Design and optimization of an efficient internal air system of a gas turbine requires thorough understanding of the flow and heat transfer in rotating disc cavities. The present study is devoted to numerical modelling of flow and heat transfer in
IntroductionImprovements in material properties of gas turbine components and the use of cooling air allow engines to operate at higher pressure ratios and higher gas temperatures thus yielding higher thermal efficiency. The reliance on cooling air makes the secondary air system one of the most critical sections of a gas turbine. The optimum design of these systems maximizes the engine performance and life, and varies depending on the applications (power turbines or jet engines), models and manufacturers. Rotating disc cavities are an important element of engine cooling air systems. As in the review by Owen & Wilson [1] these disc cavities are broadly classified into rotor-stator, co-rotating