Patent ID: 6305157
Filing Date: 2001-10-23
Classification: F01D,F02C,F04D

Abstract:
A gas turbine engine comprising:a compressor for producing a compressed fluid flow;a fuel source;a source of combustion air;a casing;a combustion zone in said casing, said combustion zone communicating with said fuel source and with said source of combustion air to prepare a heated fluid; anda power turbine rotor disk having blades, each of said blades comprising an external airfoil surface with a leading surface and a trailing surface, an inlet edge positioned downstream of said combustion zone, an outlet edge positioned downstream of said inlet edge, a blade flow portion located adjacent said trailing surface of said external airfoil surface and between said inlet edge and said outlet edge, and an internal passage with at least one opening to said external airfoil surface, said internal passage receiving said compressed fluid from said compressor and passing said compressed fluid through said at least one opening to said blade flow portion, said compressed fluid flow moving along said blade flow portion so as to create a thermal insulating boundary between said heated fluid and said trailing surface of said external airfoil surface.