the guide layer 17 to move along the Y axis, adjusts the test piece to move along the Y axis, and the displacement of the motion is ⁇ y; 3) repeat steps 1) to 2) until the test piece is on the X axis.
  • the adjustment of the plane motion is stopped; the rotation adjustment process is: 1) driving the test piece to rotate all the way through the air floating shaft 24 360°, using the sensor to measure the measured section 1 on the test piece, the spatial coordinates (x 1 , y 1 , z 1 ) of the center of the fitting of the section 1 are obtained; 2) the part to be tested is rotated by the air floating shaft 24 360°, using the sensor to measure the specified measurement section 2 on the test piece, and get the cut 2 fitting center spatial coordinates (x 2, y 2, z 2); 3) a (x 1, y 1, z 1) and (x 2, y 2, z 2) is calculated to obtain a test piece geometrical axis L the spatial position, and obtains the geometric axis L in the X axis direction and the Z-axis angle ⁇ x, Y-axis direction and

Abstract

一种航空发动机转静子装配/测量五自由度调整定位方法与装置；该方法通过绕Z轴的360°回转运动、沿X轴的平面运动和沿Y轴的平面运动、绕X轴的回转运动和绕Y轴的回转运动五个自由度的复合运动，对被测试件进行平面运动和转动的调整；该装置包括装夹机构（1）、转动台部件（A）、平动台部件（B）和回转台部件（C）；本发明建立了一种同时兼顾大承载、高精度和高刚度特性的五自由度调整定位方法与装置，提高了航空发动机的装配效率和测量精度。

Description

航空发动机转静子装配/测量五自由度调整定位方法与装置 技术领域
本发明属于航空发动机装配测量技术领域，特别涉及一种航空发动机转静子装配/测量五自由度调整定位方法与装置。
背景技术
近年来，随着先进装备制造业逐渐朝向精密化和超精密化发展，特别是航空发动机性能的不断提升，对发动机加工装配的精度要求越来越高，尤其是在追求更高推重比的同时，由于装配误差产生的发动机振动、噪声等因素对性能的影响逐渐凸显出来。这就对发动机的测试装备性能提出了严峻的挑战，因而也对所使用的调整定位工作台性能有了更高的要求。对发动机的加工装配，不仅要求工作台实现平面上二维调整的功能，而且要求工作台能调整工件的倾角，实现调倾功能。
