航空发动机燃气涡轮工作叶片阻尼片设计  

Design on the Friction Damper of Turbine Blade of the Aircraft Engine

作　　者：聂建豪 NIE Jianhao(China Aviation Development Hunan Aviation Power Machinery Research Institute,Zhuzhou Hunan 412002;Key Laboratory of Small and Medium Aero Engine Impeller Machinery,Zhuzhou Hunan 412002)

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

出　　处：《中国科技纵横》2020年第20期69-71,共3页China Science & Technology Overview

摘　　要：在航空发动机详细设计阶段中,为了减少燃气涡轮工作叶片的振动应力,设计了阻尼片结构.在具体设计中,需要确定阻尼片的壁厚.本文采用了工程计算方法,得出了壁厚与阻尼片阻尼作用的相关关系.计算结果显示,如果壁厚小于某一数值时,阻尼片的阻尼作用会随转速的增加先减弱而后增强,而当壁厚大于该数值时,阻尼片的阻尼作用会随转速的增加而不断增强.In the detailed design of a certain aircraft engine,friction dampers were used to eliminate the vibrational stress of the turbine blades.The wall thickness needed to be determined for the friction damper.In order to get it,this paper used engineering calculation methods to get the relationship between the wall thickness and the effect of eliminating the vibration of the turbine blades.The results of the calculation show that the effect of eliminating the vibrational stress of blades deteriorates in the beginning and then rises as the speed of the engine increases when the wall thickness is less than a value,and when the wall thickness is larger than this value,the effect of eliminating the vibration rises as the engine speed increases.

关 键 词：航空发动机 涡轮工作叶片 阻尼片 壁厚 设计 

分 类 号：TK441.2[动力工程及工程热物理—动力机械及工程]