Patent ID: 8172505
Filing Date: 2012-05-08
Classification: F01D,F05D

Abstract:
1. A cooling structure for a structural body, which configures a turbine, having wall surfaces provided along a high temperature combustion gas flowing substantially in the direction of an axial line of the turbine comprising: a cooling flow path provided in a space defined between the wall surfaces in the structural body meandering around a flow direction of the high temperature combustion gas; an inflow path for a cooling air formed inside of the structural body in which the cooling flow path extends in a direction substantially perpendicular to the axial direction; at least one straight flow path provided with intervals substantially in the axial direction, in which a length substantially the same as the length of the inflow path is a flow path width and extended substantially in the normal direction of the wall surface by a finite length; and a turning flow path for communicating the ends of the inflow path with the straight flow path or communicating the ends of each of the straight paths one after the other, wherein the wall surfaces are a suction surface and a pressure surface of the turbine blade, the cooling flow path has a first flow path and a second flow path directing from the center portion of the turbine blade to the leading edge thereof and to the trailing edge thereof respectively, each of the first flow path and the second flow path has the inflow path, the straight flow path, and the turning flow path; each of the inflow paths of the first flow path and the second flow path is formed along the height direction of the turbine blade and is provided to be adjacent with one another.