CN110608666B - Aero-engine rotor assembly measuring device based on four-point weighing and three-target optimization method - Google Patents

Aero-engine rotor assembly measuring device based on four-point weighing and three-target optimization method Download PDF

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CN110608666B
CN110608666B CN201910912132.4A CN201910912132A CN110608666B CN 110608666 B CN110608666 B CN 110608666B CN 201910912132 A CN201910912132 A CN 201910912132A CN 110608666 B CN110608666 B CN 110608666B
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rotor
assembly
air
weighing
stage
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CN110608666A (en
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崔继文
陈越
谭久彬
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Harbin Institute of Technology
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    • 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
    • B23P19/10—Aligning parts to be fitted together
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/26—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B7/00—Measuring arrangements characterised by the use of electric or magnetic techniques
    • G01B7/30—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring angles or tapers; for testing the alignment of axes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B7/00—Measuring arrangements characterised by the use of electric or magnetic techniques
    • G01B7/30—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring angles or tapers; for testing the alignment of axes
    • G01B7/31—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring angles or tapers; for testing the alignment of axes for testing the alignment of axes
    • G01B7/312—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring angles or tapers; for testing the alignment of axes for testing the alignment of axes for measuring eccentricity, i.e. lateral shift between two parallel axes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M1/00—Testing static or dynamic balance of machines or structures
    • G01M1/12—Static balancing; Determining position of centre of gravity
    • G01M1/122—Determining position of centre of gravity

Abstract

The invention relates to an aeroengine rotor assembly measuring device based on four-point weighing and a three-target optimization method. Based on a four-measuring-head measuring device, respectively extracting the concentricity error of the radial assembly surface and the parallelism error of the axial assembly surface of each stage of the rotor; respectively extracting radial coordinates of the mass center of each stage of the rotor based on a four-point weighing measuring device; based on a rotor assembly pose transfer model, the optimal assembly angles of the rotors at all levels are obtained by taking the coaxiality, the unbalance amount and the rotational inertia of a rotor assembly body as three optimization targets through genetic optimization; based on the torsion bar measuring device, the longitudinal axis moment of inertia of the assembly body is obtained. The invention can effectively solve the problem of over-standard coaxiality, unbalance and rotational inertia of the rotor of the aero-engine after assembly, and has the characteristics of integrated measurement of geometric and mass characteristics of the rotor, high qualification rate of one-time assembly and reduction of engine vibration.

Description

Aero-engine rotor assembly measuring device based on four-point weighing and three-target optimization method
Technical Field
The invention relates to the technical field of mechanical transfer, in particular to an aeroengine rotor assembly measuring device based on four-point weighing and a three-target optimization method.
Background
The aircraft engine is the most precise and complex rotating machine in the modern industry, and the assembly technology is the final process stage in the engine manufacturing process, particularly the core component represented by a high-pressure compressor rotor, and the assembly quality of the aircraft engine directly influences the high-speed operation stability of the engine.
The rotor coaxiality, the rotor unbalance and the overlarge rotary inertia are all important reasons for causing faults of the aero-engine, and how to realize the synchronous optimization of the rotor coaxiality, the unbalance and the rotary inertia in the assembling stage is a key common technical problem which puzzles the manufacturing industry of the aero-engine at home and abroad for a long time.
At present, research teams at home and abroad mainly improve the assembly quality of multi-stage rotors by changing the assembly phase of each stage of rotor, and Harbin university of industry proposes an aeroengine rotor assembly method and device based on multi-component concentricity optimization (the aeroengine rotor assembly method and device based on multi-component concentricity optimization). The method comprises the steps of firstly, respectively measuring the radial error and the inclination error of the assembly surface of each single-stage rotor, then calculating the influence weight of each rotor on the whole coaxiality of the assembled rotor, and finally, carrying out vector optimization on the weight of each rotor to obtain the optimal assembly angle of each rotor. The method has problems that: the influence of the quality characteristic of the rotor on the assembly quality is not considered, and the optimization of the unbalance amount and the rotational inertia of the rotor cannot be considered while the coaxiality of the rotor reaches the standard.
China aviation Shenyang dawn aeroengine Limited liability company provides an assembly process method for an aeroengine low-pressure turbine rotor (a process method for assembling the aeroengine low-pressure turbine rotor, publication number: CN 109356662A). The method comprises the steps of measuring, grinding, maintaining and fitting the assembly positions by controlling the unbalance amount of a sealing ring, the matching amount of the sealing ring and a low-pressure first-stage turbine disc, measuring the form and position tolerance of a low-pressure first-stage turbine disc and a low-pressure second-stage turbine disc, assembling the low-pressure second-stage turbine disc and a low-pressure turbine shaft layer by layer on an installation base, checking whether the assembled form and position tolerance is qualified layer by layer, assembling the low-pressure first-stage turbine disc and the sealing ring if the assembled form and position tolerance is qualified, tightening through a connecting bolt by means of an adapter and a positioning tool, and checking that the assembled low-pressure first-stage. The method has problems that: the optimal assembly phase of each stage of rotor cannot be directly given, the assembly position can only be fitted layer by layer according to the form and position tolerance of the rotor, and the assembly position fitting of the next stage of rotor can be carried out only after the form and position tolerance of the assembled rotor is checked to be qualified, so that the assembly efficiency is low.
At present, the internal engine rotor assembly technology still depends on the skill level and experience of operators to a great extent, and an optimization method for effectively guiding the assembly of the aircraft engine rotor at a high speed is lacked, so that the coaxiality, the unbalance amount and the rotational inertia index of the rotor are simultaneously met, and the assembly efficiency and the one-time assembly qualification rate of the aircraft engine rotor are greatly improved.
