FLOW AND HEAT TRANSFER THROUGH TURBINE BLADE PASSAGES

In order to design a high performance gas turbine engine for prolonged hours of continuous operation without failure, it is critical to understand and predict the flow and heat transfer through turbine blade passages. A brief survey of recent major achievements made is given in the present paper, in conjunction with the turbine blade passage flow, turbine blade heat transfer, tip-clearance effect, transitional boundary layer effect and unsteady flow effect, which were presented at the International Gas Turbine and Aeroengine Congress and Exposition, Cologne, Germany, June 1-4, 1992, and published in ASME Journal of Turbomachinery and Journal of Engineering for Gas Turbines and Power in the years 1991 and 1992. It is discussed that many phenomena which were not understood well in the past are now given better explanation through advanced experimental and numerical techniques.