Patent ID: 6817190
Filing Date: 2004-11-16
Classification: F01D,F02C,F05D

Abstract:
In a gas turbine engine having a compressor, a combustor for producing hot fluid flow, a power turbine having a rotor disk positioned immediately downstream of the combustor, the rotor disk having a plurality of blades for receiving the hot fluid flow, each said blade comprising:a root portion; an airfoil having two sides along which the hot fluid flows, an inlet edge positioned downstream of the combustor, an outlet edge positioned downstream of said inlet edge, a blade flow portion located between said inlet edge and said outlet edge on each of said sides of said airfoil; and a platform member extending transversally with respect to said airfoil and having an upstream portion protruding with respect to said inlet edge in the direction toward the combustor, said platform member further having at least a pair of openings on each of said sides of said airfoil, and arranged in series along said blade flow portion for directing fluid from the compressor to flow along said blade flow portion to create a thermal insulating boundary between the hot fluid and said sides of said airfoil, one of said openings of each of said pair of openings that is remote from said inlet edge defining an inclined passage in said platform member, the other opening of each of said pair of openings being separated by a partition from said one opening of each of said pair of openings and having an opposite wall extending in a spaced relation to said inlet edge.