Numerical Simulation of Temperature Distribution and Thermal-Stress Field in a Turbine Blade with Multilayer-Structure TBCs by a Fluid-Solid Coupling Method
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To study the temperature distribution and thermal-stress field in different service stages, a two-dimensional model of a turbine blade with thermal barrier coatings is developed, in which the conjugate heat transfer analysis and the decoupled thermal-stress calculation method are adopted. Based on the simulation results, it is found that a non-uniform distribution of temperature appears in different positions of the blade surface, which has directly impacted on stress field. The maximum temperature with a value of 1030 °C occurs at the leading edge. During the steady stage, the maximum stress of thermally grown oxide (TGO) appears in the middle of the suction side, reaching 3.75 GPa. At the end stage of cooling, the maximum compressive stress of TGO with a value of -3.5 GPa occurs at the leading edge. Thus, it can be predicted that during the steady stage the dangerous regions may locate at the suction side, while the leading edge may be more prone to failure on cooling.
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