Effect of TBC on heat transfer into nickel based refractory alloy

Abstract

The aim of the experiment is to evaluate an effect of industrially used plasma sprayed coatings of the TBC on the heat transfer into the refractory material designed for aeronautical applications. This study uses basic structural material of combustion chambers — components of turbine engines highly thermally stressed during the operation by flow of hot gasses. Using the hot gasses from the gas burner, the operational conditions inside the combustion chambers are simulated. The use of the TBC coating shows positive effect on the alloy overheating reduction. The results demonstrated decrease of the temperature with values in the range of hundreds of °C for materials covered with the TBC. This phenomenon can contribute to the development of the new types of aircraft engines with higher operational temperature and better fuel economics.