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

Abstract

Abstract: Temperature separation effect of thermal barrier coating (TBC) for aeroengine turbine blade applications 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. Simulation 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.

Key words: aero engine; thermal barrier coating (TBC); finite element method (FEM)

CLC Number:

V 231.1

DUAN Li1,GAO Junchao1,WANG Ruijun2,HU Mingkai1,SU Jingchao3 CHENG Qingqing3,ZHANG Bo3,YUAN Tao2. Simulation Analysis of Temperature Distribution of Turbine Blades by
Thermal Buffer Coating for Aero Engine[J]. Journal of Shanghai Jiao Tong University, 2017, 51(8): 915-920.

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