Patent ID: 6494031
Filing Date: 2002-12-17
Classification: F23L,F23R,Y02E

Abstract:
A gas turbine apparatus comprising:a gas turbine having a compressor, a combustor, and a turbine rotor; and a heat exchanger attached to said gas turbine for exchanging heat between a compressed air ejected from said compressor and an exhaust gas ejected from said turbine rotor, said heat exchanger being positioned axially rearward with respect to said gas turbine and connected to an exhaust gas outlet side of a back portion of said gas turbine, said heat exchanger having a core including a front, a back and an outer side, and a casing enclosing said core, said core including a plurality of heat transfer plates that partition an internal space of said core into a first path for flowing said compressed air and a second path for flowing said exhaust gas, wherein an inlet for flowing said compressed air into said first path is formed on said outer side of a back portion of said core, wherein an outlet of said compressed air passing through said first path is formed on said outer side of a front portion of said core, wherein an introduction path is formed in an annular shape between said core and said casing so that said compressed air is introduced through said introduction path from a position in front of said core via a circumferential outside around said outer side of said core into said inlet, and wherein said exhaust gas is introduced from said front of said core into said second path and ejected from said back of said core.