Patent ID: 6904750
Filing Date: 2005-06-14
Classification: F02C,F02K

Abstract:
1. A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising: (a) a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, said cylindrical member including at least one stage of spaced detonation passages disposed therethrough; (b) a shaft rotatably connected to said cylindrical member; and, (c) a stator configured in spaced arrangement with said forward surface of said cylindrical member and a portion of said shaft, said stator including at least one group of ports formed therein alignable with said detonation passages as said cylindrical member rotates; wherein detonation cycles are performed in said detonation passages so that combustion gases exit said cylindrical member in a substantially tangential direction with respect to said outer circumferential surface to create a torque which causes said cylindrical member to rotate.