发动机振动是影响飞机安全的一个重要因素，也是反映发动机性能的一项重要指标。发动机涡轮部件转速高、质量大，是发动机的一个主要振源。为了降低此影响，除了在发动机动平衡测试过程中加以消除，还必须严格控制其装配过程，因为发动机装配是动平衡的前一步骤，由装配不合理导致振动在高速运转时会放大100-1000倍，装配良好可以很大程度上减小动平衡的压力。所以，作为提高航空发动机性能的关键技术，航空发动机装配测试技术越来越受到重视，并且成为研究的热点。
航空发动机由结构复杂的涡轮静子和转子组成，静子和转子除了需要保证自身很高的同心外，更需要两者装配后高度的同心。高压涡轮转子为悬臂结构，因而轻微的不平衡和扰动都会引起较大振动反应。目前有许多关于消除飞机振动的研究，消除涡轮静转子组件轴向和径向偏摆、保证涡轮轴承支撑同心度、保证总装装配与动平衡前装配一致性等措施都可以很好地解决发动机振动问题，而这些都可以在发动机装配的过程中加以控制。
航空发动机装配的测试对象是涡轮静子和转子，在部件加工精度满足要求的条件下，最终检验靠安装配合精度和同心度的保证加以控制。发动机旋转产 生高压，它的静转子由多个堆叠在一起的单部件组成，每个部件的回转轴与整个发动机的轴线重合时最为理想。大型发动机工作时的高速旋转速度大于10000rpm，单部件轴向或径向偏摆必然会造成涡轮盘中心偏离发动机转动轴线，在这样的条件下会产生非常大的离心力，造成转子转动的不平衡，造成发动机振动，因而保证各部件的同心度是安装的重点和难点。
英国泰勒霍普森公司研制了三点法调心调倾工作台。这种工作台由三个构成等边三角形的支点A,B,P来支撑工作台台面，其中P点固定，其它的A，B两点配有驱动机构可以实现在垂直方向上微移动，从而实现工件倾角的调整(A.B.Barnaby,M.W.Mills,H.R.Lane,Metrological apparatus workpiece position controller-automatically centres and levels by computer using surface data from transducer with transverse compensation after tilting.EP240150-A2.1987:2～8)。该工作台用驱动机构来直接承载负载，负载的所有重量都落在三个支点上，这就要求驱动机构要有很大的驱动力，这种工作台不能用在大承载的情况下。
日本东京精密公司设计了一种可以在正交的两个方向分别进行偏心和倾斜调整的工作台，并给出了一种利用多个测量截面来获取工件轴线方向的倾斜调整方法(Katamachi,Shouzou.Roundness Measurement Apparatus.US20080154540.2008:1～5)。
专利CN201110450087“一种多功能测量仪用大型三维调整平台”提出了一种多功能测量仪用大型三维调整平台，平台中分布的两个伸缩电机可推动中间平台沿旋转组件作转动运动，并带动上平台一起作旋转运动，从而实现对工件Z方向倾斜摆动的调整，该平台的倾斜调整只能绕一个旋转组件旋转，倾斜调整能力有限且精度不高专利。
专利CN98229568.5“高精度快速自动调平机构”提出了一种高精度快速调平机构，其工作原理是：电机带动偏心轮转动，基座中的弹簧使顶针与偏心轮相靠，带动定位钉和定标板沿轴承套上下移动，定标板为气浮止推轴承，端面均布若干个节流微孔；承件台与半球相连，当在半球和半球座之间通以压力空气时，承件台可绕半球座球心转动，由上升气缸带动承件台上下移动。当工件与定标板接近时，形成气膜而间接相靠将工件调平。
上述现有技术存在的共性问题是大载荷的情况下，无法保证调整装置的高精度和高分辨力，然而在航空发动机装配中，叶片等回转体组件重达几百千克， 且叶片装配是直接在工作台上进行，这就要求使用的调整工作台能够承受大载荷并有很高的调整定位精度。
发明内容
本发明的目的就是针对上述已有技术存在的问题，提出一种可绕Z轴的360°回转运动、沿X轴的平面运动和沿Y轴的平面运动、绕X轴的回转运动和绕Y轴的回转运动的五个自由度调整方法，通过五个自由度的复合运动，对被测试件进行平面运动和转动的调整；本发明还提供了一种航空发动机转静子装配/测量五自由度调整定位装置。
