Jet Impingement Cooling System on the Pressure Side of Turbine Blade

摘要

This study is to investigate the effectiveness of jet impingement cooling system on the turbine blade pressure side. The objective of this study is to determine the mass blowing rate referred to Reynolds number and the nozzle exit to surface distance which will produce the highest cooling effectiveness which will be shown as Nusselt number. A model of CF6-50 blade is made from mild steel and an experiment to study the jet impingement cooling effectiveness on the pressure side of turbine blade is conducted. The parameters that are included in the experiment are the Reynolds number, Re = 646, 1322, 1970 and 2637; and nozzle exit to surface distance, s/d = 4.0 cm, 8.0 cm and 12.0 cm. The results obtained are calculated and graphs for each experiment are made. The result shows that the jet impingement cooling effectiveness are the highest at where the nozzle is pointed and the cooling effectiveness decreases as it travels further away on the blade. The theory of jet impingement cooling is presented and the several factors that affect jet impingement cooling are also discussed.