WO2020051794A1 - 一种基于径跳测量计算转子装配轴线偏心的方法 - Google Patents

一种基于径跳测量计算转子装配轴线偏心的方法 Download PDF

Info

Publication number
WO2020051794A1
WO2020051794A1 PCT/CN2018/105196 CN2018105196W WO2020051794A1 WO 2020051794 A1 WO2020051794 A1 WO 2020051794A1 CN 2018105196 W CN2018105196 W CN 2018105196W WO 2020051794 A1 WO2020051794 A1 WO 2020051794A1
Authority
WO
WIPO (PCT)
Prior art keywords
eccentricity
stage
circle
point
center
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2018/105196
Other languages
English (en)
French (fr)
Inventor
孙清超
刘鑫
高一超
汪云龙
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Dalian University of Technology
Original Assignee
Dalian University of Technology
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Dalian University of Technology filed Critical Dalian University of Technology
Priority to US16/604,037 priority Critical patent/US11307015B2/en
Priority to PCT/CN2018/105196 priority patent/WO2020051794A1/zh
Publication of WO2020051794A1 publication Critical patent/WO2020051794A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
    • G01B5/20—Measuring arrangements characterised by the use of mechanical techniques for measuring contours or curvatures
    • G01B5/201—Measuring arrangements characterised by the use of mechanical techniques for measuring contours or curvatures for measuring roundness
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
    • G01B5/24—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes
    • G01B5/25—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes for testing the alignment of axes
    • G01B5/252—Measuring arrangements characterised by the use of mechanical 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
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
    • G06F17/10—Complex mathematical operations
    • G06F17/16—Matrix or vector computation, e.g. matrix-matrix or matrix-vector multiplication, matrix factorization