上述目的通过以下的技术方案实现：
一种航空发动机转静子装配/测量五自由度调整定位方法，该方法包括绕Z轴的360°回转运动、沿X轴的平面运动和沿Y轴的平面运动、绕X轴的回转运动和绕Y轴的回转运动五个自由度；所述的X轴与Y轴相互正交，Z轴垂直于X轴与Y轴所确定的平面；通过五个自由度的复合运动，对被测试件进行平面运动和转动的调整，其具体调整过程是：
平面运动调整：1)首先通过Z轴带动被测试件整周旋转360°，采用传感器测量被测试件上指定截面的径向误差，得到被测试件在X轴的偏心量Δx和在Y轴的偏心量Δy；2)依据Δx调整被测试件沿X轴运动，运动的位移量为Δx；依据Δy调整被测试件沿Y轴运动，运动的位移量为Δy；3)重复步骤1)～2)，直到满足被测试件在X轴的偏心量Δx小于设定值Δx0，在Y轴的偏心量Δy小于设定值Δy0，则停止平面运动的调整。
转动调整：1)通过Z轴带动被测试件整周旋转360°，使用传感器测量被测试件上指定的测量截面1，得到截面1拟合圆心的空间坐标(x1,y1,z1)；2)通过Z轴带动被测试件整周旋转360°，使用传感器测量被测试件上指定的测量截面2，得到截面2拟合圆心的空间坐标(x2,y2,z2)；3)由(x1,y1,z1)和(x2,y2,z2)计算得到被测试件几何轴线的空间位置，并获得该几何轴线沿X轴方向与Z轴的夹角θx，沿Y轴方向与Z轴的夹角θy；4)依据θx调整被测试件绕Y轴回转运动，回转运动的角度为θx；依据θy调整被测试件绕X轴回转运动，回转运动的角度为θy，从而调整被测试件的几何轴线与回转轴Z尽量重合；5)重复步骤1)～4)，直到被测试件几何轴线沿X轴方向与Z轴的夹角θx小于设定值θx0，沿Y轴方向与Z 轴的夹角θy小于设定值θy0，则停止转动运动的调整。
一种航空发动机转静子装配/测量五自由度调整定位装置，该装置包括装夹机构、转动台部件、平动台部件和回转台部件。
所述的转动台部件包括台面和底座，台面置于底座上；在所述台面上配置有圆环凸型球碗，在所述底座上配置有圆环凹型球座，所述圆环凹型球座上固连有保持架，在保持架上设有沿圆周方向均匀分布的圆孔，在圆孔内嵌有球径相等的球形滚动体g1；所述的底座上的圆环凹型球座通过球形滚动体g1为台面上的圆环凸型球碗提供支承；在所述的底座上沿X轴配置有弹性限位支承柱和驱动系统Q1，所述弹性限位支承柱与配置在台面上的限位挡块紧密接触配合，用以防止台面与底座之间有相对转动；所述驱动系统Q1与配置在台面上的传动部件P1相连，用以驱动台面绕Y轴转动；在底座上沿Y轴配置有弹性导向柱和驱动系统Q2，弹性导向柱与配置在台面的导向块接触配合，用以引导台面绕X轴转动；所述驱动系统Q2与配置在台面上的传动部件P2相连，用以驱动台面绕X轴转动。
驱动系统Q1与驱动系统Q2相邻正交布置，弹性限位支承柱与弹性导向柱相邻正交布置。
所述装夹机构固连于所述的转动台部件的台面上。
所述的平动台部件置于转动台部件的下方，带动转动台部件沿X轴和Y轴运动；所述平动台部件包括底板和导向层，在所述导向层上沿圆周方向设置有减重槽，在所述的减重槽内配置有套板；在套板上密布配置有通孔，在通孔内嵌有球径相等的球形滚动体g2；套板通过球形滚动体g2为转动台部件上的底座提供支承；在与驱动系统Q2的对径处配置有驱动系统Q3，用以驱动导向层沿Y轴运动；在与驱动系统Q1的对径处配置有驱动系统Q4，用以驱转动台部件上的底座沿X轴运动。
所述的回转台部件包括气浮套、气浮轴和回转驱动系统Q5，所述的气浮轴配装在气浮套内，气浮轴的上端与所述的平动台部件的底板固连，气浮轴的下端配置有回转驱动系统Q5，用以驱动气浮轴回转运动。
在圆孔内嵌入的球形滚动体g1与在通孔内嵌入的球形滚动体g2的球径尺寸相同，或球径尺寸不同。
