Stagnation region gas film cooling: Spanwise angled injection from multiple rows of holes

The film cooling performance was modeled for a turbine vane leading edge using the stagnation region of a cylinder in cross-flow. Experiments were conducted in a rectangular duct using a cylindrical test surface. A gas turbine combustor provided heated air flow to simulate the Reynolds number and internal convection cooling of the cylinder allowed the freestream-to-wall temperature of 1.7 to be achieved. The film coolant injected at room temperature, passed through angled coolant holes. The cylindrical test surface was instrumented with miniature heat flux gages and wall thermocouples to determine the percentage reduction in the Stanton number as a function of the distance downstream of injection and the location between adjacent holes. Data from local heat flux measurements are presented for single row and multiple row injection configurations.