Patent ID: 6889505

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 circumferentially spaced detonation chambers disposed therein, each said detonation chamber including an open first end located adjacent said outer circumferential surface of said cylindrical member and a closed second end located within a middle portion of said cylindrical member; (b) a shaft rotatably connected to said cylindrical member; and, (c) a stator configured in spaced arrangement around said forward surface, said aft surface, and said outer circumferential surface of said cylindrical member and a portion of said shaft, said stator including at least one group of ports formed therein which sequentially align with said open end of said detonation chambers as said cylindrical member rotates; wherein detonation cycles are performed in said detonation chambers of each detonation stage so that reaction forces induced by said detonation cycles create a torque which causes said cylindrical member to rotate.