在热冲击与脉动热流边界条件下，应用数值方法，求解一维非傅立叶导热方程，分析双层结构热障涂层内的一维非定常传热特性。计算模型引入壁面曲率修正，考虑了涡轮叶片表面的型线曲率影响。分析结果表明，涂层材料热松弛时间的长短是瞬态传热特性的决定因素。边界受瞬态冲击热流条件下，涂层内的温度分布在10倍的松弛时间后达到平衡分布。边界热流脉动周期与松弛时间相当时，涂层内热流出现了波状传输，热障涂层内的温度呈波状分布。非傅立叶导热方程预测的温度交变厚度大于抛物型方程预测的厚度，显示了高频热流作用下，涂层材料可能发生疲劳破坏。叶片表面的的凸形曲率以指数率形式，增强了涂层内温度波幅度，解释了叶片前缘等处涂层易出现裂纹的现象。

Numerical method is used to solve the one-dimensional unsteady heat transfer of double layers thermal barrier coatings under the pulse and periodic thermal boundary conditions. The curvature effect of turbine blade profile is studied in the one dimensional hyperbolic heat conduction equation (HHC). Results show that the length of thermal relaxation time of the coating material is the determining factor of the transient heat transfer characteristics. Temperature distribution in Thermal Barrier Coatings (TBC) can reach the equilibrium distribution after 10τ under pulse thermal boundary condition. Temperature distribution exhibits wave motion within a certain range of thickness of TBC under periodic thermal boundary conditions. The affected thickness predicted by HHC equation is larger than that by parabolic heat conduction equation. It’s shown that the coating material may be fatigue failure under high frequency heat flux. The convex curvature of blade surface increases the temperature wave amplitude exponentially in the coating which explains the phenomenon that the coating is easy to crack at the leading edge of the blade.

TG174.453

国家自然科学基金资助项目（51276116）