Definitions

  • the invention belongs to the calculation method of rotor assembly axis eccentricity, and can be applied to the axis prediction, assembly phase optimization, and assembly guidance process in the assembly process of important components such as aero engine high-pressure compressor rotor, high-pressure turbine disc, and low-pressure rotor assembly.
  • the measurement of rotor assembly axis eccentricity is an important step in the optimization of assembly phase prediction.
  • the fitted circle method is a method of performing least squares fitting based on the measured radial runout data at the joints of the stop, and the method of calculating the eccentricity of the assembly axis by using the fit circle of the inner and outer stop calibers of the two rotors is simple.
  • the shape characteristics between the mating surfaces of the stop are grasped as a whole, but the fitted circle obtained by the least square method cannot fully reflect the amplitude characteristics in the initial shape, and the error between the fitted circle and the initial shape circle is irregular.
  • the actual rotation centerline method is the prediction method of the eccentricity of the axis adopted by Axiam. Its essence is to measure the actual data generated after assembly by measuring the runout data at the disc stops at all levels. Rotate the axis, and adjust and optimize the assembly phase based on this axis. This method is mainly applied abroad. The key technology has not yet been introduced in China. It has high prediction accuracy. Existing, there is no basic centering and tilting process of the roundness meter in the application of this method, and it is difficult to adapt to the production and installation of China's aero engine rotor Process.
  • the invention is based on the measurement of the radial runout of the rotor connection stop before assembly, taking into account the normal elastic deformation, and proposes a calculation method for the eccentricity of the axis after assembly. This method can realize the The eccentricity prediction of the axis, and then the optimal adjustment of the assembly phase can be further realized, which has important practical significance.
  • the present invention proposes a calculation method for calculating the eccentricity of assembly between stages based on the measured path jump data at the joints of the disc ends of the rotor parts in combination with engineering practice. .
  • the relationship between the radial runout and the eccentricity at the stop connection is calculated. Due to the uneven radial runout of the joints in the circumferential direction, the actual assembly interference amount is uneven, so the deformation after assembly is uneven.
  • This method seeks the relationship between the uneven deformation amount after assembly and the occurrence of eccentricity. The relationship between the measured path jump data and the eccentricity of the assembly axis can be obtained.
  • the stop fit is an interference fit, it does not apply to the rigid assumption.
  • This method considers the deformation caused by the interference assembly at the joint of the stopper, explores the influence of the uneven assembly deformation caused by the uneven stopper shape on the assembly eccentricity, and determines the amount of eccentricity by using a spring equivalent method.
  • the contact point is equivalent to the contact of two springs.
  • the center of the upper end A 2 and the lower end B 1 coincide as the initial state.
  • the elastic force generated by a pair of contact points with a large amount of deformation is greater.
  • the resulting elastic forces are all different. Sum the vectors of all the elastic forces to get the direction of the vector resultant force.
  • the lower end face B 1 of the upper end piece B will move in this direction. If the distance e is moved, the sum of all elastic force vectors is 0. , Then the center position of the lower end B 1 is the actual fitting position, and the distance moved is the eccentricity e.
  • This method first uses a roundness meter to measure the radial runout at the flange end of each level, and then uses the radial runout data at the adjacent two levels of disk end as input parameters.
  • the relative eccentricity matrix of the adjacent two-level discs after assembly multiply the eccentricity matrix of each adjacent two-level discs to obtain the total eccentricity matrix reflecting the coaxiality of the multi-level disc assembly; it is necessary to point out that different assemblies are adjusted Phase will get different eccentricity matrix, but the assembly phase of two adjacent discs is limited by the number of bolt holes, positioning holes, etc.
  • the optimal assembly phase can be sought before assembly, greatly reducing the number of repeated disassembly and assembly, and improving the qualification rate of one assembly.
  • FIG. 1 is a schematic diagram of a mating surface of two end rotors
  • FIG. 2 is a schematic diagram of a relative burr convex value
  • FIG. 3 is a schematic diagram of a fitted state of a rotor
  • FIG. 5 is a schematic diagram of a combined force in an ideal state
  • FIG. 6 is a schematic diagram showing the relationship between displacement and eccentricity at each point
  • e is the eccentricity
  • O is the initial center of the circle
  • O 2 is the center of the eccentric circle
  • r is the radius of the rotor base circle
  • d is the displacement of the measuring point
  • ⁇ is the eccentric angle
  • ⁇ 2 is the corresponding angle of the measuring point
  • ⁇ is the triangle Corresponding angle
  • FIG. 7 is a schematic diagram of an equilibrium state.
  • a method for calculating the eccentricity of the rotor assembly axis based on run-off measurement the steps are as follows:
  • Step A Adjacent two-stage discs, the connection between the next-stage rotor A and the upper-stage rotor B is positioned with a stop-fit interference, then the centers of the bottom and top faces are A O1 , A O2 , B O1 , B O2 , read out the measured radial runout value of the mating surfaces of the two rotors with a matrix, the data is in the form of a ring, then the lower end radial runout data of the upper end B is expressed as: B O1 ( ⁇ , z b1 ), the radial runout data of the upper end surface of the lower end piece A is expressed as: A O2 ( ⁇ , z a2 ); characterized by polar coordinate representation; the position of the circle center O in the global coordinate system is O (0,0), has been Know the mating stop radius R;
  • Step B Calculate the relative beat value of each point.
  • the upper and lower end faces are in an interference fit.
  • the "burr” shown in the figure indicates that during the part manufacturing process, due to the existence of machining errors, the actual diameter of the rotor's mating stop is within the machining error range. Randomly generated, that is, the radius value of each measuring point relative to the ideal circle center is also randomly generated, and the magnitude of the burr value is the distance between each measuring point and the base circle;
  • Step C As shown in FIG. 2, due to the interference of the stopper, when the two rotors are assembled, the stopper perimeter will generate an elastic force with a direction pointing to the center of the circle and an uneven size.
  • the stiffness at the burr is negligible compared to the base circle. For the time being, assume that the relative position of the center of the circle is unchanged during the assembly of the base circle.
  • the burr is equivalent to a spring, and the burr stiffness function is assumed to be k. 1 (n), where n is the burr width; base circle stiffness is k 2 (y), where y is the distance from the surface of the base circle.
  • h 1 is the burr at a point of B 1 and h 2 is the burr at a point of A 2.
  • x represents the displacement distance
  • 1 represents the first stage: two springs are compressed at the same time
  • 2 represents the second stage: h 1 spring compression
  • 3 represents the third stage: base circle compression stage.
  • F stands for elastic force. The relationship between force and displacement at each stage is as follows:
  • the first stage is a first stage
  • the third stage is the third stage.
  • the first stage is a first stage
  • the third stage is the third stage.
  • Step D Calculate the contact force at each point in the ideal state. Considering that the contact surfaces of the two ends of the rotor A and the rotor B are both springs, the non-uniform runout value of the two ends is equivalent to an uneven elastic force, and the solid part of the base is regarded as a rigid body without deformation. From equations (1) to (6), as shown in FIG. 5, firstly, calculate the elastic forces at the points where the centers of the two mating surfaces coincide in the ideal situation, where i represents the number of measured points;
  • Step E The resultant force vector calculation part: as shown in FIG. 6, the spring forces of the respective measuring points are vector-synthesized at the center of the circle to obtain the resultant force F n ;
  • Step F Calculate the eccentricity e.
  • the offset direction of the actual center of mass from the center of the circle, that is, the direction of the eccentricity is the direction of the resultant force F n ; if the relative position of the center of the two rotors is moved in the direction of F n , the contact portions of each pair of measuring points will change, and each measurement The point elastic force changes until the force is balanced and reaches an equilibrium state, and the centroid offset and eccentric angle are calculated according to this principle;
  • e is the eccentricity amount
  • O is the initial center of the circle
  • O 2 is the center of the eccentric circle
  • r is the radius of the base circle of the rotor
  • d is the displacement of the measuring point
  • ⁇ 2 is the angle corresponding to the measurement point
  • ⁇ is the angle corresponding to the triangle.
  • the eccentricity e can be obtained by solving equation (9).

