涡轮叶片等离子涂层应力分析  

Stress Analysis for Plasma Sprayed Thermal Barrier Coating on the Turbine Vane

作　　者：唐家鹏[1] 李志永[2] 

机构地区：[1]中北大学机电工程学院,太原030051 [2]北京航空航天大学,北京100083

出　　处：《弹箭与制导学报》2010年第6期227-229,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：根据航空发动机涡轮叶片等离子涂层即热障涂层系统在各种工况下的特性,建立了叶片试件的结构模型及有限元模型。利用MSC.Marc软件对热障涂层进行了系统性的分析,分别计算了不同初始无应力状态温度和不同氧化层厚度条件下涂层内部的应力变化情况,从而了解热障涂层的失效特点和其影响因素的作用特点,为提高涂层的寿命提供理论参考。According to the characteristics of the plasma sprayed thermal barrier coating on the aero engine turbine vane under different conditions,structure and finite element model of the vane were established.Thermal barrier coating was analyzed by Marc software systematically.The stress changes in the coating under different temperature and oxide thickness were calculated separately. The failure characteristics of the thermal barrier coating and the effect characteristics of its factors were learned.

关 键 词：涡轮叶片 有限元 热障涂层 残余应力 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]