Patent ID: 6308513
Filing Date: 2001-10-30
Classification: F01D,F02C,Y02E,Y02T

Abstract:
A gas turbine comprising:a compressor for introducing compressed air;a turbine having an output shaft for driving said compressor; anda combustor for combusting compressed air and fuel to produce motive gases to drive said turbine;said turbine including an inlet to introduce a jet stream of said motive gases in a tangential direction, an outlet for exhausting expanded gases, a stator having at least one flow deflector extending radially inward at a position between said inlet and said outlet, and a turbine rotor rotatably received in said stator, said turbine rotor having an annular jet stream path communicating with said inlet and said outlet to allow said jet stream to run in a circumferential direction, and a plurality of turbine blades formed around a periphery of said turbine rotor in close proximity with said annular jet stream path, and said flow deflector being disposed in said annular jet stream path to deflect said jet stream toward said turbine blades.