Landscapes

  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Mathematical Physics (AREA)
  • Pure & Applied Mathematics (AREA)
  • Mathematical Analysis (AREA)
  • Mathematical Optimization (AREA)
  • Computational Mathematics (AREA)
  • Data Mining & Analysis (AREA)
  • Theoretical Computer Science (AREA)
  • Computing Systems (AREA)
  • Algebra (AREA)
  • Databases & Information Systems (AREA)
  • Software Systems (AREA)
  • General Engineering & Computer Science (AREA)
  • A Measuring Device Byusing Mechanical Method (AREA)

Abstract

一种基于径跳测量计算转子装配轴线偏心的方法，包括各点数据的矩阵表征及相对跳动值的计算、弹簧等效模型的建立及理想状态下各点接触力的计算、偏心方向及大小；各点相对跳动值的计算，并根据两止口配合面的径跳数据对应计算各点装配过盈量的过程；弹簧等效模型的建立基于弹性变形假设，分析接触过程中各阶段的力与位移关系，以不均匀的过盈量进而得出各点的不均匀接触力；偏心量的确定即在弹簧等效模型基础上，根据平衡状态方程计算最终确定偏心量的大小。本方法基于生产实际中的实测径跳数据，实现了在装配前对轴线偏心的预测，提高了装配后的转子同轴度，对航空发动机转子件装配过程中的轴线预测、装配相位调整与优化有着重要的现实指导意义。

