Thermal modeling of various thermal barrier coatings in a high heat flux rocket engine

Abstract

One- and two-dimensional thermal models were developed to predict the thermal response of tubes with and without thermal barrier coatings (TBCs) tested for short durations in a H 2/O 2 rocket engine. Temperatures were predicted using median thermophysical property data for traditional air plasma sprayed ZrO 2–Y 2O 3 TBCs, as well as air plasma sprayed and low pressure plasma sprayed ZrO 2–Y 2O 3/NiCrAlY cermet coatings. Good agreement was observed between predicted and measured metal temperatures. It was also shown that the variation in the reported values of the thermal conductivity of plasma sprayed ZrO 2–Y 2O 3 coatings can result in temperature differences of up to 180°C at the ceramic/metal interface. In contrast, accounting for the presence of the bond coat or radiation from the ceramic layer had only a small effect on substrate temperatures (<20°C). The thermal models were also used to show that for the short duration test conditions of this study, a 100 μm thick ZrO 2–Y 2O 3 coating would provide a metal temperature benefit of approximately 300°C over an uncoated tube while a 200 μm thick coating would provide a benefit greater than 500°C. The difference in the thermal response between tubes and rods was also predicted and used to explain the previously-observed increased life of TBCs on rods over that on tubes.