起动阶段涡轮导向叶片热应力及冷却作用研究  

Research of Thermal Stress and Cooling Effect on a Turbine Guide Vane During the Start-Up Period

作　　者：艾延廷[1] 刘仲尧[1,2] 王志[1] 

机构地区：[1]沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室 [2]95906部队一大队机务中队

出　　处：《机械设计与制造》2015年第1期97-100,104,共5页Machinery Design & Manufacture

基　　金：航空科学基金(2012ZB54007)

摘　　要：建立了涡轮导向叶片有限元分析模型,参照相关的试验数据和文献资料确定热边界条件,计算了发动机起动阶段涡轮导向叶片各瞬时的温度及热应力。分析所得高温、高应力区域与相似条件下某型发动机地面试车过程中出现裂纹的区域基本一致,验证了数值模拟过程的正确性。在此基础上,对比分析施加对流冷却与无冷却措施两种条件下的计算结果,发现对流冷却使叶片各点温度下降而应力升高,推断出温度与应力的变化趋势反向,因而在叶片冷却系统的设计中需要权衡温度与应力的关系。其结果与结论对叶片瞬态热应力计算和热疲劳分析有一定的借鉴意义。A finite element analysis model for a turbine guide vane was developed.The thermal boundary conditions was set up in terms of the data measured and recorded in previous tests and literature,based on which a transient temperature and thermal stress simulation was carried out for start-up period.The obtained areas of high temperature and stress were consistent with the areas cracked in the ground testing of an aero-engine under similar conditions,thus,the correctness of numerical simulation was validated.By comparison of the calculation results under convection cooling condhion and no-cooling condition,it was founded that the temperature of the vane would decrease while the stress on it increased under convection cooling condition,the changing tendency of temperature and stress was contrary,so the tradeoff between temperature and stress is indispensable when designing the cooling system.h has certain reference for transient thermal stress simulation and thermal fatigue analysis of a turbine guide vane.

关 键 词：涡轮导向叶片 有限元分析 瞬态温度场 瞬态热应力场 热疲劳 

分 类 号：TH16[机械工程—机械制造及自动化] V235.11[航空宇航科学与技术—航空宇航推进理论与工程]