液体火箭发动机涡轮叶片结构特性的有限元分析  

Finite Element Analysis of the Turbine Blade Structural Characteristics for Liquid Propellant Rocket Engine

作　　者：魏鹏飞[1] 吴建军[1] 陈启智[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2005年第2期29-31,共3页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(50276068)

摘　　要：为了提高液体火箭发动机的可靠性、可用性以及可维护性而进行的发动机寿命预估与减损控制研究,需要对发动机的零(部)件进行结构特性分析。通过建立某型液体火箭发动机涡轮转子叶片的有限元分析模型,分别进行无阻尼自由振动下的模态分析、无阻尼强迫振动下的谐波响应分析与有阻尼强迫振动下的瞬态响应等结构动特性分析,得到涡轮转子叶片的固有频率及与之对应的振型、谐波响应与瞬态响应。It is necessary to analyze the structural characteristics of the engine key components so as to be able to predict the engine life and mitigate the components damage, and extend the engine Me for improving the reliability, availability and maintainability of liquid rocket engines. The model of the turbine rotor blade with finite element analysis for the newly developing large-thrust liquid rocket engine is set up. Based on these models, characteristics analysis of structural dynamics such as modal analysis under undamped free vibration, harmonic response under undamped forced vibration and transient response under damped forced vibration, is performed respectively. Meanwhile, natural frequencies and mode shapes, harmonic response and transient response of a single turbine rotor blade, are also obtained.

关 键 词：液体火箭发动机 结构特性 涡轮叶片 涡轮转子叶片 有限元分析模型 无阻尼自由振动 谐波响应分析 瞬态响应 强迫振动 动特性分析 控制研究 寿命预估 可维护性 模态分析 固有频率 可靠性 可用性 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程] V232.4