ABSTRAKT

The purpose of this paper is to describe the major heat transfer areas that have to be dealt within the development of a modern aero-engine. The focus will be on gas turbine engines; piston and rocket engines will be excluded. Although the focus will be on aero-engines, many statements will also be relevant to stationary gas turbines.
Gas turbines, being heat engines, have always received the attention of heat transfer specialistics. The present paper will show that, owing to the trends in aircraft gas turbine design, which will be described briefly, the scope of heat transfer problems has greatly increased. By looking at each component separately it will be demonstrated that many new challenging problems have arisen besides the hitherto classical areas of combustor and turbine cooling.