Numerical Simulation of Temperature Distribution and Thermal-Stress Field in a Turbine Blade with Multilayer-Structure TBCs by a Fluid-Solid Coupling Method

doi:10.1016/j.jmst.2016.03.009

Abstract

Abstract:

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.

Key words: Thermal barrier coatings, Temperature distribution, Thermal-stress field, Conjugate heat transfer, Decoupled thermal-stress calculation, Fluid-solid coupling

W.Z. Tang, L. Yang, W. Zhu, Y.C. Zhou, J.W. Guo, C. Lu. Numerical Simulation of Temperature Distribution and Thermal-Stress Field in a Turbine Blade with Multilayer-Structure TBCs by a Fluid-Solid Coupling Method[J]. J. Mater. Sci. Technol., 2016, 32(5): 452-458.

Figures/Tables 9

Illustration of the finite element model of a two-dimensional turbine blade with TBCs.

Computational grid of external flow field of CFD model.

Contour plot of temperature of the turbine blade at the steady stage. The regions 1, 2, 3 and 4 are the typical locations, which are the leading edge, the suction side, the trailing edge and the pressure side, respectively.

Temperature distribution on the external surface of the turbine blade with TBCs.

Comparison of the non-dimensional temperature distribution on the external surface of TBCs with that of literature.

Temperature distribution along the external surface of TBCs to the substrate at the four typical locations.

von Mises stress contour plot of the turbine blade at the end of cooling (a) and stress evolution in TGO at the different stages of thermal loading (b).

Distribution of normalized PEEQ in TGO.

Stress evolution along X direction of the local coordinate system in TGO with the thermal loading history at the four typical locations: (a) leading edge

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