Description

一种基于径跳测量计算转子装配轴线偏心的方法 技术领域
本发明属于转子装配轴线偏心计算方法，可应用于如航空发动机高压压气机转子、高压涡轮盘、低压转子组件等重要零组件装配过程中的轴线预测、装配相位优化、装配指导过程之中。
背景技术
在装备制造过程中，装配作为一个十分重要的环节，对产品的性能及可靠性有着直接影响。对于航空发动机转子组件而言，保证其装配后的同轴度满足要求非常重要，各级转子之间依靠止口配合进行定位，而止口配合属于过盈配合，装配后各级盘间产生的轴线偏心主要是由于装配前止口配合处形貌不均匀，从而导致装配后止口周各处径向力不均匀产生的，因而结合工厂实际装配流程，在考虑止口过盈装配弹性变形的基础上，寻求各级盘在装配前止口配合处的形貌与装配后所产生的轴线偏心之间的关系至关重要。
转子装配轴线偏心的测定是应用于装配相位预测优化中的重要步骤。拟合圆法是一种基于所测止口配合处径向跳动数据进行最小二乘拟合，通过两转子件内外止口径跳拟合圆计算装配轴线偏心的方法，这种算法程序简单，能够从整体上把握止口配合面间的形貌特征，但由于最小二乘法得到的拟合圆无法充分反映初始形貌中的幅值特征，其拟合圆与初始形貌圆间误差不规则，故其所预测轴线偏心的精度难以保证；实际回转中心线法是Axiam公司所采用的轴线偏心预测方法，其本质是通过对各级盘止口处跳动数据的测量，探求其装配后产生的实际回转轴线，并基于此轴线进行装配相位的调整与优化，此方法主要应用于国外，关键技术尚未引进国内，具有较高的预测准确度，但受我国零部件制造水平限制，零件超差现象普遍存在，本方法应用过程中没有圆度仪基本 的调心调倾过程，较难适应于我国航空发动机转子的生产装配过程中。
本发明是基于对转子连接止口装配前的径向跳动的测量，考虑法向弹性变形，提出了一种装配后轴线偏心的计算方法，该方法可以实现对某一装配相位下各级盘的轴线偏心预测，而后可以进一步实现装配相位的优化调整，具有重要的现实意义。
发明内容
为满足航空发动机转子件装配过程中的同轴度要求，本发明结合工程实践，基于转子件各级盘止口连接处的实测径跳数据，提出了一种计算各级间装配偏心的计算方法。
本方法的计算原理如下：
在考虑两级盘装配中某一确定的安装相位的前提下，考虑装配过程中止口处弹塑性变形，计算止口连接处径向跳动与偏心量的关系。由于止口连接处周向各位置的径向跳动不均匀，导致实际装配过盈量不均匀，因而装配后所产生的变形不均匀，本方法寻求装配后不均匀变形量与产生偏心的关系，即可得到实测径跳数据与装配轴线偏心的关系。
由于止口配合属于过盈配合，因而不适用于刚性假设。本方法考虑止口配合处由于过盈装配产生的变形，探究不均匀止口形貌所产生的不均匀装配变形对装配偏心的影响关系，采用弹簧等效的方式确定偏心量，即将每一组接触点等效为两个弹簧接触，上端面A 2及下端面B 1两圆心重合为初始状态，变形量较大的一对接触点所产生的弹性力就较大，因而不同位置接触点所产生的弹性力均不同。对所有弹性力进行矢量求和，得出矢量合力的方向，基于实际配合情况下，上端件B的下端面B 1将会沿此方向移动，若移动距离e后，所有弹性力 矢量和为0，则此时下端面B 1圆心位置即为实际配合位置，所移动距离即为偏心量e。
本方法首先采用圆度仪对各级法兰盘止口处的径向跳动进行测量，而后以每相邻两级盘止口处的径跳数据为输入参数，通过本算法的计算，得出相邻两级盘装配后的相对偏心矩阵；将每相邻两级盘的偏心矩阵叠乘，即可得到反映多级盘装配体同轴度的总偏心矩阵；需要指出的是调整不同的装配相位会得到不同的偏心矩阵，但相邻两级盘的装配相位受螺栓孔、定位孔等的限制是有限的个数。以运用本方法计算出的总偏心矩阵作为评定参数，可在装配前寻求最优装配相位，大大降低反复拆装次数，提高一次装配合格率。
附图说明
图1是端两转子配合面示意图；
图2是相对毛刺凸起值示意图；
图3是转子配合状态示意图；
图4是理想状态弹性力示意图；
图5是理想状态合力示意图；
