IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0405561
(2003-04-02)
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발명자
/ 주소 |
- Butler, Lawrence
- Venkataramani, Kattalaicheri Srinivasan
- Murrow, Kurt David
- Leyva, Ivett Alejandra
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출원인 / 주소 |
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인용정보 |
피인용 횟수 :
7 인용 특허 :
6 |
초록
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A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation cham
A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation chambers is disposed therein. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement around the forward surface, the aft surface, and the outer circumferential surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein which sequentially align with the detonation chambers as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation chambers of each detonation stage so that reaction forces induced by the detonation cycles create a torque which causes the cylindrical member to rotate. Each detonation chamber includes a first open end located adjacent the outer circumferential surface of the cylindrical member and a second closed end located within a middle portion of the cylindrical member.
대표청구항
▼
1. 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 ci
1. 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.2. The pulse detonation system of claim 1, wherein a focused shock wave is formed in said detonation chambers to initiate detonation of a fuel/air mixture therein.3. The pulse detonation system of claim 2, wherein said detonations have an initiation point adjacent said second end of each said detonation chamber.4. The pulse detonation system of claim 1, wherein an end wall defining said second end of each said detonation chamber is contoured.5. The pulse detonation system of claim 1, each said group of ports in said stator further comprising an air port in flow communication with a source of compressed air.6. The pulse detonation system of claim 1, each said group of ports in said stator further comprising a fuel port in flow communication with a fuel source.7. The pulse detonation system of claim 1, each said group of ports in said stator further comprising an exhaust port.8. The pulse detonation system of claim 1, further comprising a plurality of port groups provided in said stator, wherein a plurality of detonation cycles occur in a predetermined timing and sequence in each said detonation stage during a revolution of said cylindrical member.9. The pulse detonation system of claim 1, wherein said detonation chambers of each detonation stage are symmetrically spaced circumferentially within said rotor.10. The pulse detonation system of claim 1, said cylindrical member further comprising a plurality of internal passages formed therein, each said internal passage including a first end in flow communication with a first detonation chamber and a second end in flow communication with a second detonation chamber.11. The pulse detonation system of claim 10, wherein said first end of each said internal passage is located adjacent a closed end of said first detonation chamber and said second end of each said internal passage is located adjacent an open end of said second detonation chamber.12. The pulse detonation system of claim 11, wherein said first detonation chamber is located upstream of said second detonation chamber with respect to the direction of rotation for said rotor.13. The pulse detonation system of claim 10, wherein said first and second detonation chambers are in the same detonation stage.14. The pulse detonation system of claim 10, wherein said first and second detonation chambers are in adjacent detonation stages of said cylindrical member.15. The pulse detonation system of claim 1, wherein said detonation chambers of each said detonation stage are positioned substantially in a distinct radial plane through said cylindrical member.16. The pulse detonation system of claim 1, wherein said plurality of detonation chambers of each said detonation stage are angled circumferentially so as to not be substantially perpendicular to said longitudinal centerline axis.17. The pulse detonation system of claim 16, wherein said port groups in said stator are angled circumferentially so as to be alignable with said detonation chambers.18. The pulse detonation system of claim 1, said cylindrical member further comprising a plurality of detonation stages positioned in spaced axial relation.19. The pulse detonation system of claim 1, said cylindrical member further comprising a plurality of ports formed in a middle portion, each said port having a first end positioned adjacent said closed end of each detonation chamber and in flow communication therewith and a second end adjacent said aft surface thereof.20. The pulse detonation system of claim 19, said stator further comprising at least one port formed in an aft portion thereof, wherein said cylindrical member ports are periodically aligned with said aft stator port so that gases in said detonation chambers are vented therethrough.21. The pulse detonation system of claim 19, further comprising at least one device for initiating a detonation positioned adjacent said aft surface of said cylindrical member, wherein each said cylindrical member port is periodically aligned therewith.22. The pulse detonation system of claim 1, further comprising a fuel manifold for supplying fuel to each said fuel port.23. A pulse detonation system for a gas turbine engine having a longitudinal 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; (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; (d) a fuel manifold formed in said shaft in flow communication with a source of fuel; and, (e) a plurality of fuel passages formed in a middle portion of said cylindrical member, wherein each fuel passage is in flow communication with said fuel manifold at a first end and one of said detonation chambers at a second end. 24. The pulse detonation system of claim 23, further comprising:(a) a heat exchanger positioned around each said detonation chamber, wherein said second end of each fuel passage is in flow communication therewith; and, (b) a device for injecting fuel from said heat exchanger into each detonation chamber. 