航空发动机涡轮叶片测量评估的多样本融合方法  

Multi-samples Integration Method for CMM Data of Turbine Blade

作　　者：张强[1] 蒋睿嵩[2] 汪文虎[2] 赵德中[2] ZHANG Qiang JIANG Ruisong WANG Wenhu ZHAO Dezhong(The Key Laboratory of Advanced High Temperature Structural Materials, Beijing Institute of Aeronautical Materials, Beijing 100095, China The Key Laboratory of Contemporary Design and Integrated Manufacturing Technology, Northwestern Polytechnical University, Xi＇an 710072, China)

机构地区：[1]北京航空材料研究院先进高温结构材料国防科技重点实验室,北京100095 [2]西北工业大学现代设计与集成制造技术教育部重点实验室,陕西西安710072

出　　处：《铸造技术》2017年第4期974-977,共4页Foundry Technology

基　　金：国家自然科学基金资助项目(51475374;51505387);中央高校基础研究基金资助项目(3102015ZY087)

摘　　要：为获得涡轮叶片精铸位移场进行模具型腔优化,需要对叶片进行测量评估。由于精铸工艺系统误差和随机误差的影响,单个叶片并不能精确的表征叶片变形量;为此,需要针对一批叶片进行测量评估,从而获得统计意义下的精铸位移场,这其中主要的难点即为多样本测量数据的融合问题。为此,本文提出并研究了一种基于最短路径准则的涡轮叶片多样本测量数据融合方法,通过建立数据点融合模型,实现了多样本数据的统计学建模,从而有效的消除了制造系统误差对精铸位移场的影响,并进行了实例验证。In order to obtain the displacement field of investment casting in die cavity optimization, it is necessary to measure and evaluate the deformation of turbine blade. Due to the influence of systemic and random error of casting process, single turbine blade cannot represent the deformation appropriately. Hence, a group of turbine blades should be measured to estimate the random error in fabrication process. Multi-measuring data integration is the key problem to obtain the statistic displacement field. Aiming at the problem, a minimum path based on integration method was proposed in this study. A mathematical model was established and demonstrated to achieve the purpose of data integration.

关 键 词：涡轮叶片 测量评估 精铸位移场 数据融合 多样本 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程] V263.1