To provide a rear end collision cooling system for a turbine blade of a gas turbine engine.
The cooling system for a turbine blade of the gas turbine engine includes the turbine blade having a rear end, a concave side and a convex side. The rear end defines at least a pair of collision holes having a longitudinal center axis relatively nearer to an end of a blade in the nearest part in one of the concave side and the convex side than to an end of the blade in the nearest part in the other of the concave side and the the convex side. Alternatively or in addition to the above structure, the rear end defines at least a pair of collision holes having a longitudinal center axis tilted in the refrigerant flow direction toward one of the concave side and the convex side and opposed to the other of the concave side and the convex side.
ROELOFFS NORMAN F
PIETRASZKIEWICZ EDWARD
Tomioka Kiyoshi