Анализ теплообмена при струйном охлаждении входной кромки лопатки газовой турбины

Abstract

The numeral analysis of the flow and heat transfer under jet cooling in area of leading edge of the gas turbine blade is studied. The average heat transfer coefficients are calculated for the leading edge surface for the different flow regimes, jets, and fins on the wall. Basing on these data, the known heat transfer equations were analyzed. One of the equations was approved for using in the nozzle vanes or blades cooling system calculations