Numerical Simulation of Temperature Distribution and Thermal-Stress Field in a Turbine Blade with Multilayer-Structure TBCs by a Fluid–Solid Coupling Method
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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DOI：
10.1016/j.jmst.2016.03.009
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发表时间：
2016-05
影响因子：
10.9
通讯作者：
W. Tang;Yang Li;Zhuo Wang;Y. Zhou;J. Guo;Chunsheng Lu
中科院分区：
文献类型：
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作者：
W. Tang;Yang Li;Zhuo Wang;Y. Zhou;J. Guo;Chunsheng Lu
重点建立了一种具有多层热障涂层的涡轮机叶片的二维有限元模型，采用CHT法计算了涡轮机叶片的温度场，得到了TGO内的热应力场，并预测了TGO内的危险区域。为了研究不同服役阶段的温度场和热应力场，建立了一种具有热障涂层的涡轮机叶片的二维模型，采用了耦合传热分析和热应力解耦计算方法。结果表明，叶片表面不同位置的温度分布不均匀，直接影响了应力场的分布。最高温度值为1030 ℃，出现在前缘。在稳定阶段，热生长氧化物（TGO）的最大应力出现在吸力面的中间，达到3.75 GPa。在冷却结束阶段，TGO的最大压应力值为-3.5 GPa出现在前缘。因此，可以预测，在稳定阶段，危险区域可能位于吸力侧，而前缘可能更容易发生冷却故障。
HighlightsA 2D FE model of a turbine blade with multilayer-structure TBCs was developed.The temperature distribution of the turbine blade was obtained by CHT method.The thermal-stress field in TGO was obtained and dangerous regions were predicted.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.