Disclosure of Invention
The invention provides an aeroengine rotor assembly measuring device based on four-point weighing and a three-target optimization method for optimizing rotor coaxiality, unbalance amount and rotational inertia and improving rotor assembly quality, and provides the following technical scheme:
an aircraft engine rotor assembly measuring device based on four-point weighing, the device comprising: the device comprises a base 1, an air flotation shafting 2, a weighing sensor 3, a leveling and inclination adjusting platform 4, a hydraulic chuck 5, a left upright transverse guide rail 6a, a right upright transverse guide rail 6b, a left upright vertical guide rail 7a, a right upright vertical guide rail 7b, a left lower transverse measuring rod 8a, a left upper transverse measuring rod 8b, a right lower transverse measuring rod 8c, a right upper transverse measuring rod 8d, a left lower telescopic inductive sensor 9a, a left upper telescopic inductive sensor 9b, a right lower lever inductive sensor 9c, a right upper lever inductive sensor 9d and a measured rotor 10;
the air-floating shafting 2 comprises an air-floating upper plate 2a, an air-floating main shaft 2b, an air-floating lower plate 2c, a circular grating ruler 2d, a circular grating reading head 2e, a cylinder 2f, a shifting fork 2g, a permanent magnet 2h, a coil 2i, a photoelectric counter 2j, a torsion bar 2k and a torsion bar locking device 2 l;
the weighing sensor 3 comprises a weighing sensor 3a, a weighing sensor 3b, a weighing sensor 3c and a weighing sensor 3d, and the weighing sensor 3a, the weighing sensor 3b, the weighing sensor 3c and the weighing sensor 3d are distributed in a rectangular shape;
the air-floating upper plate 2a is arranged on the upper end part of an air-floating main shaft 2b, the air-floating lower plate 2c is arranged on the lower end part of the air-floating main shaft 2b, a circular grating ruler 2d is arranged on the outer wall of the side surface of the air-floating lower plate 2c, a circular grating reading head 2e is arranged on the inner wall of a base 1 and is transversely aligned with the circular grating ruler 2d, an air cylinder 2f is arranged on the inner wall of the base 1, a shifting fork 2g is arranged on the outer wall of the air-floating lower plate 2c, a permanent magnet 2h is arranged on the outer ring of the air-floating main shaft 2b, a coil 2i is arranged on the outer ring of the air-floating main shaft 2b and is longitudinally aligned with the permanent magnet 2h, a photoelectric counter 2j is arranged on the outer ring of the air-floating lower plate 2c, a torsion bar 2k is arranged on the central position of the air-, a leveling and inclination-adjusting platform 4 is arranged on a weighing sensor 3, the leveling and inclination-adjusting platform 4 is positioned on the central position of an air floating shaft system 2, a hydraulic chuck 5 is arranged on the central position of the leveling and inclination-adjusting platform 4, a left upright post transverse guide rail 6a and a right upright post transverse guide rail 6b are symmetrically distributed on two sides of the air floating shaft system 2 and are fixedly arranged on a base 1, a left upright post vertical guide rail 7a is arranged on the left upright post transverse guide rail 6a, a right upright post vertical guide rail 7b is arranged on the right upright post transverse guide rail 6b, a left lower transverse measuring rod 8a and a left upper transverse measuring rod 8b are horizontally nested on the left upright post vertical guide rail 7a, a right lower transverse measuring rod 8c and a right upper transverse measuring rod 8d are horizontally nested on the right upright post vertical guide rail 7b, a left lower telescopic inductive sensor 9a is arranged at the end part of the left lower transverse measuring rod 8a, a left upper telescopic inductive sensor, the right upper lever type inductive sensor 9c is arranged at the end part of the right upper transverse measuring rod 8c, the right lower lever type inductive sensor 9d is arranged at the end part of the right lower transverse measuring rod 8d, and the measured rotor 10 is arranged on the hydraulic chuck 5.
Preferably, the load cell is a SBS shear Beam load cell of Mettler-Toriledo.
A three-target optimization method for rotor assembly of an aircraft engine based on four-point weighing is based on a four-point weighing based rotor assembly measuring device of the aircraft engine, and comprises the following steps:
step 1: aligning and adjusting the leveling and inclination adjusting platform 4, ensuring that the centroid of the assembly reference surface is concentric with the rotation axis of the leveling and inclination adjusting platform 4 shaft system, ensuring that the assembly reference surface is parallel to the leveling and inclination adjusting platform 4 plane, ensuring that the assembly reference is the bottom surface of the bottom layer rotor, taking the rotation axis of the air floatation shaft system 2 as the Z axis, taking the intersection point of the rotation axis and the upper surface of the air floatation upper plate 2a as the origin of coordinates, taking a straight line which passes through the origin of coordinates and is transversely parallel to the base 1 as the X axis, and taking a straight line which passes through the origin of coordinates and is perpendicular to the X axis as the Y axis;
step 2: measuring the concentricity and the parallelism of each single-stage rotor to obtain the concentricity and the parallelism of the measured rotor 10;
and step 3: measuring the mass center coordinate of each single-stage rotor to obtain the mass center coordinate of the measured rotor 10;
and 4, step 4: optimizing three targets of coaxiality, unbalance and longitudinal axis moment of inertia of the multistage rotor to obtain an optimal assembly angle of the measured rotor 10;
and 5: assembling the single-stage rotors together according to the optimal assembly angle of the rotors at each stage;
step 6: and detecting the coaxiality, the mass center offset and the rotational inertia of the assembly to ensure that the assembly requirement indexes are met.
Preferably, the step 1 of aligning and tilt adjusting the leveling and tilt adjusting table 4 specifically includes:
step 1.1: a measured rotor 10 is placed on the leveling and inclination adjusting platform 4 and fixed through a hydraulic chuck 5, and a right lower lever type inductive sensor 9c and a right upper lever type inductive sensor 9d are in contact with a radial assembly reference surface of the measured rotor 10 and used for aligning; contacting a left lower telescopic inductive sensor 9a and a left upper telescopic inductive sensor 9b with an axial assembly reference surface of a measured rotor 10 for adjusting inclination;
step 1.2: the air flotation shafting 2 drives the measured rotor 10 to uniformly rotate at the speed of 6r/min to 10r/min through the leveling and inclination adjusting platform 4, the right lower lever type inductive sensor 9c and the right upper lever type inductive sensor 9d perform equal-interval sampling on the radial assembly reference surface of the measured rotor 10, the left lower telescopic inductive sensor 9a and the left upper telescopic inductive sensor 9b perform equal-interval sampling on the axial assembly reference surface of the measured rotor 10, and the number of sampling points meets the requirement of 1000 to 2000 points per circle; performing least square circle fitting on the sampled data on the radial assembly datum plane of the measured rotor 10 to obtain an eccentricity, and performing least square plane fitting on the sampled data on the axial assembly datum plane of the measured rotor 10 to obtain an inclination;
step 1.3: and adjusting the aligning knob of the leveling and inclination adjusting platform 4 according to the size and the angle of the eccentric amount, and adjusting the inclination adjusting knob of the leveling and inclination adjusting platform 4 according to the size and the angle of the inclination amount until the leveling and inclination adjusting platform 4 meets the condition that the size of the eccentric amount of the radial reference surface is in the range of 0 to 3 mu m and the size of the inclination amount of the axial reference surface is in the range of 0 to 2'.
Preferably, the step 2 specifically comprises:
step 2.1: contacting a right lower lever type inductive sensor 9c and a right upper lever type inductive sensor 9d with a radial assembly measuring surface of a measured rotor 10, contacting a left lower telescopic inductive sensor 9a and a left upper telescopic inductive sensor 9b with an axial assembly measuring surface of the measured rotor 10, and enabling an air floatation shaft system 2 to rotate at a constant speed of 6r/min to 10 r/min;
step 2.2: sampling at equal intervals on the radial assembly measuring surface of the measured rotor 10 by adopting a right lower lever type inductive sensor 9c and a right upper lever type inductive sensor 9d, sampling at equal intervals on the axial assembly measuring surface of the measured rotor 10 by adopting a left lower telescopic inductive sensor 9a and a left upper telescopic inductive sensor 9b, and counting the number of sampling points to meet 1000-2000 points per circle;
step 2.3: and carrying out least square circle fitting on the sampled data on the radial assembly measuring surface of the measured rotor 10 to obtain concentricity, carrying out least square plane fitting on the sampled data on the axial assembly measuring surface of the measured rotor 10 to obtain parallelism, and simultaneously recording corresponding phase angles of all points by adopting a circular grating reading head 2 e.