25. A method of providing power to a drive shaft in a gas turbine engine, comprising the following steps:(a) providing a rotatable cylindrical member having at least one stage of circumferentially spaced detonation chambers therein, wherein each said detonation chamber includes an open first end located adjacent an outer circumferential surface of said cylindrical member and a closed second end located within a middle portion of said cylindrical member; (b) providing a stator in spaced relation around said cylindrical member, said stator having at least one group of ports formed therein which sequentially align with said open end of said detonation chambers as said cylindrical member rotates; (c) connecting said cylindrical member to a drive shaft; (d) performing a detonation cycle in each said detonation chamber; and, (e) producing a torque on said cylindrical member which causes said cylindrical member and said drive shaft to rotate. 26. The method of claim 25, said detonation cycle further comprising the steps of:(a) supplying compressed air to said detonation chambers; (b) injecting fuel into said detonation chambers; (c) initiating a detonation of a fuel/air mixture in said detonation chambers; and, (d) exhausting products of combustion from said detonation chambers. 27. The method of claim 26, wherein said detonation of said fuel/air mixture in said detonation chamber is initiated by a focused shock wave formed therein.28. The method of claim 26, wherein said detonation is initiated at a predetermined point adjacent said closed end of said detonation chamber.29. The method of claim 26, wherein said torque is created by reaction forces induced by said detonation cycle being applied to an end wall of said detonation chamber.30. The method of claim 26, wherein detonation of said fuel/air mixture in said detonation chamber is initiated by an ignition device.31. The method of claim 26, further comprising the step of causing said cylindrical member to rotate at a predetermined speed prior to injecting fuel into said detonation chambers.32. The method of claim 26, further comprising the step of purging combustion gases from said detonation chambers.33. The method of claim 26, further comprising the step of aligning said detonation chambers of each said detonation stage in a predetermined timing and sequence with an air port in said stator, a fuel port in circumferentially spaced relation to said air port, and an exhaust port in circumferentially spaced relation to said fuel port.34. 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) 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 an outer circumferential surface of said cylindrical member and a closed second end located within a middle portion of said cylindrical member, wherein said cylindrical member is connected to said drive shaft; and, (2) 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 said detonation stage so that reaction forces induced by said detonation cycles create a torque which causes said cylindrical member to rotate and power said fan section and said booster compressor.35. The gas turbine engine of claim 34, each said group of ports in said stator further comprising:(a) an air port in flow communication with a source of compressed air; (b) a fuel port in flow communication with a fuel source; and, (c) an exhaust port. 36. The gas turbine engine of claim 35, further comprising a precombustor in flow communication with a fuel supply and a supply of compressed air so as to produce detonable combustion products therein, said precombustor being in flow communication with each said fuel port in said stator.37. The pulse detonation system of claim 34, said cylindrical member further comprising a plurality of internal passages formed therein, each said internal passage including a first end in flow communication with a first detonation chamber and a second end in flow communication with a second detonation chamber.38. The pulse detonation system of claim 34, said cylindrical member further comprising a plurality of ports formed in a middle portion, each said port having a first end positioned adjacent said closed end of each detonation chamber and in flow communication therewith and a second end adjacent said aft surface thereof, wherein gases in said detonation chamber are vented therethrough.39. The pulse detonation system of claim 38, further comprising at least one device for initiating a detonation positioned adjacent said aft surface of said cylindrical member, wherein each said cylindrical member port is periodically aligned therewith.40. A gas turbine engine, comprising:(a) a bellmouth at a forward end of said gas turbine engine; (b) a compressor positioned downstream of and in flow communication with said bellmouth, said compressor including a first compressor blade row and a second blade row connected to a drive shaft and interdigitated with said first compressor blade row; (c) a load connected to said drive shaft; and, (d) a pulse detonation system for powering said drive shaft, said pulse detonation system further comprising: (1) 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 an outer circumferential surface of said cylindrical member and a closed second end located within a middle portion of said cylindrical member, wherein said cylindrical member is connected to said drive shaft; and, (2) 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 said detonation stage so that reaction forces induced by said detonation cycles create a torque which causes said cylindrical member to rotate and power said compressor and said load.41. The gas turbine engine of claim 40, each said group of ports in said stator further comprising:(a) an air port in flow communication with a source of compressed air; (b) a fuel port in flow communication with a fuel source; and, (c) an exhaust port. 42. The pulse detonation system of claim 40, said cylindrical member further comprising a plurality of internal passages formed therein, each said internal passage including a first end in flow communication with a first detonation chamber and a second end in flow communication with a second detonation chamber.43. The pulse detonation system of claim 40, said cylindrical member further comprising a plurality of ports formed in a middle portion, each said port having a first end positioned adjacent said closed end of each detonation chamber and in flow communication therewith and a second end adjacent said aft surface thereof, wherein gases in said detonation chamber are vented therethrough.44. The pulse detonation system of claim 43, further comprising at least one device for initiating a detonation positioned adjacent said aft surface of said cylindrical member, wherein each said cylindrical member port is periodically aligned therewith.45. The pulse detonation system of claim 1, where no ignition device is in communication with said detonation chambers.46. The pulse detonation system of claim 1, wherein each said detonation chamber is substantially linear from said first end to said second end has has a substantially constant diameter.
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