Evaluation method for the usage effectiveness of thermal barrier coating for turbine blade

A method for evaluating an application effect of a thermal barrier coating for a turbine vane, the method comprising the following steps:

• step 1, establishing a geometric model;
• step 2, establishing a computational grid according to the geometric model;
• step 3, setting a solution boundary condition and a material parameter according to the computational grid to perform iterative computation so as to obtain distribution of temperature fields of two computational domains for the thermal barrier coating and the turbine vane;
• step 4, setting a solution boundary condition and a material parameter according to the distribution of the temperature field of the computational domain for the thermal barrier coating and a computational grid for the thermal barrier coating to perform iterative computation, so as to obtain distribution of a stress field of the thermal barrier coating as well as maximum principal stress and maximum shear stress data of the stress field of the thermal barrier coating;
• step 5, performing a preset calculation program for calculation according to the distribution of the temperature fields of the two computational domains for the thermal barrier coating and the turbine vane as well as the maximum principal stress and maximum shear stress data of the stress field of the thermal barrier coating to obtain a heat insulation effect of the thermal barrier coating, so as to obtain a local comprehensive evaluation factor and a global comprehensive evaluation factor of the thermal barrier coating;
• and
• step 6, evaluating the heat insulation effect and a stress level of the thermal barrier coating according to the local comprehensive evaluation factor and the global comprehensive evaluation factor of the thermal barrier coating.