Preferably, the step 3 specifically comprises:
step 3.1: taking the rotation center of the air floatation shaft system 2 as a total reference, and installing a weighing sensor 3a, a weighing sensor 3b, a weighing sensor 3c and a weighing sensor 3d on the table surface of an air floatation upper plate 2a in a rectangular distribution;
step 3.2, symmetrically arranging a weighing sensor 3a and a weighing sensor 3d on two sides of an X axis, wherein the distance between the connecting lines of the bearing points of the weighing sensor 3a and the weighing sensor 3d is H and is parallel to the Y axis, symmetrically arranging a weighing sensor 3b and a weighing sensor 3c on two sides of the X axis, wherein the connecting line of the bearing points of the weighing sensor 3b and the weighing sensor 3c is parallel to the Y axis, the distance between the connecting lines of the bearing points of the weighing sensor 3a and the weighing sensor 3b is L and is parallel to the X axis, and the weighing sensor 3a and the weighing sensor 3b are symmetrical relative to the Y axis;
step 3.3: measuring to obtain the barycenter coordinate of the measured rotor 10; the barycentric coordinates of the measured rotor 10 are represented by:
Figure BDA0002215051190000041
wherein M is the weight of the measured rotor 10, F1、F2、F3And F4Difference between no-load and load of load cell 3a, load cell 3b, load cell 3c and load cell 3d, GxIs the abscissa of the centroid of the measured rotor 10; gyIs the ordinate of the centroid of the measured rotor 10.
Preferably, the step 4 specifically includes:
step 4.1: establishing a calculation model for predicting the concentricity and the mass center coordinates of the rotor after the multi-stage rotor is transferred, and expressing the calculation model by the following formula:
Figure BDA0002215051190000042
Figure BDA0002215051190000043
Figure BDA0002215051190000051
wherein, XQiAnd XHiAssembly face centroid coordinate vectors, ZQ, before and after assembly of the i-th rotoriAnd ZHiRespectively are mass center coordinate vectors before and after the i-th-stage rotor is assembled; rziA rotation matrix of the ith-stage rotor around the Z axis of the top surface of the ith-1-stage rotor; ryiA rotation matrix of the ith-stage rotor around a total reference Y axis; h isiParallelism measured for the i-th rotor; c. CiConcentricity measured for the i-th stage rotor; hiIs the ith stage rotor height; thetaziThe angle of the ith-stage rotor rotating around the Z axis on the top surface of the ith-1-stage rotor;
determining the concentricity of the ith-stage rotor after the multi-stage rotor is matched, and expressing the concentricity of the ith-stage rotor after the multi-stage rotor is matched by the following formula:
Figure BDA0002215051190000052
wherein, CHiFor the concentricity, XH, of i-th rotor after the rotor has been rotatably coupled to more than one rotori(x)Assembling the abscissa of the face centroid after the i-th-stage rotor is assembled; XHi(y)Assembling the ordinate of the face centroid for the i-th rotor after assembly;
determining the centroid coordinate vector of the whole assembly body after the assembly of the multistage rotors, and representing the centroid coordinate vector of the whole assembly body after the assembly of the multistage rotors by the following formula:
Figure BDA0002215051190000053
wherein ZH is the mass center coordinate vector of the whole assembly body after the assembly of the multistage rotors, ZHiAssembling a centroid coordinate vector for the ith-stage rotor; miIs the i-th stage rotor weight;
determining the moment of inertia of the longitudinal shaft of the ith-stage rotor after the multistage rotor is assembled, and expressing the moment of inertia of the longitudinal shaft of the ith-stage rotor after the multistage rotor is assembled by the following formula:
JHi＝(ZHi(x) 2+ZHi(y) 2)Mi(7)
wherein JHiThe moment of inertia of the longitudinal axis of the ith-stage rotor after the multistage rotor is assembled;
step 4.2: establishing an optimization target, wherein the optimization target is three targets, namely, the unbalance amount of the whole coaxiality and the moment of inertia of the longitudinal axis after the multi-stage rotor is assembled, the coaxiality is the maximum value of the concentricity of each single-stage rotor after the rotors are assembled, and the coaxiality is calculated by the following formula:
c＝max{CHi,i＝1,2,...,n} (8)
wherein c is the coaxiality, and n is the number of rotor stages;
the unbalance amount is the product of the total mass of the assembly body and the mass center offset, and the mass center offset and the unbalance amount are represented by the following formula:
Figure BDA0002215051190000061
Figure BDA0002215051190000062
wherein, ZHxAs the abscissa of the centroid of the entire assembly, ZHyIs the ordinate of the mass center of the whole assembly body;
the moment of inertia of the longitudinal axis, which is the product of the total mass of the fitting body and the square of the offset of the center of mass, is expressed by the following equation:
Figure BDA0002215051190000063
wherein J is the moment of inertia of the longitudinal axis;
step 4.3: establishing a tri-objective minimization function, which is expressed by the following formula:
Figure BDA0002215051190000064
wherein the content of the first and second substances,
Figure BDA0002215051190000065
in order to be the objective function, the target function,
Figure BDA0002215051190000066
is a vector formed by the assembly angles of the single-stage rotors; thetaznThe angle of the nth-stage rotor rotating around the normal axis of the top surface of the nth-1 stage rotor,
Figure BDA0002215051190000067
optimizing a function for a single target based on coaxiality;
Figure BDA0002215051190000068
for monocular based on centroid offsetThe function is optimized on the basis of the standard,
Figure BDA0002215051190000069
a single objective optimization function based on the amount of unbalance is represented,
Figure BDA00022150511900000610
representing a single objective optimization function based on the moment of inertia;
step 4.4: converting the three-target minimization function into a fitness function of the genetic algorithm, and expressing the fitness function of the genetic algorithm by the following formula:
Figure BDA00022150511900000611
Figure BDA00022150511900000612
wherein, c△For the minimum value of the coaxiality-based single-objective optimization function, U△For the minimum of a single-objective optimization function based on the amount of unbalance, J△Is the minimum value of a single-target optimization function based on the moment of inertia;
step 4.5: obtaining the optimal transfer angle theta of each stage of rotor through a genetic algorithmziAnd the coaxiality, the unbalance amount and the rotational inertia are close to the minimum value of each single target optimization, so that the coaxiality, the unbalance amount and the rotational inertia of the rotor are simultaneously optimized under the same assembly reference.
Preferably, the polarity of the longitudinal axis moment of inertia of the assembly is measured, and the idle period T of the bearing rotary table is measured0Moment of inertia J of the turntable0＝AT0 2Measuring common runout period Ts of a standard sample and a bearing rotary table, wherein the rotational inertia of the standard sample is Js, and obtaining a proportionality coefficient
Figure BDA0002215051190000071
Measuring the common-pendulum period T of the measured rotor and the bearing rotary table, and measuring the longitudinal axis moment of inertia J of the measured assembly bodyc＝A(T2-T0 2)。
Preferably, a torsion bar 2k is locked through a torsion bar locking device 2l, and a cylinder 2f pushes a shifting fork 2g to drive an air floatation shaft system 2 to generate micro angular displacement; the air cylinder 2f is loosened, and the air floatation shaft system 2 generates periodic compound pendulum motion under the action of the elastic restoring force of the torsion bar 2 k; the photoelectric counter 2j records the runout period of the air floatation shaft system 2.
