Patent ID: 6711889
Filing Date: 2004-03-30
Classification: F02C,F23C,F23R,F28D,Y10S

Abstract:
A gas turbine engine, comprising:a cylindrical-shaped casing comprising a circular shoulder portion that includes a casing opening at a first end thereof, and a bottom plate sealing a second end of said casing on an opposite side thereof; a heat exchanger comprising two spaced-apart divider walls which extend spirally inwards from an inner perimeter of said casing towards an inner chamber inside said casing, and a top plate spacing a gap with the shoulder portion of said casing, said two spaced-apart divider walls sealing both ends with the top plate and the bottom plate and forming spirally a compressed air passageway and a turbine exhaust gas passageway adjacent to each other throughout the heat exchanger; a combustor installed in the inner chamber of said casing comprising a main exhaust opening formed towards the first end, and a sidewall formed with a plurality of air holes therethrough; and a turbine engine rotor comprising a coaxial compressor rotor and a turbine rotor, each of the rotors having a plurality of blades, wherein the blades of compressor rotor are positioned facing said casing opening, and the blades of turbine rotor are positioned facing said main exhaust opening.