Patent ID: 6351937
Filing Date: 2002-03-05
Classification: F01D,F04D

Abstract:
A gas turbine plant comprising:an air compressor; a gas turbine combustor; a gas turbine, said air compressor, said gas turbine combustor and said gas turbine being operatively connected in series; an air compressor shaft accommodated in the air compressor and composed of discs piled up along an axial direction of the air compressor shaft; a gas turbine shaft accommodated in the gas turbine and composed of discs piled up along an axial direction of the gas turbine shaft; and an intermediate shaft interposed between the air compressor shaft and the gas turbine shaft, wherein at least one of the discs of the air compressor shaft and the discs of the gas turbine shaft is provided with a coaxial, air guiding, bulged portion which is directly exposed to a flow of high pressure air extracted from said air compressor, and which redirects the flow of high pressure air into a passage structure associated with said intermediate shaft.