Session: 12-12 Film cooling computational studies (II)

Paper Number: 126121

126121 - Effect of Thermal Barrier Coating Simulation Method on Cooling Characteristics of Turbine Vanes 

Thermal barrier coating (TBC) is widely used in turbine vanes relying on the good thermal resistance and corrosion resistance. It is of great significance to accurately simulate the flow and heat transfer characteristics of coated vanes. However, there is no uniform standard for the simulation method of TBC. In this paper, the numerical study of vanes with a single-layer coating was conducted. The effect of the simulation methods (thin-wall with virtual thickness and real thickness) on the flow and heat transfer characteristics was investigated under different TBC properties and turbulence intensity. The results showed the mass flow of film holes on the suction surface of real TBC vanes was reduced by 24 %, when the TBC thickness was 0.3 mm. The average temperature of TBC surface and area covered by film was reduced by 5 K and 25 K, respectively. The temperature difference between the two methods on the coating surface was significantly larger than that on the metal surface. And it decreased with the increase of overall cooling effectiveness but increased with thermal conductivity of TBC. Compared with real TBC vanes, the average surface temperature of virtual TBC vanes was less sensitive to the thermal conductivity and more sensitive to the turbulence intensity. When the turbulence intensity was low (Tu = 0.05), the temperature of the coated surface covered by film was lower, while when the turbulence intensity was high (Tu = 0.2), the result was just the opposite. Finally, a simplified coating simulation method was proposed, and the accuracy of this method on the heat transfer characteristics of vanes with a double-layer coating was verified.

Presenting Author: Zequn Du Beihang University

Presenting Author Biography: I am a student from Beihang university. I am majoring in numerical studies on the combined effect of film cooling and thermal barrier coating on the heat transfer of turbine blades.

Authors:

Zequn Du Beihang University
Ruquan You Beihang University
Haiwang Li Beihang University
Yi Huang Beihang University