Patent ID: 6931858

Claim:
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, each said detonation passage including at least a portion thereof with a longitudinal axis extending therethrough which is oriented at a circumferential angle to said longitudinal centerline axis; (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 aft surface of said cylindrical member to create a torque which causes said cylindrical member to rotate.