图6是各点位移与偏心量关系示意图；
图6中：e为偏心量，O为初始圆心，O 2为偏心圆圆心，r为转子基圆半径，d为测点位移，θ为偏心角，θ 2为测点对应角度，γ为三角形对应角度；
图7是平衡状态示意图。
具体实施方式
以下结合附图和技术方案，进一步说明本方法的具体计算方式。
实施例
一种基于径跳测量计算转子装配轴线偏心的方法，步骤如下：
步骤A：相邻两级盘，下一级转子A与上一级转子B的连接采用止口过盈配合进行定位，则自下而上各面中心分别为A O1、A O2、B O1、B O2，读取所测两转子止口配合面的径向跳动值用矩阵表征，数据的形式是一个圆环，则上端件B的下端面径向跳动数据表示为：B O1(α,z b1)，下端件A的上端面径向跳动数据表示为：A O2(α,z a2)；用极坐标表示法表征；圆心O在全局坐标系中的位置为O(0,0),已知配合止口半径R；
步骤B：计算各点的相对跳动值。如图1所示，上端面与下端面配合状态为过盈配合，所示“毛刺”即指零件制造过程中，由于加工误差的存在，转子的配合止口处的实际直径在加工误差范围内随机产生，即每个测点相对理想圆心的半径值也是随机产生，毛刺值的大小即各测点相对基圆的距离；
步骤C：如图2所示，由于止口过盈量的存在，两转子在装配时止口周会产生方向指向圆心、大小不均匀的弹性力，为了计算各测点弹性力的大小，需计算各点处的相对毛刺凸起值，毛刺处的刚度较基圆可忽略不计，暂假设基圆装配过程中圆心的相对位置不变；将毛刺部分等效为弹簧，假设毛刺刚度函数为k 1(n)，其中n为毛刺宽度；基圆刚度为k 2(y)，其中y为距基圆表面的距离。如图3所示，h 1为B 1某点毛刺值，h 2为A 2某点毛刺值，若h 2>h 1，x代表位移距离，①代表第一阶段：两弹簧同时压缩；②代表第二阶段：h 1弹簧压缩；③代表第三阶段：基圆压缩阶段。F代表受到的弹性力。各阶段力与位移关系如下：
第一阶段：
Figure PCTCN2018105196-appb-000001
第二阶段：
F＝k 1(n)h 2+k 1(n)(x-2h 2)  (2)
第三阶段：
F＝k 2(y)(x-h 1-h 2)+k 1(n)h 2+k 1(n)(h 1-h 2)  (3)
若h 2<h 1，同理可得：
第一阶段：
Figure PCTCN2018105196-appb-000002
第二阶段：
F＝k 1(n)h 1+k 1(n)(x-2h 1)  (5)
第三阶段：
F＝k 2(y)(x-h 1-h 2)+k 1(n)h 1+k 1(n)(h 2-h 1)  (6)
步骤D：计算理想状态下各点接触力。考虑转子A与转子B两止口接触面均为弹簧，将两止口不均匀径跳值等效为不均匀弹性力，基体的实体部分视为刚体，不产生形变。由式(1)至式(6)，如图5所示，首先计算出理想状况下两配合面圆心重合情况下的各点弹性力，其中i代表测点数；
计算式同式(1)到(6)；
步骤E：合力矢量计算部分：如图6所示，将各个测点弹簧力在圆心处矢量合成，得出合力F n；
Figure PCTCN2018105196-appb-000003
步骤F：计算偏心量e。实际质心相对圆心的偏移方向，即偏心量的方向即为合力F n的方向；将两转子圆心的相对位置沿F n方向移动，则每对测点接触部分均会产生变化，同时各测点弹性力产生变化，直至受力平衡，达到平衡状态，依此原理计算质心偏移量及偏心角；
由于圆心移动一定距离，每个点位移距离不同，如图6所示，e为偏心量，O为初始圆心，O 2为偏心圆圆心，r为转子基圆半径，d为测点位移，θ为偏心角，θ 2为测点对应角度，γ为三角形对应角度。
由几何关系可得：
Figure PCTCN2018105196-appb-000004
由式(8)可得出偏心量与测点位移关系，如图7，通过圆心处矢量力合成，得到合力，当达到平衡状态时，可得：
Figure PCTCN2018105196-appb-000005
通过求解式(9)即可得到偏心量e。