X轴与Y轴相互正交，气浮轴的回转轴线垂直于X轴与Y轴所确定的平面。
本发明具有以下特点及有益效果：
1、本发明中将五个自由度运动复合起来，对被测试件进行平面运动和转动的调整，实现了将被测试件调整到装配测量过程中所需的任意位姿；同时所设计的五自由度调整定位装置充分利用了球面导向和滚动减磨的特性，以及气体润滑的运动高精度特性，达到在大负载情况下，仍具有高位移灵敏度和高稳定性的优良特性，满足航空发动机转静子精密装调和测量需要；
2、本发明装置中使转动台部件放置在底板的球形滚动体g2上，将转动台部件与底座的摩擦力变为滚动摩擦，降低了摩擦力，从而保证在大承载的情况下该装置具有高位移灵敏度，提高装置调整的精确性；
3、本发明装置中的套板采用轻质材料，减轻了球形滚动体g2在减重槽内滚动的阻力，提高了平动台部件沿X轴方向运动的移灵敏度。
本发明方法与装置特别适用于航空发动机转静子装配测量场合，解决大负载或超大负载场合下，对被装配/测量试件进行精确调整及定位的问题。
附图说明
图1为航空发动机转静子装配/测量五自由度调整方法坐标系图；
图2为航空发动机转静子装配/测量五自由度调整定位装置结构示意图；
图3为航空发动机转静子装配/测量五自由度调整定位装置的台面结构示意图；
图4为航空发动机转静子装配/测量五自由度调整定位装置的底座结构示意图；
图5为航空发动机转静子装配/测量五自由度调整定位装置的导向层结构示意图。
图中：A、转动台部件；B、平动台部件；C回转台部件；1、装夹机构；2、台面；3、底座；4、圆环凸型球碗；5、圆环凹型球座；6、保持架；7、圆孔；8、弹性限位支承柱；9、驱动系统Q1；10限位挡块；11、传动部件P1；12、弹性导向柱；13、驱动系统Q2；14、导向块；15、传动部件P2；16、底板；17、导向层；18、减重槽；19、套板；20、通孔；21、驱动系统Q3；22、驱动系统Q4；23、气浮套；24、气浮轴；25、回转驱动系统Q5；L、被测试件的几何轴线。
具体实施方式
下面结合附图对本发明的实施例作详细说明。
如图2所示，一种航空发动机转静子装配/测量五自由度调整定位装置，该装置包括装夹机构1、转动台部件A、平动台部件B和回转台部件C。
所述的转动台部件A包括台面2和底座3，台面2置于底座3上；在所述台面2上配置有圆环凸型球碗4，在所述底座3上配置有圆环凹型球座5，所述圆环凹型球座5上固连有保持架6，在保持架6上设有沿圆周方向均匀分布的圆孔7，在圆孔7内嵌有球径相等的球形滚动体g1；所述的底座3上的圆环凹型球座5通过球形滚动体g1为台面2上的圆环凸型球碗4提供支承；在所述的底座3上沿X轴配置有弹性限位支承柱8和驱动系统Q19，所述弹性限位支承柱8与配置在台面2上的限位挡块10紧密接触配合，用以防止台面2与底座3之间有相对转动；所述驱动系统Q19与配置在台面2上的传动部件P111相连，用以驱动台面2绕Y轴转动；在底座3上沿Y轴配置有弹性导向柱12和驱动系统Q213，弹性导向柱12与配置在台面2的导向块14接触配合，用以引导台面2绕X轴转动；所述驱动系统Q213与配置在台面2上的传动部件P215相连，用以驱动台面2绕X轴转动。
驱动系统Q19与驱动系统Q213相邻正交布置，弹性限位支承柱8与弹性导向柱12相邻正交布置。
所述装夹机构1固连于所述的转动台部件A的台面2上。
所述的平动台部件B置于转动台部件A的下方，带动转动台部件A沿X轴和Y轴运动；所述平动台部件B包括底板16和导向层17，在所述导向层17上沿圆周方向设置有减重槽18，在所述的减重槽18内配置有套板19；在套板19上密布配置有通孔20，在通孔20内嵌有球径相等的球形滚动体g2；套板19通过球形滚动体g2为转动台部件A上的底座3提供支承；在与驱动系统Q213的对径处配置有驱动系统Q321，用以驱动导向层17沿Y轴运动；在与驱动系统Q19的对径处配置有驱动系统Q422，用以驱转动台部件A上的底座3沿X轴运动。
