涡轴发动机燃气涡轮叶片动应力分析  

Dynamic stress analysis of turboshaft engine gas turbine blade

作　　者：龙伦 李建华 袁巍 张如刚 曹鹏 LONG Lun;LI Jian-hua;YUAN Wei;ZHANG Ru-gang;CAO Peng(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Key Laboratory of Aero-engine Vibration Technology,Aero Engine Corporation of China,Zhuzhou 412002,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中国航空发动机集团航空发动机振动技术重点实验室,湖南株洲412002

出　　处：《燃气涡轮试验与研究》2022年第5期21-26,共6页Gas Turbine Experiment and Research

基　　金：国家科技重大专项项目(779608000000200007)。

摘　　要：针对涡轴发动机燃气涡轮叶片动应力试验测点位置选取、动应力测试结果开展了系统的分析研究。采用有限元方法对燃气涡轮叶片进行振动分析,结合测点敏感性、叶片模态试验和不平衡量分析对燃气涡轮叶片动应力试验测点位置进行了优化,根据优化后的测点位置方案开展了动应力试验,并从共振转速、激振源、危险模态、高周疲劳评估等方面对动应力试验结果进行了分析。研究表明:非明确结构激振可导致燃气涡轮叶片1阶共振;对于在工作转速范围内存在共振的燃气涡轮叶片,若高周疲劳评估满足要求,也可安全使用。研究工作可为燃气涡轮叶片振动设计提供参考。The position selection and the results of dynamic stress measurement were analyzed and studied systematically in the turboshaft engine gas turbine blade.The vibration analysis of gas turbine blade was carried out by finite element method,and the position of dynamic stress measurement was optimized by measuring point sensitivity,blade modal test and unbalance analysis.According to the optimized measuring point position scheme,the dynamic stress measurement was carried out,and the results of dynamic stress measurement were analyzed on aspects of resonance speed,excitation source,dangerous mode,high cycle fatigue evaluation.The results show that the first-order resonance of gas turbine blades can be induced by non-explicit structural excitation;for gas turbine blades with resonance within the operating speed range,they can also be safely used if they meet the requirements of high cycle fatigue evaluation.The research work can provide reference for the vibration design of gas turbine blade.

关 键 词：航空发动机 燃气涡轮叶片 动应力 测点敏感性 共振转速 高周疲劳评估 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]