Patent ID: 6928804

Claim:
A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising: (a) an air inlet duct in flow communication with a source of compressed air, said air inlet duct including at least one port formed therein for permitting compressed air to flow therethrough; (b) a fuel injector mounted to said air inlet duct in circumferentially spaced relation to each said port; (c) a device mounted to said air inlet duct in circumferentially spaced relation to each said fuel injector for initiating a detonation wave; and, (d) a rotatable ring member positioned in coaxial relation around a portion of said air inlet duct, said ring member including at least one stage of detonation disposed therein; wherein detonation waves are produced in each said detonation stage and combustion gases following each said detonation wave create a torque which causes said ring member to rotate.