The invention has the following beneficial effects:
the existing aircraft engine rotor assembly optimization method only optimizes the overall coaxiality of the assembled multistage rotor so as to realize the optimized assembly of the assembled multistage rotor from the angle of geometric quantity without generating excessive bending of an assembly axis. The assembly optimization method comprehensively considers the geometric and mass characteristics of the multistage rotor, can realize multi-target synchronous optimization of the integral coaxiality, the unbalance amount and the rotational inertia of the assembled multistage rotor, can control the assembly axis not to generate transition bending, and can control the unbalance amount and the rotational inertia of the rotor within an allowable range. The existing aeroengine rotor assembly measuring device can only extract geometric information centroid coordinates, concentricity, parallelism, height and the like of a measured rotor, and cannot extract the total mass, centroid coordinates and rotational inertia of the measured rotor at the same time. The measuring device can realize the integrated measurement of the geometric quantity and the quality information of the measured rotor.
Drawings
FIG. 1 is a flow chart of a four-point weighing-based three-target optimization method for aircraft engine rotor assembly;
FIG. 2 is a schematic view of an aircraft engine rotor assembly measurement device based on four-point weighing;
FIG. 3 is a schematic view of the arrangement of the measurement air-floating axis system and the circular grating;
FIG. 4 is a schematic view of a load cell distribution;
fig. 5 is a schematic diagram comparing the pre-optimization fitting effect with the post-optimization fitting effect. Fig. 5-a shows the assembly effect before optimization, and fig. 5-b shows the assembly effect after optimization.
Detailed Description
The present invention will be described in detail with reference to specific examples.
The first embodiment is as follows:
according to fig. 2 and 3, the invention provides a four-point weighing-based aeroengine rotor assembly measuring device, comprising: the device comprises a base 1, an air flotation shafting 2, a weighing sensor 3, a leveling and inclination adjusting platform 4, a hydraulic chuck 5, a left upright transverse guide rail 6a, a right upright transverse guide rail 6b, a left upright vertical guide rail 7a, a right upright vertical guide rail 7b, a left lower transverse measuring rod 8a, a left upper transverse measuring rod 8b, a right lower transverse measuring rod 8c, a right upper transverse measuring rod 8d, a left lower telescopic inductive sensor 9a, a left upper telescopic inductive sensor 9b, a right lower lever inductive sensor 9c, a right upper lever inductive sensor 9d and a measured rotor 10;
the air-floating shafting 2 comprises an air-floating upper plate 2a, an air-floating main shaft 2b, an air-floating lower plate 2c, a circular grating ruler 2d, a circular grating reading head 2e, a cylinder 2f, a shifting fork 2g, a permanent magnet 2h, a coil 2i, a photoelectric counter 2j, a torsion bar 2k and a torsion bar locking device 2 l;
the air-floating upper plate 2a is arranged on the upper end part of an air-floating main shaft 2b, the air-floating lower plate 2c is arranged on the lower end part of the air-floating main shaft 2b, a circular grating ruler 2d is arranged on the outer wall of the side surface of the air-floating lower plate 2c, a circular grating reading head 2e is arranged on the inner wall of a base 1 and is transversely aligned with the circular grating ruler 2d, an air cylinder 2f is arranged on the inner wall of the base 1, a shifting fork 2g is arranged on the outer wall of the air-floating lower plate 2c, a permanent magnet 2h is arranged on the outer ring of the air-floating main shaft 2b, a coil 2i is arranged on the outer ring of the air-floating main shaft 2b and is longitudinally aligned with the permanent magnet 2h, a photoelectric counter 2j is arranged on the outer ring of the air-floating lower plate 2c, a torsion bar 2k is arranged on the central position of the air-, a leveling and inclination-adjusting platform 4 is arranged on a weighing sensor 3, the leveling and inclination-adjusting platform 4 is positioned on the central position of an air floating shaft system 2, a hydraulic chuck 5 is arranged on the central position of the leveling and inclination-adjusting platform 4, a left upright post transverse guide rail 6a and a right upright post transverse guide rail 6b are symmetrically distributed on two sides of the air floating shaft system 2 and are fixedly arranged on a base 1, a left upright post vertical guide rail 7a is arranged on the left upright post transverse guide rail 6a, a right upright post vertical guide rail 7b is arranged on the right upright post transverse guide rail 6b, a left lower transverse measuring rod 8a and a left upper transverse measuring rod 8b are horizontally arranged on the left upright post vertical guide rail 7a, a right lower transverse measuring rod 8c and a right upper transverse measuring rod 8d are horizontally arranged on the right upright post vertical guide rail 7b, a left lower telescopic inductive sensor 9a is arranged at the end part of the left lower transverse measuring rod 8a, a left upper telescopic inductive sensor, the right upper lever type inductive sensor 9c is arranged at the end part of the right upper transverse measuring rod 8c, the right lower lever type inductive sensor 9d is arranged at the end part of the right lower transverse measuring rod 8d, and the measured rotor 10 is arranged on the hydraulic chuck 5.
According to fig. 4, load cell 3 comprises load cell 3a, load cell 3b, load cell 3c and load cell 3d, wherein load cell 3a, load cell 3b, load cell 3c and load cell 3d are distributed in a rectangular pattern, and the load cell is a SBS shear beam type load cell having a midler-toledo structure.
The grating reading head is arranged on the side face of the air floatation lower plate, the circular grating ruler is arranged on the inner wall of the base, and when the permanent magnet is matched with the coil to drive the rotary table to rotate, the grating reading head is matched with the circular grating ruler to record the rotation angle information of the rotary table, and sampling is performed according to the angle of the circular grating.
The double measuring rods are symmetrically arranged at two sides of the air floatation rotary table, carry four differential sensors and a measuring system, ensure that the phase of the double measuring rods opposite to the sensors is 180 degrees through four groups of line lasers, and align to the rotation axis of the air floatation shaft system.