所述的回转台部件C包括气浮套23、气浮轴24和回转驱动系统Q525，所 述的气浮轴24配装在气浮套23内，气浮轴24的上端与所述的平动台部件B的底板16固连，气浮轴24的下端配置有回转驱动系统Q525，用以驱动气浮轴24回转运动。
在圆孔7内嵌入的球形滚动体g1与在通孔20内嵌入的球形滚动体g2的球径尺寸相同，或球径尺寸不同。
X轴与Y轴相互正交，气浮轴24的回转轴线垂直于X轴与Y轴所确定的平面。
航空发动机转静子装配/测量五自由度调整定位方法，利用回转驱动系统Q525带动气浮轴24在气浮套23内形成绕Z轴的360°回转运动，由驱动系统Q422驱转动台部件A上的底座3沿X轴运动，驱动系统Q321驱动导向层17沿Y轴运动，带动负载也沿Y轴运动。平面运动调整过程为：1)首先通过气浮轴24带动被测试件整周旋转360°，采用传感器测量被测试件上指定截面的径向误差，得到被测试件在X轴的偏心量Δx和在Y轴的偏心量Δy；2)依据Δx利用驱动系统Q422驱转动台部件A上的底座3沿X轴运动，调整被测试件沿X轴运动，运动的位移量为Δx；依据利用Δy驱动系统Q321驱动导向层17沿Y轴运动，调整被测试件沿Y轴运动，运动的位移量为Δy；3)重复步骤1)～2)，直到满足被测试件在X轴的偏心量Δx小于设定值Δx0，在Y轴的偏心量Δy小于设定值Δy0，则停止平面运动的调整；转动调整过程为：1)通过气浮轴24带动被测试件整周旋转360°，使用传感器测量被测试件上指定的测量截面1，得到截面1拟合圆心的空间坐标(x1,y1,z1)；2)通过气浮轴24带动被测试件整周旋转360°，使用传感器测量被测试件上指定的测量截面2，得到截面2拟合圆心的空间坐标(x2,y2,z2)；3)由(x1,y1,z1)和(x2,y2,z2)计算得到被测试件几何轴线L的空间位置，并获得该几何轴线L沿X轴方向与Z轴的夹角θx，沿Y轴方向与Z轴的夹角θy；4)依据θx调整被测试件绕Y轴回转运动，驱动系统Q19与配置在台面2上的传动部件P111相连，用以驱动台面2绕Y轴转动；回转运动的角度为θx；依据θy调整被测试件绕X轴回转运动，利用在底座3上沿Y轴配置的弹性导向柱12和驱动系统Q213，弹性导向柱12与配置在台面2的导向块14接触配合，用以引导台面2绕X轴转动；驱动系统Q213与配置在台面2上的传动部件P215相连驱动台面2绕X轴转动，回转运动的角度为θy，从而调整被测试件的几何轴线L与回转轴Z尽量重合；5)重复步骤1)～4)，直到被测试件几何轴线L 沿X轴方向与Z轴的夹角θx小于设定值θx0，沿Y轴方向与Z轴的夹角θy小于设定值θy0，则停止转动运动的调整。

Claims (4)

  1. 一种航空发动机转静子装配/测量五自由度调整定位方法，其特征在于：该方法包括绕Z轴的360°回转运动、沿X轴的平面运动和沿Y轴的平面运动、绕X轴的回转运动和绕Y轴的回转运动五个自由度；所述的X轴与Y轴相互正交，Z轴垂直于X轴与Y轴所确定的平面；通过五个自由度的复合运动，对被测试件进行平面运动和转动的调整，其具体调整过程是：
    平面运动调整：1)首先通过Z轴带动被测试件整周旋转360°，采用传感器测量被测试件上指定截面的径向误差，得到被测试件在X轴的偏心量Δx和在Y轴的偏心量Δy；2)依据Δx调整被测试件沿X轴运动，运动的位移量为Δx；依据Δy调整被测试件沿Y轴运动，运动的位移量为Δy；3)重复步骤1)～2)，直到满足被测试件在X轴的偏心量Δx小于设定值Δx0，在Y轴的偏心量Δy小于设定值Δy0，则停止平面运动的调整；