Claims (1)

  1. 一种基于径跳测量计算转子装配轴线偏心的方法，其特征在于，步骤如下：
    步骤A、相邻两级盘，下一级转子A与上一级转子B的连接采用止口过盈配合进行定位，则自下而上各面中心分别为A O1、A O2、B O1、B O2，读取所测两转子止口配合面的径向跳动值用矩阵表征，数据的形式是一个圆环，则上端件B的下端面径向跳动数据表示为：B O1(α,z b1)，下端件A的上端面径向跳动数据表示为：A O2(α,z a2)；用极坐标表示法表征；圆心O在全局坐标系中的位置为O(0,0)，已知配合止口半径R；
    步骤B、计算各点的相对跳动值：上端面与下端面配合状态为过盈配合，所形成的“毛刺”即指零件制造过程中，由于加工误差的存在，转子的配合止口处的实际直径在加工误差范围内随机产生，即每个测点相对理想圆心的半径值也是随机产生，毛刺值的大小即各测点相对基圆的距离；
    步骤C、由于止口过盈量的存在，两转子在装配时止口周产生方向指向圆心、大小不均匀的弹性力，为了计算各测点弹性力的大小，需计算各测点处的相对毛刺凸起值，毛刺处的刚度较基圆忽略不计，暂假设基圆装配过程中圆心的相对位置不变；将毛刺部分等效为弹簧，假设毛刺刚度函数为k 1(n)，其中n为毛刺宽度；基圆刚度为k 2(y)，其中y为距基圆表面的距离；h 1为B 1某一点毛刺值，h 2为A 2某另一点毛刺值，若h 2>h 1，x代表位移距离，①代表第一阶段：两弹簧同时压缩；②代表第二阶段：h 1弹簧压缩；③代表第三阶段：基圆压缩阶段；F代表受到的弹性力；各阶段力与位移关系如下：
    第一阶段：
    Figure PCTCN2018105196-appb-100001
    第二阶段：
    F＝k 1(n)h 2+k 1(n)(x-2h 2)  (2)
    第三阶段：
    F＝k 2(y)(x-h 1-h 2)+k 1(n)h 2+k 1(n)(h 1-h 2)  (3)
    若h 2<h 1，同理得：
    第一阶段：
    Figure PCTCN2018105196-appb-100002
    第二阶段：
    F＝k 1(n)h 1+k 1(n)(x-2h 1)  (5)
    第三阶段：
    F＝k 2(y)(x-h 1-h 2)+k 1(n)h 1+k 1(n)(h 2-h 1)  (6)
    步骤D、计算理想状态下各点接触力：考虑转子A与转子B两止口接触面均为弹簧，将两止口不均匀径跳值等效为不均匀弹性力，基体的实体部分视为刚体，不产生形变；由式(1)～式(6)，首先计算出理想状况下两配合面圆心重合情况下的各点弹性力；
    计算式同式(1)到(6)；
    步骤E、合力矢量计算部分：将各个测点弹簧力在圆心处矢量合成，得出合力F n；
    Figure PCTCN2018105196-appb-100003
    其中，i代表测点数；
    步骤F、计算偏心量e：实际质心相对圆心的偏移方向，即偏心量的方向即为合力F n的方向；将两转子圆心的相对位置沿F n方向移动，则每对测点接触部分均产生变化，同时各测点弹性力产生变化，直至受力平衡，达到平衡状态，依此原理计算质心偏移量及偏心角；
    由于圆心移动一定距离，每个点位移距离不同，e为偏心量，O为初始圆心， O 2为偏心圆圆心，r为转子基圆半径，d为测点位移，θ为偏心角，θ 2为测点对应角度，γ为三角形对应角度；
    由几何关系得：
    Figure PCTCN2018105196-appb-100004
    由式(8)得出偏心量与测点位移关系，通过圆心处矢量力合成，得到合力，当达到平衡状态时，得：
    Figure PCTCN2018105196-appb-100005
    通过求解式(9)即得到偏心量e。
PCT/CN2018/105196 2018-09-12 2018-09-12 一种基于径跳测量计算转子装配轴线偏心的方法 Ceased WO2020051794A1 (zh)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US16/604,037 US11307015B2 (en) 2018-09-12 2018-09-12 Method for calculating eccentricity of rotor assembly axis based on radial runout measurement
PCT/CN2018/105196 WO2020051794A1 (zh) 2018-09-12 2018-09-12 一种基于径跳测量计算转子装配轴线偏心的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2018/105196 WO2020051794A1 (zh) 2018-09-12 2018-09-12 一种基于径跳测量计算转子装配轴线偏心的方法