The second embodiment is as follows:
according to the figure 1, the invention provides a three-target optimization method for the assembly of an aircraft engine rotor based on four-point weighing, which comprises the following steps:
step 1: aligning and adjusting the leveling and inclination adjusting platform 4, ensuring that the centroid of the assembly reference surface is concentric with the rotation axis of the leveling and inclination adjusting platform 4 shaft system, ensuring that the assembly reference surface is parallel to the leveling and inclination adjusting platform 4 plane, ensuring that the assembly reference is the bottom surface of the bottom layer rotor, taking the rotation axis of the air floatation shaft system 2 as the Z axis, taking the intersection point of the rotation axis and the upper surface of the air floatation upper plate 2a as the origin of coordinates, taking a straight line which passes through the origin of coordinates and is transversely parallel to the base 1 as the X axis, and taking a straight line which passes through the origin of coordinates and is perpendicular to the X axis as the Y axis;
the step 1 of aligning and inclination adjusting of the aligning and inclination adjusting platform 4 is as follows:
step 1.1: a measured rotor 10 is placed on the leveling and inclination adjusting platform 4 and fixed through a hydraulic chuck 5, and a right lower lever type inductive sensor 9c and a right upper lever type inductive sensor 9d are in contact with a radial assembly reference surface of the measured rotor 10 and used for aligning; contacting a left lower telescopic inductive sensor 9a and a left upper telescopic inductive sensor 9b with an axial assembly reference surface of a measured rotor 10 for adjusting inclination;
step 1.2: the air flotation shafting 2 drives the measured rotor 10 to uniformly rotate at the speed of 6-10 r/min through the leveling and inclination adjusting platform 4, the right lower lever type inductive sensor 9c and the right upper lever type inductive sensor 9d perform equal-interval sampling on the radial assembly reference surface of the measured rotor 10, the left lower telescopic inductive sensor 9a and the left upper telescopic inductive sensor 9b perform equal-interval sampling on the axial assembly reference surface of the measured rotor 10, and the number of sampling points meets 1000-2000 points per circle; performing least square circle fitting on the sampled data on the radial assembly datum plane of the measured rotor 10 to obtain an eccentricity, and performing least square plane fitting on the sampled data on the axial assembly datum plane of the measured rotor 10 to obtain an inclination;
step 1.3: and adjusting the aligning knob of the leveling and inclination adjusting platform 4 according to the size and the angle of the eccentric amount, and adjusting the inclination adjusting knob of the leveling and inclination adjusting platform 4 according to the size and the angle of the inclination amount until the leveling and inclination adjusting platform 4 meets the requirements that the size of the eccentric amount of the radial reference surface is in the range of 0-3 mu m, and the size of the inclination amount of the axial reference surface is in the range of 0-2'.
Step 2: measuring the concentricity and the parallelism of each single-stage rotor to obtain the concentricity and the parallelism of the measured rotor 10;
the step 2 specifically comprises the following steps:
step 2.1: contacting a lower right lever type inductive sensor 9c and an upper right lever type inductive sensor 9d with a radial assembly measuring surface of a measured rotor 10, contacting a lower left telescopic inductive sensor 9a and an upper left telescopic inductive sensor 9b with an axial assembly measuring surface of the measured rotor 10, and enabling an air floatation shaft system 2 to rotate at a constant speed of 6-10 r/min;
step 2.2: sampling at equal intervals on the radial assembly measuring surface of the measured rotor 10 by adopting a right lower lever type inductive sensor 9c and a right upper lever type inductive sensor 9d, sampling at equal intervals on the axial assembly measuring surface of the measured rotor 10 by adopting a left lower telescopic inductive sensor 9a and a left upper telescopic inductive sensor 9b, and counting the number of sampling points to meet 1000-2000 points per circle;
step 2.3: and carrying out least square circle fitting on the sampled data on the radial assembly measuring surface of the measured rotor 10 to obtain concentricity, carrying out least square plane fitting on the sampled data on the axial assembly measuring surface of the measured rotor 10 to obtain parallelism, and simultaneously recording corresponding phase angles of all points by adopting a circular grating reading head 2 e.
And step 3: measuring the mass center coordinate of each single-stage rotor to obtain the mass center coordinate of the measured rotor 10;
the step 3 specifically comprises the following steps:
step 3.1: taking the rotation center of the air floatation shaft system 2 as a total reference, and installing a weighing sensor 3a, a weighing sensor 3b, a weighing sensor 3c and a weighing sensor 3d on the table surface of an air floatation upper plate 2a in a rectangular distribution;
step 3.2, symmetrically arranging a weighing sensor 3a and a weighing sensor 3d on two sides of an X axis, wherein the distance between the connecting lines of the bearing points of the weighing sensor 3a and the weighing sensor 3d is H and is parallel to the Y axis, symmetrically arranging a weighing sensor 3b and a weighing sensor 3c on two sides of the X axis, wherein the connecting line of the bearing points of the weighing sensor 3b and the weighing sensor 3c is parallel to the Y axis, the distance between the connecting lines of the bearing points of the weighing sensor 3a and the weighing sensor 3b is L and is parallel to the X axis, and the weighing sensor 3a and the weighing sensor 3b are symmetrical relative to the Y axis;
step 3.3: measuring to obtain the barycenter coordinate of the measured rotor 10; the barycentric coordinates of the measured rotor 10 are represented by:
Figure BDA0002215051190000101
wherein M is the weight of the measured rotor 10, F1、F2、F3And F4Difference between no-load and load of load cell 3a, load cell 3b, load cell 3c and load cell 3d, GxIs the abscissa of the centroid of the measured rotor 10; gyIs the ordinate of the centroid of the measured rotor 10.
And 4, step 4: optimizing three targets of coaxiality, unbalance and longitudinal axis moment of inertia of the multistage rotor to obtain an optimal assembly angle of the measured rotor 10;
step 4.1: establishing a calculation model for predicting the concentricity and the mass center coordinates of the rotor after the multi-stage rotor is transferred, and expressing the calculation model by the following formula:
Figure BDA0002215051190000102
Figure BDA0002215051190000103
Figure BDA0002215051190000111
wherein, XQiAnd XHiAssembly face centroid coordinate vectors, ZQ, before and after assembly of the i-th rotoriAnd ZHiRespectively are mass center coordinate vectors before and after the i-th-stage rotor is assembled; rziA rotation matrix of the ith-stage rotor around the Z axis of the top surface of the ith-1-stage rotor; ryiA rotation matrix of the ith-stage rotor around a total reference Y axis; h isiParallelism measured for the i-th rotor; c. CiConcentricity measured for the i-th stage rotor; hiIs the ith stage rotor height; thetaziThe angle of the ith-stage rotor rotating around the Z axis on the top surface of the ith-1-stage rotor;
determining the concentricity of the ith-stage rotor after the multi-stage rotor is matched, and expressing the concentricity of the ith-stage rotor after the multi-stage rotor is matched by the following formula:
Figure BDA0002215051190000112
wherein, CHiFor the concentricity, XH, of i-th rotor after the rotor has been rotatably coupled to more than one rotori(x)Assembling the abscissa of the face centroid after the i-th-stage rotor is assembled; XHi(y)Assembling the ordinate of the face centroid for the i-th rotor after assembly;
determining the centroid coordinate vector of the whole assembly body after the assembly of the multistage rotors, and representing the centroid coordinate vector of the whole assembly body after the assembly of the multistage rotors by the following formula:
Figure BDA0002215051190000113
