Reduced thermal conductivity for possible thermal buffer coating application in aero engine turbine blade

Abstract

The thermal barrier coating (TBC) used for aero engine turbine blade requires a low thermal conductivity layer to buffer the surface heat wave into the base super alloys. Since air has a nearly lowest thermal conductivity, adding the air or increase the porosity would improve the thermal buffering effect. In this paper this principle was demonstrated by using the deep trenched silicon wafer with ICP deep trench etching technique, by ionized porous Ti surface, by foamed copper and foamed nickel and by porous YSZ TBC film. SEM, AFM and thermal conductivity measurements were used to characterize the morphology and thermal insulating properties. Computer simulation was also conducted to analyze the thermal conducting properties using the porous structure in the thermal buffer structure. Show more