Publications (1)

Publication Number Publication Date
WO2020051794A1 true WO2020051794A1 (zh) 2020-03-19

Family

ID=69777339

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2018/105196 Ceased WO2020051794A1 (zh) 2018-09-12 2018-09-12 一种基于径跳测量计算转子装配轴线偏心的方法

Country Status (2)

Country Link
US (1) US11307015B2 (zh)
WO (1) WO2020051794A1 (zh)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114739344A (zh) * 2022-03-18 2022-07-12 西安交通大学 一种圆度误差在线测量方法及系统
CN115048618A (zh) * 2022-06-01 2022-09-13 华中科技大学 一种柱面装配间隙公差分析方法
CN119589398A (zh) * 2024-12-18 2025-03-11 重庆齿轮箱有限责任公司 高速齿轮箱机械密封的装配方法
CN119737847A (zh) * 2024-12-26 2025-04-01 萍乡百斯特电瓷有限公司 一种瓷绝缘子瓷件和坯件偏心测量及剔除的方法

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112364448B (zh) * 2020-10-14 2024-07-12 大连理工大学 一种实现航空发动机转子直线装配的方法
CN112945049B (zh) * 2021-01-27 2023-12-15 哈尔滨工业大学 基于特征点提取的航空轴承内圈沟道形状误差精确评定方法
CN112880619B (zh) * 2021-01-27 2023-10-27 哈尔滨工业大学 一种基于子域分割的航空轴承几何误差精确评定方法
CN114018202B (zh) * 2021-11-08 2024-02-02 绍兴职业技术学院 一种快速评定圆度的新算法
CN115077920B (zh) * 2022-06-21 2023-07-14 大连理工大学 多级涡轮部件装配变形试验设备
CN115773729A (zh) * 2022-11-23 2023-03-10 清华大学 航空发动机装配状态下的转子单元同轴度测量装置和方法
CN119862649B (zh) * 2025-02-20 2025-10-21 西北工业大学 航空发动机螺栓法兰转子连接结构的同心度计算和控制方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002097961A1 (de) * 2001-05-30 2002-12-05 Continental Teves Ag & Co. Ohg Verfahren und schaltungsanordnung zur sensorlosen, elektrischen rotorlagemessung einer permanent erregten synchronmaschine
CN101556145A (zh) * 2009-04-29 2009-10-14 徐州工程学院 低速重载转子偏心量图像监测装置及方法
CN102426615A (zh) * 2011-09-01 2012-04-25 北京理工大学 一种用于精密机械系统误差传递建模的配合误差计算方法
CN103776365A (zh) * 2014-02-14 2014-05-07 哈尔滨工业大学 基于径向与轴向基准的航空发动机多轴转子装配方法与装置
CN105627969A (zh) * 2015-12-29 2016-06-01 中国航空工业集团公司沈阳发动机设计研究所 一种发动机高压涡轮间隙值修正方法

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6052956B2 (ja) * 2012-07-02 2016-12-27 株式会社ミツトヨ 形状解析方法および形状解析プログラム
US9573198B1 (en) * 2013-06-06 2017-02-21 The Boeing Company Double eccentric positioning apparatus