wherein ZH is the mass center coordinate vector of the whole assembly body after the assembly of the multistage rotors, ZHiAssembling a centroid coordinate vector for the ith-stage rotor; miIs the i-th stage rotor weight;
determining the moment of inertia of the longitudinal shaft of the ith-stage rotor after the multistage rotor is assembled, and expressing the moment of inertia of the longitudinal shaft of the ith-stage rotor after the multistage rotor is assembled by the following formula:
JHi＝(ZHi(x) 2+ZHi(y) 2)Mi(7)
wherein JHiThe moment of inertia of the longitudinal axis of the ith-stage rotor after the multistage rotor is assembled;
step 4.2: establishing an optimization target, wherein the optimization target is three targets, namely, the unbalance amount of the whole coaxiality and the moment of inertia of the longitudinal axis after the multi-stage rotor is assembled, the coaxiality is the maximum value of the concentricity of each single-stage rotor after the rotors are assembled, and the coaxiality is calculated by the following formula:
c＝max{CHi,i＝1,2,...,n} (8)
wherein c is the coaxiality, and n is the number of rotor stages;
the unbalance amount is the product of the total mass of the assembly body and the mass center offset, and the mass center offset and the unbalance amount are represented by the following formula:
Figure BDA0002215051190000121
Figure BDA0002215051190000122
wherein, ZHxAs the abscissa of the centroid of the entire assembly, ZHyIs the ordinate of the mass center of the whole assembly body;
the moment of inertia of the longitudinal axis, which is the product of the total mass of the fitting body and the square of the offset of the center of mass, is expressed by the following equation:
Figure BDA0002215051190000123
wherein J is the moment of inertia of the longitudinal axis;
step 4.3: establishing a tri-objective minimization function, which is expressed by the following formula:
Figure BDA0002215051190000124
wherein the content of the first and second substances,
Figure BDA0002215051190000125
in order to be the objective function, the target function,
Figure BDA0002215051190000126
is a vector formed by the assembly angles of the single-stage rotors; thetaznThe angle of the nth-stage rotor rotating around the normal axis of the top surface of the nth-1 stage rotor,
Figure BDA0002215051190000127
optimizing a function for a single target based on coaxiality;
Figure BDA0002215051190000128
for a single objective optimization function based on centroid offsets,
Figure BDA0002215051190000129
a single objective optimization function based on the amount of unbalance is represented,
Figure BDA00022150511900001210
representing a single objective optimization function based on the moment of inertia;
step 4.4: converting the three-target minimization function into a fitness function of the genetic algorithm, and expressing the fitness function of the genetic algorithm by the following formula:
Figure BDA00022150511900001211
Figure BDA00022150511900001212
wherein, c△For the minimum value of the coaxiality-based single-objective optimization function, U△For the minimum of a single-objective optimization function based on the amount of unbalance, J△Is the minimum value of a single-target optimization function based on the moment of inertia;
step 4.5: obtaining the optimal transfer angle theta of each stage of rotor through a genetic algorithmziAnd the coaxiality, the unbalance amount and the rotational inertia are close to the minimum value of each single target optimization, so that the coaxiality, the unbalance amount and the rotational inertia of the rotor are simultaneously optimized under the same assembly reference.
And 5: assembling the single-stage rotors together according to the optimal assembly angle of the rotors at each stage;
step 6: and detecting the coaxiality, the mass center offset and the rotational inertia of the assembly to ensure that the assembly requirement indexes are met.
A torsion bar 2k is locked by a torsion bar locking device 2l, and a cylinder 2f pushes a shifting fork 2g to drive an air floatation shaft system 2 to generate micro angular displacement; the air cylinder 2f is loosened, and the air floatation shaft system 2 generates periodic compound pendulum motion under the action of the elastic restoring force of the torsion bar 2 k; the photoelectric counter 2j records the runout period of the air floatation shaft system 2.
The grating reading head 2e is arranged on the side surface of the air floatation lower plate 2c, the circular grating ruler 2d is arranged on the inner wall of the base 1, when the permanent magnet 2h is matched with the coil 2i to drive the rotary table to rotate, the grating reading head 2e is matched with the circular grating ruler 2d to record the rotation angle information of the rotary table, and sampling is carried out according to the angle of the circular grating.
The above description is only a preferred embodiment of the four-point weighing-based aeroengine rotor assembly measuring device and the three-target optimization method, and the protection range of the four-point weighing-based aeroengine rotor assembly measuring device and the three-target optimization method is not limited to the above embodiments, and all technical solutions belonging to the idea belong to the protection range of the invention. It should be noted that modifications and variations which do not depart from the gist of the invention will be those skilled in the art to which the invention pertains and which are intended to be within the scope of the invention.

Claims (7)

1. A three-target optimization method for aircraft engine rotor assembly based on four-point weighing is based on an aircraft engine rotor assembly measuring device based on four-point weighing, and the device comprises: the device comprises a base (1), an air floatation shaft system (2), a weighing sensor (3), a leveling and inclining platform (4), a hydraulic chuck (5), a left upright transverse guide rail (6a), a right upright transverse guide rail (6b), a left upright vertical guide rail (7a), a right upright vertical guide rail (7b), a left lower transverse measuring rod (8a), a left upper transverse measuring rod (8b), a right lower transverse measuring rod (8c), a right upper transverse measuring rod (8d), a left lower telescopic inductive sensor (9a), a left upper telescopic inductive sensor (9b), a right lower lever inductive sensor (9c), a right upper lever inductive sensor (9d) and a measured rotor (10);
the air-floating shafting (2) comprises an air-floating upper plate (2a), an air-floating main shaft (2b), an air-floating lower plate (2c), a circular grating ruler (2d), a circular grating reading head (2e), a cylinder (2f), a shifting fork (2g), a permanent magnet (2h), a coil (2i), a photoelectric counter (2j), a torsion bar (2k) and a torsion bar locking device (2 l);
the weighing sensors (3) comprise a first weighing sensor (3a), a second weighing sensor (3b), a third weighing sensor (3c) and a fourth weighing sensor (3d), and the first weighing sensor (3a), the second weighing sensor (3b), the third weighing sensor (3c) and the fourth weighing sensor (3d) are distributed in a rectangular shape;
the air-floating type air-floating device is characterized in that an air-floating upper plate (2a) is installed on the upper end part of an air-floating main shaft (2b), an air-floating lower plate (2c) is installed on the lower end part of the air-floating main shaft (2b), a circular grating ruler (2d) is installed on the outer wall of the side surface of the air-floating lower plate (2c), a circular grating reading head (2e) is installed on the inner wall of a base (1) and is transversely aligned with the circular grating ruler (2d), an air cylinder (2f) is installed on the inner wall of the base (1), a shifting fork (2g) is installed on the outer wall of the air-floating lower plate (2c), a permanent magnet (2h) is installed on the outer ring of the air-floating main shaft (2b), a coil (2i) is installed on the outer ring of the main shaft (2b), the coil (2i) is longitudinally aligned with the permanent magnet (2h), an photoelectric counter (, the torsion bar locking device (2l) is arranged at the bottom of the base (1), the torsion bar locking device (2l) is symmetrically distributed at two sides of a torsion bar (2k), the weighing sensor (3) is arranged on an air-floating upper plate (2a), the leveling and inclination-adjusting platform (4) is arranged on the weighing sensor (3), the leveling and inclination-adjusting platform (4) is positioned at the central position of an air-floating shaft system (2), the hydraulic