Patent ID: 8079812

Claim:
A turbine component used in a gas turbine engine, the turbine component comprising: a turbine component main body; and a plurality of film cooling holes formed at regions exposed to a hot gas in the turbine component main body, the film cooling holes expel cooling air, which is introduced from a side of an inner wall surface of the turbine component main body, along an outer wall surface of the turbine component main body, each of the film cooling holes comprising: a straight hole portion formed in a portion of the turbine component at the side of the inner wall surface so constituted that a cross section of the straight hole portion is substantially uniform in shape along a thickness direction of the turbine component main body, and a diverging hole portion continuous to the straight hole portion so constituted that a cross section of the diverging hole portion gradually broadens toward the side of the outer wall surface, the diverging hole portion having an outlet surface at a downstream side of the hot gas, wherein each of the film cooling holes is so constituted that the outlet surface of the diverging hole portion from a center portion to both end sides gradually leans toward the downstream side of the hot gas on the basis of a hypothetical plane parallel to two directions of an axial center direction and a lateral direction of the straight hole portion, and each of the film cooling holes is so constituted that the outlet surface of the diverging hole portion leans toward an upstream side of the hot gas at a center in the lateral direction on the basis of the hypothetical plane.