某型发动机涡轮工作叶片动应力测试研究  

Research on Vibration Stress Testing of an Engine Turbine Rotor Blades

作　　者：吴炜 WU Wei(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou Hunan 412002;Hunan Key Laboratory of Turbomachinery on Medium and Small Aeroengine,Zhuzhou Hunan 412002)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]冲小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002

出　　处：《中国科技纵横》2022年第2期76-78,共3页China Science & Technology Overview

摘　　要：为摸清某型涡扇发动机低压涡轮工作叶片减振设计改进效果,对改进叶片与现有使用叶片的振动应力进行对比测试,本文重点介绍了贴片方案、发动机测试改装和数据处理分析,在发动机实际工作状态下,得到叶片测试部位的真实动应力。结果表明,在全转速范围内发动机低压涡轮工作叶片振动应力均处于较低的水平,改进叶片振动应力低于现有使用叶片。To figure out the vibration damping effect of low-press turbine blade in a turbofan engine,and make a comparison vibration stress test between the optimized blade and the existing one.Patch position of strain page,engine adaption modification and date analysis were presented.The actual vibration stress of the testing positions were obtained under the real engine operation conditions.The results show that the vibration stress of the low-pressure turbine blade is lower under all engine operation conditions,and the Vibration stress of the optimized blade is lower than the existing one.

关 键 词：涡轮工作叶片 动应力测试 航空发动机 

分 类 号：V23119[航空宇航科学与技术—航空宇航推进理论与工程]