chuck (5) is arranged at the central position of the leveling and inclination-adjusting platform (4), the left upright transverse guide rail (6a) and the right upright transverse guide rail (6b) are symmetrically distributed at two sides of the air-floating shaft system (2) and are fixedly arranged on the base (1), the left upright vertical guide rail (7a) is arranged on the left upright transverse guide rail (6a), the right upright vertical guide rail (7b) is arranged on the right upright transverse guide rail (6b), the left lower transverse measuring bar (8a) and the left upper transverse measuring bar (8b) are horizontally nested on the left upright vertical guide rail (, horizontal measuring rod (8c) and upper right horizontal survey (8d) level nestification are on vertical guide rail (7b) of right side stand down, lower left telescopic inductive sensor (9a) are installed in horizontal measuring rod (8a) tip under a left side, telescopic inductive sensor (9b) are installed in upper left horizontal measuring rod (8b) tip, lever inductive sensor (9c) are installed in upper right horizontal measuring rod (8c) tip, lever inductive sensor (9d) are installed in horizontal measuring rod (8d) tip under the right side down, surveyed rotor (10) are installed on hydraulic chuck (5), characterized by: the method comprises the following steps:
step 1: aligning and adjusting the leveling and inclination adjusting platform (4), ensuring that the centroid of the assembly reference surface is concentric with the rotation axis of the leveling and inclination adjusting platform (4), ensuring that the assembly reference surface is parallel to the plane of the leveling and inclination adjusting platform (4), ensuring that the assembly reference is the bottom surface of the bottom layer rotor, taking the rotation axis of the air floatation axis system (2) as the Z axis, taking the intersection point of the rotation axis and the upper surface of the air floatation upper plate (2a) as the origin of coordinates, taking a straight line which passes through the origin of coordinates and is transversely parallel to the base (1) as the X axis, and taking a straight line which passes through the origin of coordinates and is perpendicular to the X axis as the Y axis;
step 2: measuring the concentricity and the parallelism of each single-stage rotor to obtain the concentricity and the parallelism of the measured rotor (10);
and step 3: measuring the mass center coordinate of each single-stage rotor to obtain the mass center coordinate of the measured rotor (10);
and 4, step 4: optimizing three targets of coaxiality, unbalance and longitudinal axis moment of inertia of the multistage rotor to obtain the optimal assembly angle of the measured rotor (10);
the step 4 specifically comprises the following steps:
step 4.1: establishing a calculation model for predicting the concentricity and the mass center coordinates of the rotor after the multi-stage rotor is transferred, and expressing the calculation model by the following formula:
Figure FDA0002529991140000021
Figure FDA0002529991140000022
Figure FDA0002529991140000023
wherein, XQiAnd XHiAssembly face centroid coordinate vectors, ZQ, before and after assembly of the i-th rotoriAnd ZHiRespectively are mass center coordinate vectors before and after the i-th-stage rotor is assembled; rziA rotation matrix of the ith-stage rotor around the Z axis of the top surface of the ith-1-stage rotor; ryiA rotation matrix of the ith-stage rotor around a total reference Y axis; h isiParallelism measured for the i-th rotor; c. CiConcentricity measured for the i-th stage rotor; hiIs the ith stage rotor height; thetaziThe angle of the ith-stage rotor rotating around the Z axis on the top surface of the ith-1-stage rotor;
determining the concentricity of the ith-stage rotor after the multi-stage rotor is matched, and expressing the concentricity of the ith-stage rotor after the multi-stage rotor is matched by the following formula:
Figure FDA0002529991140000031
wherein, CHiFor the concentricity, XH, of i-th rotor after the rotor has been rotatably coupled to more than one rotori(x)Assembling the abscissa of the face centroid after the i-th-stage rotor is assembled; XHi(y)Assembling the ordinate of the face centroid for the i-th rotor after assembly;
determining the centroid coordinate vector of the whole assembly body after the assembly of the multistage rotors, and representing the centroid coordinate vector of the whole assembly body after the assembly of the multistage rotors by the following formula:
Figure FDA0002529991140000032
wherein ZH is the mass center coordinate vector of the whole assembly body after the assembly of the multistage rotors, ZHiAssembling a centroid coordinate vector for the ith-stage rotor; miIs the i-th stage rotor weight;
determining the moment of inertia of the longitudinal shaft of the ith-stage rotor after the multistage rotor is assembled, and expressing the moment of inertia of the longitudinal shaft of the ith-stage rotor after the multistage rotor is assembled by the following formula:
Figure FDA0002529991140000033
wherein JHiThe moment of inertia of the longitudinal axis of the ith-stage rotor after the multistage rotor is assembled;
step 4.2: establishing an optimization target, wherein the optimization target is three targets, namely, the unbalance amount of the whole coaxiality and the moment of inertia of the longitudinal axis after the multi-stage rotor is assembled, the coaxiality is the maximum value of the concentricity of each single-stage rotor after the rotors are assembled, and the coaxiality is calculated by the following formula:
c＝max{CHi,i＝1,2,...,n} (8)
wherein c is the coaxiality, and n is the number of rotor stages;
the unbalance amount is the product of the total mass of the assembly body and the mass center offset, and the mass center offset and the unbalance amount are represented by the following formula:
Figure FDA0002529991140000034
Figure FDA0002529991140000035
wherein, ZHxAs the abscissa of the centroid of the entire assembly, ZHyIs the ordinate of the mass center of the whole assembly body;
the moment of inertia of the longitudinal axis, which is the product of the total mass of the fitting body and the square of the offset of the center of mass, is expressed by the following equation:
Figure FDA0002529991140000036
wherein J is the moment of inertia of the longitudinal axis;
step 4.3: establishing a tri-objective minimization function, which is expressed by the following formula:
Figure FDA0002529991140000041
wherein the content of the first and second substances,
Figure FDA0002529991140000042
in order to be the objective function, the target function,
Figure FDA0002529991140000043
is a vector formed by the assembly angles of the single-stage rotors; thetaznThe angle of the nth-stage rotor rotating around the normal axis of the top surface of the nth-1 stage rotor,
Figure FDA0002529991140000044
optimizing a function for a single target based on coaxiality;
Figure FDA0002529991140000045
based on the offset of the centre of massA single-objective optimization function is used to optimize,
Figure FDA0002529991140000046
a single objective optimization function based on the amount of unbalance is represented,
Figure FDA0002529991140000047
representing a single objective optimization function based on the moment of inertia;
step 4.4: converting the three-target minimization function into a fitness function of the genetic algorithm, and expressing the fitness function of the genetic algorithm by the following formula:
Figure FDA0002529991140000048
Figure FDA0002529991140000049
wherein, c△For the minimum value of the coaxiality-based single-objective optimization function, U△For the minimum of a single-objective optimization function based on the amount of unbalance, J△Is the minimum value of a single-target optimization function based on the moment of inertia;
step 4.5: obtaining the optimal transfer angle theta of each stage of rotor through a genetic algorithmziSo that the coaxiality, the unbalance amount and the rotational inertia are close to the minimum value of each single target optimization, and the coaxiality, the unbalance amount and the rotational inertia of the rotor are simultaneously optimized under the same assembly reference;
and 5: assembling the single-stage rotors together according to the optimal assembly angle of the rotors at each stage;
step 6: and detecting the coaxiality, the mass center offset and the rotational inertia of the assembly to ensure that the assembly requirement indexes are met.
