Patent ID: 7124573

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 passages disposed therethrough, each said detonation passage further comprising: (1) a leading portion positioned adjacent said forward surface of said cylindrical member, said leading portion having a centerline therethrough oriented at a designated angle to an axis extending substantially parallel to said longitudinal centerline axis within a specified plane; (2) a trailing portion positioned adjacent said aft surface of said cylindrical member, said trailing portion having a centerline therethrough oriented at a designated angle to said axis within said specified plane; and, (3) a middle portion connecting said leading and trailing portions, said middle portion having a centerline therethrough with a substantially constantly changing slope in said specified plane; (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 leading portions of said detonation passages as said cylindrical member rotates; wherein detonation cycles are performed in said detonation passages so that combustion gases interact therewith to create a torque which causes said cylindrical member to rotate.