Numerical prediction and correlation of leading edge jet impingement with varying jet shapes and flow conditions for gas turbine cooling.
Access changed 10/25/18.
To increase the core power of gas turbine engines, the combustion temperature is elevated above the metallurgical limits of the internal components. As a consequence, active cooling schemes are required to prevent the blades from melting. In this study, a numerical investigation of leading edge impingement cooling was performed. The effects of jet Reynolds number, jet-to-target surface spacing, jet-to-jet spacing, target surface curvature, and jet aspect ratio on the target surface Nusselt numbers were quantified. In all cases, the jets were equally spaced and had fully filleted edges. The numerical results were utilized to develop an empirical correlation for the surface average Nusselt number. The correlation enables engine designers to accurately predict the heat flux on the blade wall, as well as identify the optimal leading edge geometry to minimize the amount of cooling air required; thus, increasing the thermal efficiency of the gas turbine engine.