某型航空发动机高温总压探针模态分析及强度校核  

Modal analysis and strength check of an aeroengine's high-temperature total pressure probe

作　　者：左泽敏[1] 武瑞娟[1] 郭斌[1] 

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《现代机械》2015年第2期26-29,共4页Modern Machinery

摘　　要：安装于被试航空发动机内涵高温区的探针的可靠性直接关系被试发动机安全,设计高温总压探针时对其进行模态分析及强度校核十分必要。依据总压探针在被试发动机上的安装接口及内部结构,设计了探针的三维模型,根据大量试验数据统计,得出探针工作的温度范围、对应被试发动机工作状态和探针受到的激励功率谱密度,并通过ANSYS计算总压探针在各个温度下的模态和等效应力,以确定其避开发动机对应转速的激励,并进行强度校核。计算结果表明,该总压探针模态及强度满足使用要求,为探针的设计及装机使用提供依据。The reliability of the probe installed in the high temperature part of the tested aeroengine is directly relevant to the aeroengine＇s safety,so mode analysis and strength check is a necessary step in the design of high- temperature probe. According to the install connector and interior structure of aeroengine,this paper designs the three- dimensional model of the probe. The temperature range in which the probe works,the working condition of the corresponding tested aeroengine and the excitation power spectral density are obtained based on great number of test data. The mode and equivalent stress of the probe within different temperature ranges are worked out by ANSYS software,in order to avoid the excitation of the corresponding revolving speed of the engine. Strength check is also carried out. The results show that the total pressure probe mode and its strength meet the requirements,which provides reference for future design and installation of probes in this field.

关 键 词：航空发动机 高温探针 模态分析 强度校核 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]