基于实测数据的航空发动机转子叶尖装配间隙预测  

Prediction of rotor blade tip assembly clearance based on measured data for aero-engine

作　　者：邓王倩 莫蓉[1] 陈凯[1,2] 冯鑫 夏华腾 孙惠斌 常智勇[1] DENG Wangqian;MO Rong;CHEN Kai;FENG Xin;XIA Huateng;SUN Huibin;CHANG Zhiyong(Key Laboratory of High Performance Manufacturing for Aeroengine,Ministry of Industry and Information Technology,Northwestern Polytechnical University,Xi'an 710072,China;South Industry Company Limited,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China)

机构地区：[1]西北工业大学航空发动机高性能制造工业和信息化部重点实验室,西安710072 [2]中国航空发动机集团有限公司南方工业有限公司,湖南株洲412002

出　　处：《航空动力学报》2022年第6期1273-1283,共11页Journal of Aerospace Power

基　　金：国家科技重大专项(2017-Ⅶ-0010-0104);基础科研计划(XXXX2018213A001);装备预研基金(61409230204);陕西省重点研发计划(2018ZDXM-GY-068,2016KTZDGY4-02)。

摘　　要：以多级转静子装配过程为研究对象,基于空间几何变换理论及形位公差理论,提出了一种多级转子叶尖间隙预测方法。具体是将转静子系统分为转子、静子、支承等3个子系统,分别针对子系统建立装配偏差子模型,进一步将各模型进行坐标统一,以配合面的实测偏差数据作为输入量,计算同一轴向位置处的转子叶尖坐标及机匣坐标,从而计算出转子叶尖间隙。试验结果表明,采用所述间隙预测模型,可准确预测转子叶尖间隙,预测最大相对误差为11%,从而为装配质量分析提供了参考依据。Taking the multi-stage rotor and stator assembly process as the research object,and based on the spatial geometric transformation theory and the shape and position tolerance theory,a multi-stage rotor blade tip clearance prediction method was proposed. Specifically,the rotor and stator system was divided into three subsystems: rotor, stator and support. The sub-models of assembly deviation were established for each subsystem. The coordinates of each submodel were unified. The measured deviation data of fitting surface were taken as the input to calculate the rotor blade tip coordinates and casing coordinates at the same axial position, so as to calculate the rotor blade tip clearance. The test results showed that the prediction model could accurately predict the rotor blade tip clearance,and the maximum relative error of prediction was11%,thus providing a reference for the assembly quality analysis.

关 键 词：叶尖装配间隙预测 航空发动机转子 实测数据 刚柔误差耦合 偏差传递 

分 类 号：V263.23[航空宇航科学与技术—航空宇航制造工程]