This study experimentally investigated the effect of showerhead hole injection angle on film cooling effectiveness over a turbine vane surface. A linear cascade was designed based on the 50 % span profile of a high pressure turbine vane, and the test vanes were manufactured using additive manufacturing. Coolant was supplied independently through separate internal channels to the showerhead, pressure side, and suction side holes. The showerhead injection angle was set to 0°, 30°, and 60°, and a vane without showerhead holes was also tested to isolate the effect of hole presence. Film cooling effectiveness was measured using the pressure-sensitive paint method under a mainstream inlet Mach number of 0.109 and average blowing ratios of 1.0 and 2.0. The results show that the showerhead hole configuration influences not only the leading edge region but also the downstream film cooling effectiveness on the vane surface. Smaller injection angles reduce film cooling effectiveness in the downstream region, even in the absence of showerhead coolant injections. Under showerhead-only injection conditions, increasing the blowing ratio enhances coolant lift-off, while increasing the injection angle promotes lateral redistribution of coolant toward the shroud side and upper span region. Under full injection conditions, higher film cooling effectiveness is observed in the upper span region, indicating that coolant distribution varies with the showerhead injection angle. Within the tested range, the 30° case generally provided the highest area-averaged FCE under most full-injection conditions, whereas lower and higher injection angles result in reduced performance due to non-uniform distribution or excessive spanwise redistribution. These results demonstrate that the showerhead hole configuration affects vane cooling performance through modification of coolant distribution along the vane surface.


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