2. The three-target optimization method for the assembly of the aeroengine rotor based on the four-point weighing as claimed in claim 1, which is characterized in that: the weighing sensor is an SBS shear beam type weighing sensor with a Mettler-Tollido structure.
3. The three-target optimization method for the assembly of the aeroengine rotor based on the four-point weighing as claimed in claim 1, which is characterized in that: the step 1 of aligning and inclination adjusting of the aligning and inclination adjusting platform (4) is as follows:
step 1.1: a measured rotor (10) is placed on a leveling and inclination-adjusting platform (4) and fixed through a hydraulic chuck (5), and a right lower lever type inductance sensor (9c) and a right upper lever type inductance sensor (9d) are in contact with a radial assembly reference surface of the measured rotor (10) and used for aligning; contacting a left lower telescopic inductive sensor (9a) and a left upper telescopic inductive sensor (9b) with an axial assembly reference surface of a measured rotor (10) for adjusting inclination;
step 1.2: an air flotation shaft system (2) drives a measured rotor (10) to rotate at a constant speed of 6r/min to 10r/min through a leveling and inclination adjusting platform (4), a right lower lever type inductive sensor (9c) and a right upper lever type inductive sensor (9d) perform equal-interval sampling on a radial assembly reference surface of the measured rotor (10), a left lower telescopic inductive sensor (9a) and a left upper telescopic inductive sensor (9b) perform equal-interval sampling on an axial assembly reference surface of the measured rotor (10), and the number of sampling points meets 1000-2000 points per circle; performing least square circle fitting on the sampled data on the radial assembly reference surface of the measured rotor (10) to obtain an eccentricity, and performing least square plane fitting on the sampled data on the axial assembly reference surface of the measured rotor (10) to obtain an inclination;
step 1.3: and adjusting the aligning knob of the leveling and inclination adjusting platform (4) according to the size and the angle of the eccentric amount, and adjusting the inclination adjusting knob of the leveling and inclination adjusting platform (4) according to the size and the angle of the inclination amount until the leveling and inclination adjusting platform (4) meets the requirements that the size of the eccentric amount of the radial reference surface is in the range of 0 to 3 mu m and the size of the inclination amount of the axial reference surface is in the range of 0 to 2'.
4. The three-target optimization method for the assembly of the aeroengine rotor based on the four-point weighing as claimed in claim 1, which is characterized in that: the step 2 specifically comprises the following steps:
step 2.1: a right lower lever type inductive sensor (9c) and a right upper lever type inductive sensor (9d) are in contact with a radial assembly measuring surface of a measured rotor (10), a left lower telescopic inductive sensor (9a) and a left upper telescopic inductive sensor (9b) are in contact with an axial assembly measuring surface of the measured rotor (10), and an air floatation shaft system (2) rotates at a constant speed of 6r/min to 10 r/min;
step 2.2: sampling at equal intervals on a radial assembly measuring surface of a measured rotor (10) by adopting a right lower lever type inductive sensor (9c) and a right upper lever type inductive sensor (9d), sampling at equal intervals on an axial assembly measuring surface of the measured rotor (10) by adopting a left lower telescopic inductive sensor (9a) and a left upper telescopic inductive sensor (9b), and counting the number of sampling points to meet 1000-2000 points per circle;
step 2.3: and carrying out least square circle fitting on the sampled data on the radial assembly measuring surface of the measured rotor (10) to obtain concentricity, carrying out least square plane fitting on the sampled data on the axial assembly measuring surface of the measured rotor (10) to obtain parallelism, and recording corresponding phase angles of all points by adopting a circular grating reading head (2 e).
5. The three-target optimization method for the assembly of the aeroengine rotor based on the four-point weighing as claimed in claim 1, which is characterized in that: the step 3 specifically comprises the following steps:
step 3.1: taking the rotation center of the air floatation shaft system (2) as a total reference, and installing a first weighing sensor (3a), a second weighing sensor (3b), a third weighing sensor (3c) and a fourth weighing sensor (3d) on the table surface of an air floatation upper plate (2a) in a rectangular distribution manner;
step 3.2, symmetrically arranging a first weighing sensor (3a) and a fourth weighing sensor (3d) at two sides of an X axis, wherein the connecting line distance of bearing points of the first weighing sensor (3a) and the fourth weighing sensor (3d) is H and is parallel to the Y axis, symmetrically arranging a second weighing sensor (3b) and a third weighing sensor (3c) at two sides of the X axis, wherein the connecting line of the bearing points of the second weighing sensor (3b) and the third weighing sensor (3c) is parallel to the Y axis, the connecting line distance of the bearing points of the first weighing sensor (3a) and the second weighing sensor (3b) is L and is parallel to the X axis, and the first weighing sensor (3a) and the second weighing sensor (3b) are symmetrical relative to the Y axis;
step 3.3: measuring to obtain the barycenter coordinate of the measured rotor (10); the coordinates of the center of mass of the measured rotor (10) are expressed by:
Figure FDA0002529991140000061
wherein M is the weight of the measured rotor (10), F1、F2、F3And F4The difference between the no-load and the load of the first weighing cell (3a), the second weighing cell (3b), the third weighing cell (3c) and the fourth weighing cell (3d), GxIs the abscissa of the centroid of the measured rotor (10); gyIs the ordinate of the centroid of the measured rotor (10).
6. The three-target optimization method for the assembly of the aeroengine rotor based on the four-point weighing as claimed in claim 1, which is characterized in that: measuring the polarity of the longitudinal axis rotational inertia of the assembly, and measuring the period T of the idle pendulum of the air-floating shafting (2)0Moment of inertia J of the turntable0＝AT0 2Measuring the common runout period Ts of a standard sample piece and the air floatation shaft system (2), wherein the rotational inertia of the standard sample piece is Js, and obtaining a proportionality coefficient
Figure FDA0002529991140000062
Measuring the common pendulum period T of the measured rotor (10) and the air-floating shaft system 2, and then measuring the longitudinal axis moment of inertia J of the measured assembly bodyc＝A(T2-T0 2)。
7. The method for optimizing the three-target assembly of the rotor of the aircraft engine based on the four-point weighing as claimed in claim 6, wherein the method comprises the following steps: the torsion bar (2k) is locked through the torsion bar locking device (2l), and the air cylinder (2f) pushes the shifting fork (2g) to drive the air floatation shaft system (2) to generate micro angular displacement; the cylinder (2f) is loosened, and the air floatation shaft system (2) generates periodic compound pendulum motion under the action of the elastic restoring force of the torsion bar (2 k); and the photoelectric counter (2j) records the runout period of the air floatation shaft system (2).
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