    转动调整：1)通过Z轴带动被测试件整周旋转360°，使用传感器测量被测试件上指定的测量截面1，得到截面1拟合圆心的空间坐标(x1,y1,z1)；2)通过Z轴带动被测试件整周旋转360°，使用传感器测量被测试件上指定的测量截面2，得到截面2拟合圆心的空间坐标(x2,y2,z2)；3)由(x1,y1,z1)和(x2,y2,z2)计算得到被测试件几何轴线(L)的空间位置，并获得该几何轴线(L)沿X轴方向与Z轴的夹角θx，沿Y轴方向与Z轴的夹角θy；4)依据θx调整被测试件绕Y轴回转运动，回转运动的角度为θx；依据θy调整被测试件绕X轴回转运动，回转运动的角度为θy，从而调整被测试件的几何轴线(L)与回转轴Z尽量重合；5)重复步骤1)～4)，直到被测试件几何轴线(L)沿X轴方向与Z轴的夹角θx小于设定值θx0，沿Y轴方向与Z轴的夹角θy小于设定值θy0，则停止转动运动的调整。
  2. 一种航空发动机转静子装配/测量五自由度调整定位装置，该装置包括装夹机构(1)、转动台部件(A)、平动台部件(B)和回转台部件(C)；其特征在于：
    所述的转动台部件(A)包括台面(2)和底座(3)，台面(2)置于底座(3)上；在所述台面(2)上配置有圆环凸型球碗(4)，在所述底座(3)上配置有圆环凹型球座(5)，所述圆环凹型球座(5)上固连有保持架(6)，在保持架(6)上设有沿圆周方向均匀分布的圆孔(7)，在圆孔(7)内嵌有球径相等的球形滚动体g1；所述的底座(3)上的圆环凹型球座(5)通过球形滚动体g1为台面(2)上的圆环凸型球碗(4)提供支承；在所述的底座(3)上沿X轴配置有弹性限位支承柱(8)和驱动系统Q1(9)，所述弹性限 位支承柱(8)与配置在台面(2)上的限位挡块(10)紧密接触配合，用以防止台面(2)与底座(3)之间有相对转动；所述驱动系统Q1(9)与配置在台面(2)上的传动部件P1(11)相连，用以驱动台面(2)绕Y轴转动；在底座(3)上沿Y轴配置有弹性导向柱(12)和驱动系统Q2(13)，弹性导向柱(12)与配置在台面(2)的导向块(14)接触配合，用以引导台面(2)绕X轴转动；所述驱动系统Q2(13)与配置在台面(2)上的传动部件P2(15)相连，用以驱动台面(2)绕X轴转动；
    驱动系统Q1(9)与驱动系统Q2(13)相邻正交布置，弹性限位支承柱(8)与弹性导向柱(12)相邻正交布置；
    所述装夹机构(1)固连于所述的转动台部件(A)的台面(2)上；
    所述的平动台部件(B)置于转动台部件(A)的下方，带动转动台部件(A)沿X轴和Y轴运动；所述平动台部件(B)包括底板(16)和导向层(17)，在所述导向层(17)上沿圆周方向设置有减重槽(18)，在所述的减重槽(18)内配置有套板(19)；在套板(19)上密布配置有通孔(20)，在通孔(20)内嵌有球径相等的球形滚动体g2；套板(19)通过球形滚动体g2为转动台部件(A)上的底座(3)提供支承；在与驱动系统Q2(13)的对径处配置有驱动系统Q3(21)，用以驱动导向层(17)沿Y轴运动；在与驱动系统Q1(9)的对径处配置有驱动系统Q4(22)，用以驱转动台部件(A)上的底座(3)沿X轴运动；
    所述的回转台部件(C)包括气浮套(23)、气浮轴(24)和回转驱动系统Q5(25)，所述的气浮轴(24)配装在气浮套(23)内，气浮轴(24)的上端与所述的平动台部件(B)的底板(16)固连，气浮轴(24)的下端配置有回转驱动系统Q5(25)，用以驱动气浮轴(24)回转运动。
  3. 根据权利要求2所述的一种航空发动机转静子装配/测量五自由度调整定位装置，其特征在于：在圆孔(7)内嵌入的球形滚动体g1与在通孔(20)内嵌入的球形滚动体g2的球径尺寸相同，或球径尺寸不同。
  4. 根据权利要求2所述的一种航空发动机转静子装配/测量五自由度调整定位装置，其特征在于：X轴与Y轴相互正交，气浮轴(24)的回转轴线垂直于X轴与Y轴所确定的平面。
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