Patent ID: 6397577
Filing Date: 2002-06-04
Classification: F01D,F02C,Y02T

Abstract:
A gas turbine engine structure, comprising:(a) a first substantially fixed outer housing defined along a substantially central axis of the engine structure; (b) a second substantially fixed inner housing disposed substantially coaxially of said outer housing; (c) a generally tubular shaped rotor rotatably disposed between said first and second housings, said rotor defining a compressor region of the engine structure between said rotor and one of said first and second housings, and defining a turbine region of the engine between said rotor and the other of said first and second housings; (d) a combustor disposed at a first end of said first and second housings and operatively communicating with said turbine region and said compressor region; (e) a plurality of compressor vanes mounted on one of the inner surface of said outer housing and outer surface of said inner housing, and a plurality of turbine vanes mounted on the other of said inner surface of said outer housing and said outer surface of said inner housing; and (f) a plurality of compressor blades mounted on said rotor in interdigitating relationship with said compressor vanes, and a plurality of turbine blades mounted on said rotor in interdigitating relationship with said turbine vanes.