Stagnation Region Gas Film Cooling for Turbine Blade Leading-Edge Applications

An experimental investigation was conducted to model the film cooling performance for a turbine vane leading edge using the stagnation region of a cylinder in cross-flow. Experiments were conducted with a single row of spanwise angled coolant holes for a range of the coolant blowing ratio with a freestream-to-wall temperature ratio =2.1 and ReD = 170,000 characteristic of the gas-turbine environment. Data from local heat flux measurements are presented for coolant hole injection angles of 25°, 35°, and 45° with the row of holes located at three positions relative to the stagnation line on the cylinder. Results show the spanwise (hole-to-hole) variation of heat flux reduction due to film cooling and indicate conditions for the optimum film cooling performance.