| 摘要 |
A pulse detonation system (46) for a gas turbine engine (10) having a longitudinal centerline axis (12) extending therethrough, where the pulse detonation syst em (46) includes an air inlet duct (48) in flow communication with a source of compressed air, the air inlet duct (48) including at least one port (50) formed therein for permitting compressed air (26) to flow therethrough, a fuel injector (52) mounted to th e air inlet duct (48) in circumferentially spaced relation to each port (50), and a devi ce (54) mounted to the air inlet duct (48) in circumferentially spaced relation to each fuel injector (52) for initiating a detonation wave. A rotatable ring member (56) is also positioned in coaxial relation around a portion of the air inlet duct (48), with the ring member (56) including at least one stage of detonation (58/60/62/64) dispose d therein. Accordingly, a detonation wave is produced in each detonation stage (58,60,62,64) and combustion gases following each detonation wave create a torque which causes the ring member (56) to rotate. Each detonation stage (58,60,62,64) in the ring member (56) further includes a plurality of circumferentially spaced detonation ducts (66) extending tangentially from an inner surface (74) of the ring member (56), wherein the detonation ducts (66) are aligned with each port (50), the fuel injector (52) and the initiation device (54) in a predetermined timing and sequence s o that detonation waves are produced therein.
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