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002097961A1 (de) * 2001-05-30 2002-12-05 Continental Teves Ag & Co. Ohg Verfahren und schaltungsanordnung zur sensorlosen, elektrischen rotorlagemessung einer permanent erregten synchronmaschine
CN101556145A (zh) * 2009-04-29 2009-10-14 徐州工程学院 低速重载转子偏心量图像监测装置及方法
CN102426615A (zh) * 2011-09-01 2012-04-25 北京理工大学 一种用于精密机械系统误差传递建模的配合误差计算方法
CN103776365A (zh) * 2014-02-14 2014-05-07 哈尔滨工业大学 基于径向与轴向基准的航空发动机多轴转子装配方法与装置
CN105627969A (zh) * 2015-12-29 2016-06-01 中国航空工业集团公司沈阳发动机设计研究所 一种发动机高压涡轮间隙值修正方法

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114739344A (zh) * 2022-03-18 2022-07-12 西安交通大学 一种圆度误差在线测量方法及系统
CN115048618A (zh) * 2022-06-01 2022-09-13 华中科技大学 一种柱面装配间隙公差分析方法
CN119589398A (zh) * 2024-12-18 2025-03-11 重庆齿轮箱有限责任公司 高速齿轮箱机械密封的装配方法
CN119737847A (zh) * 2024-12-26 2025-04-01 萍乡百斯特电瓷有限公司 一种瓷绝缘子瓷件和坯件偏心测量及剔除的方法

Also Published As

Publication number Publication date
US20200309502A1 (en) 2020-10-01
US11307015B2 (en) 2022-04-19

Similar Documents

Publication Publication Date Title
WO2020051794A1 (zh) 一种基于径跳测量计算转子装配轴线偏心的方法
CN109117461B (zh) 一种基于径跳测量计算转子装配轴线偏心的方法
US11093582B2 (en) Method for calculating axis deviation of rotor assembly based on end face runout measurement
CN109117460B (zh) 一种基于端跳测量计算转子装配轴线偏斜的方法
CN107036512A (zh) 一种联轴器找中心的计算方法
CN108266459B (zh) 基于轴承磨配间隙的机床主轴径向跳动计算方法
CN106837426B (zh) 一种发动机核心机转子质心偏心的优化方法
CN102430918B (zh) 导向和校正装置的同轴度导向和校正方法
CN108694294A (zh) 一种航空发动机高压转子装配偏心量预测方法
CN105423876A (zh) 基于公差调控的大型高速回转装备装配测量方法及装置
CN110567339A (zh) 一种特大型轴承端面圆周孔位置度的检测方法
CN115420246A (zh) 一种基于七系统参数补偿的回转体部件垂直度误差传递方法
CN114169259B (zh) 主泵静压轴封在极限工况运行可靠性的计算评价方法
CN104482838A (zh) 一种螺旋桨叶片测量技术
CN111060058B (zh) 一种海底管道竖向弯曲检测方法
CN114838643B (zh) 一种航空发动机叶片叠合轴基准检测装置及方法
CN209131569U (zh) 一种非平面曲轴锻件的相位角检具
CN104392077A (zh) 风电锁紧盘及其传递扭矩的确定方法
CN104330065B (zh) 一种螺旋锥齿轮齿面曲率干涉检验方法
CN108254180A (zh) 一种凸轮升程误差评定的优化改进方法
CN113515825A (zh) 角接触球轴承内圈轴向、径向跳动预测方法
CN108227186B (zh) 确定光学系统环形口径二次曲面最接近比较球面曲率半径的方法
CN115854967B (zh) 一种航空发动机转子装配质量的评价控制方法
CN103934659A (zh) 高精度多级碟片堆积转子的跳动控制与优化安装方法
CN104680586A (zh) 空间任意位置椭球面最小区域拟合方法

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18933482

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 18933482

Country of ref document: EP

Kind code of ref document: A1