航空发动机叶片表面热障涂层温度分布的仿真分析

Simulation Analysis of Temperature Distribution of Turbine Blades by Thermal Buffer Coating for Aero Engine

采用有限元固体热传导仿真模型分析航空发动机导向叶片表面热障涂层(TBC)的温度特性;采用工程实验的通用模型,输入因变量(Input)→仿真模型和边界条件(Process)→输出变量(Output),进行热障涂层的实验设计;比较了几种热涂层材料(如ZrO2系列TBC)的隔热性能,分析了不同的基底与TBC厚度下隔热性能的变化情况.同时,通过计算机仿真方法探讨了国内外相关文献中的TBC隔热效果的差异性.结果表明,温度边界条件对于准确估算TBC的隔热效果至关重要.在对比TBC的隔热性能时,需对测温环境进行标定.

Temperature separation effect of thermal barrier coating （TBC） for aero-engine turbine blade ap- plications has been studied extensively with the aid of computer simulation by the finite element method （FEM）. In this simulation studies, a general engineering methodology is implemented, i.e. the ＂Input- Process-Output＂ methodology as part of the undergraduate participation research program in Shanghai Jiao Tong University. Thermal buffering effect of different TBC materials （ZrO2, HfO2, CeO2, etc. ）, various combinations of TBC and base metal dimensions and structures are compared. Similar comparison is made on various TBC thickness to provide a qualitative picture on the thermal buffering effect on turbine blade dimensions. The conclusion may provide some guidelines in turbine blade thermal dynamic design. Simula- tion also shows that for correct calibration of the TBC＇s thermal buffering effect proper boundary conditions in the TBC characterization must be specified, and this could explain the various contradictions in different reports on different thermal buffering temperature in various TBC samples.