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A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough, the pulse detonation system includes an air inlet duct in flow communication with a source of compressed air, the air inlet duct including at least one port formed therein for permitting

A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough, the pulse detonation system includes an air inlet duct in flow communication with a source of compressed air, the air inlet duct including at least one port formed therein for permitting compressed air to flow therethrough, a fuel injector mounted to the air inlet duct in circumferentially spaced relation to each port, and a device mounted to the air inlet duct in circumferentially spaced relation to each fuel injector for initiating a detonation wave. A rotatable ring member is also positioned in coaxial relation around a portion of the air inlet duct, with the ring member including at least one stage of detonation disposed therein. Accordingly, a detonation wave is produced in each detonation stage and combustion gases following each detonation wave create a torque which causes the ring member to rotate. Each detonation stage in the ring member further includes a plurality of circumferentially spaced detonation ducts extending tangentially from an inner surface of the ring member, wherein the detonation ducts are aligned with each port, the fuel injector and the initiation device in a predetermined timing and sequence so that detonation waves are produced therein.

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1. 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

1. 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.2. The pulse detonation system of claim 1, each said detonation stage in said ring member further comprising a plurality of circumferentially spaced detonation ducts extending tangentially from an inner surface of said ring member.3. The pulse detonation system of claim 2, wherein said detonation ducts are aligned with each said port, said fuel injector and said initiation device in a predetermined timing and sequence so that said detonation wave is produced therein.4. The pulse detonation system of claim 2, wherein said plurality of detonation ducts for each said detonation stage are positioned in a distinct radial plane.5. The pulse detonation system of claim 2, wherein said plurality of detonation ducts in each said detonation stage are aligned circumferentially with said detonation ducts of an adjacent detonation stage.6. The pulse detonation system of claim 2, wherein said plurality of detonation ducts in each said detonation stage are staggered circumferentially with said detonation ducts of an adjacent detonation stage.7. The pulse detonation system of claim 2, wherein said plurality of detonation ducts of each said detonation stage are angled rearward with respect to an axis substantially perpendicular to said longitudinal centerline axis.8. The pulse detonation system of claim 2, wherein said plurality of detonation ducts of each said detonation stage are oriented substantially perpendicular to and offset from said longitudinal centerline axis.9. The pulse detonation system of claim 2, wherein said plurality of detonation ducts of each said detonation stage have a substantially constant diameter for at least a portion thereof.10. The pulse detonation system of claim 2, wherein said plurality of detonation ducts of each said detonation stage have a substantially convergent diameter for at least a portion thereof.11. The pulse detonation system of claim 2, wherein said plurality of detonation ducts of each said detonation stage are substantially linear from a first end adjacent an inner surface of said rotatable ring member to a second end adjacent an outer surface of said rotatable ring member.12. The pulse detonation system of claim 2, wherein said plurality of detonation ducts of each said detonation stage are curved for at least a portion thereof.13. The pulse detonation system of claim 1, wherein said rotatable ring member is hollow between said plurality of detonation ducts.14. The pulse detonation system of claim 1, said rotatable ring member further comprising a plurality of detonation stages positioned in spaced axial relation.15. The pulse detonation system of claim 1, further comprising a plurality of seals positioned between said air inlet duct and an inner surface of said rotatable ring member.16. The pulse detonation system of claim 1, further comprising a fuel manifold for supplying fuel to each said fuel injector.17. The pulse detonation system of claim 2, wherein each said initiation device is activated when in alignment with each detonation duct of each said detonation stage.18. The pulse detonation system of claim 2, wherein each said initiation device is activated in accordance with a predetermined delay between detonation ducts of each said detonation stage.19. The pulse detonation system of claim 2, further comprising a device for controlling the injection of fuel into said detonation ducts of each said detonation stage by said fuel injectors.20. The pulse detonation system of claim 2, further comprising a device for controlling the initiation of detonation waves in said detonation ducts of each said detonation stage by said initiation devices.21. The pulse detonation system of claim 1, further comprising a plurality of air ports, fuel injectors and initiation devices provided in and mounted to said air inlet duct.22. The pulse detonation system of claim 21, said air inlet duct including a predetermined amount of circumferential space between each said initiation device and an adjacent port for permitting compressed air to flow therethrough.23. The pulse detonation system of claim 21, wherein a plurality of detonation cycles in a predetermined timing and sequence occur in each said detonation stage during a revolution of said ring member.24. A gas turbine engine, comprising:(a) a fan section at a forward end of said gas turbine engine including at least a first fan blade row connected to a drive shaft; (b) a booster compressor positioned downstream of said fan section, said booster compressor including a first compressor blade row and a second compressor blade row connected to said drive shaft and interdigitated with said first compressor blade row; and, (c) a pulse detonation system for powering said drive shaft, said pulse detonation system further comprising: (1) an air inlet duct in flow communication with said booster compressor, said air inlet duct including at least one port formed therein for permitting compressed air to flow therethrough; (2) a fuel injector mounted to said air inlet duct in circumferentially spaced relation to each said port; (3) a device mounted to said air inlet duct in circumferentially spaced relation to each said fuel injector for initiating a detonation wave; and, (4) a rotatable ring member positioned in coaxial relation around a portion of said air inlet duct and connected to said drive shaft, said ring member including at least one stage of detonation disposed therein; wherein detonation waves are produced in each said detonation stage such that combustion gases following said detonation waves create a torque which causes said ring member to rotate and power said fan section and said booster compressor.25. The gas turbine engine of claim 24, each said detonation stage further comprising a plurality of circumferentially spaced detonation ducts extending tangentially from a an inner surface of said ring member.26. The gas turbine engine of claim 25, wherein said detonation ducts are aligned with said port, said fuel injector and said initiation device in a predetermined timing and sequence so that a detonation cycle is performed therein.27. The gas turbine engine of claim 25, wherein said detonation ducts of each said detonation stage are located within a distinct radial plane.28. The gas turbine engine of claim 24, said rotatable ring member further comprising a plurality of detonation stages positioned in spaced axial relation.29. The gas turbine engine of claim 25, further comprising a nozzle plenum in flow communication with outlets of said detonation ducts so that additional thrust is produced.30. The gas turbine engine of claim 29, further comprising at least one turbine stage in flow communication with said nozzle plenum.