IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0418859
(2003-04-18)
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발명자
/ 주소 |
- Venkataramani, Kattalaicheri Srinivasan
- Butler, Lawrence
- Lee, Ching Pang
- Maclin, Harvey Michael
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출원인 / 주소 |
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인용정보 |
피인용 횟수 :
7 인용 특허 :
5 |
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 spaced detonation passages are disposed
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 spaced detonation passages are disposed therethrough. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein alignable with the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases exit the cylindrical manner in a substantially tangential direction with respect to the outer circumferential surface to create a torque which causes the cylindrical member to rotate. Each detonation passage includes a first portion extending from the cylindrical member forward surface to a middle portion of the cylindrical member and a second portion extending from the first portion to the outer circumferential surface of the cylindrical member.
대표청구항
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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 sp
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 spaced detonation passages disposed therethrough; (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 detonation passages as said cylindrical member rotates; wherein detonation cycles are performed in said detonation passages so that combustion gases exit said cylindrical member in a substantially tangential direction with respect to said outer circumferential surface to create a torque which causes said cylindrical member to rotate.2. The pulse detonation system of claim 1, each said detonation passage comprising a first portion extending from said cylindrical member forward surface into a middle portion of said cylindrical member and a second portion extending from said first portion to said outer circumferential surface of said cylindrical member.3. The pulse detonation system of claim 2, wherein said first portion of said detonation passages is substantially linear.4. The pulse detonation system of claim 2, wherein said first portion of said detonation passages has a longitudinal axis extending therethrough substantially parallel to said longitudinal centerline axis.5. The pulse detonation system of claim 2, wherein said second portion of said detonation passages is substantially linear.6. The pulse detonation system of claim 2, wherein said second portion of said detonation passages is substantially non-linear.7. The pulse detonation system of claim 2, wherein said second portion of said detonation passages has a longitudinal axis extending therethrough oriented at an angle to said longitudinal axis extending through said first portion of said detonation passages.8. The pulse detonation system of claim 7, wherein said longitudinal axis extending through said second portion of said detonation passages is oriented substantially perpendicular to said longitudinal axis extending through said first portion of said detonation passages.9. The pulse detonation system of claim 7, wherein said longitudinal axis extending through said second portion of said detonation passages is oriented at an obtuse angle to said longitudinal axis extending through said first portion of said detonation passages.10. The pulse detonation system of claim 2, wherein said second portion of said detonation passages extends substantially tangentially to said outer circumferential surface of said cylindrical member.11. The pulse detonation system of claim 1, wherein said detonation passages are symmetrically spaced within said cylindrical member.12. The pulse detonation system of claim 1, wherein the number of said detonation passages in said cylindrical member is a function of a diameter for said cylindrical member and a length of each said detonation passage.13. The pulse detonation system of claim 1, wherein said detonation passages are aligned with each said port in a predetermined timing and sequence.14. The pulse detonation system of claim 1, wherein said detonation passages have a substantially constant diameter.15. The pulse detonation system of claim 1, wherein said detonation passages have a substantially convergent diameter for at least a portion thereof.16. The pulse detonation system of claim 2, wherein said first portions of said detonation passages are arranged in an annular configuration having a predetermined radius.17. The pulse detonation system of claim 2, said cylindrical member further comprising a plurality of portions extending substantially tangentially from said outer circumferential surface.18. The pulse detonation system of claim 17, wherein said second portion of said detonation passages extend through said extending portions of said cylindrical member.19. 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.20. The pulse detonation system of claim 19, wherein said air port is configured to extend annularly in said stator a predetermined amount.21. 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.22. The pulse detonation system of claim 21, further comprising a fuel manifold for supplying fuel to each said fuel port.23. The pulse detonation system of claim 21, further comprising a device for controlling the injection of fuel into said detonation passages through said fuel ports.24. The pulse detonation system of claim 1, each said group of ports in said stator further comprising a port having a device for initiating a detonation wave associated therewith.25. The pulse detonation system of claim 24, further comprising a device for controlling the initiation of detonation waves in said detonation passages by said initiation devices.26. 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 passage during a revolution of said cylindrical member.27. The pulse detonation system of claim 26, said stator including a predetermined amount of circumferential space between each said port group.28. The pulse detonation system of claim 1, said cylindrical member further comprising an additional stage of spaced detonation passages disposed therethrough.29. The pulse detonation system of claim 28, said detonation passages of said additional stage being positioned radially interior to said first stage of detonation passages.30. The pulse detonation system of claim 28, said detonation passages of said additional stage being positioned radially exterior to said first stage of detonation passages.31. The pulse detonation system of claim 28, wherein said detonation passages of said additional detonation stage are substantially aligned circumferentially with said detonation passages of said first stage.32. The pulse detonation system of claim 28, said stator further comprising a second group of ports formed therein alignable with said detonation passages of said additional detonation stage.33. The pulse detonation system of claim 1, further comprising a plurality of seals positioned between said stator and said forward surface of said cylindrical member.34. 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 a plurality of spaced detonation passages therein; (b) providing a stator in spaced relation to a forward surface of said cylindrical member, said stator having at least one group of ports formed therein; (c) connecting said cylindrical member to a drive shaft; (d) performing a detonation cycle in each said detonation passage; and, (e) producing a torque on said cylindrical member which causes said cylindrical member and said drive shaft to rotate. 35. The method of claim 34, said detonation cycle further comprising the steps of:(a) supplying compressed air to said detonation passages; (b) injecting fuel into said detonation passages; (c) initiating a detonation wave in said detonation passages; and, (d) exhausting products of combustion from said cylindrical member in a substantially tangential direction with respect to an outer circumferential surface thereof. 36. The method of claim 35, wherein said detonation wave is initiated at a predetermined point in said detonation passage.37. The method of claim 35, wherein said detonation wave is initiated by a device igniting fuel and air in said detonation passage.38. The method of claim 34, further comprising the step of causing said cylindrical member to rotate at a predetermined speed prior to injecting fuel into said detonation passages.39. The method of claim 34, further comprising the step of aligning said detonation passages 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 a port having an initiation device associated therewith in circumferentially spaced relation to said fuel port.40. 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 detonation passages disposed therethrough, wherein said cylindrical member is connected to said drive shaft; and, (2) 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 detonation passages as said cylindrical member rotates; wherein detonation cycles are performed in said detonation passages so that combustion gases exit said cylindrical member in a substantially tangential direction with respect to said outer circumferential surface to create a torque which causes said cylindrical member to rotate and power said fan section and said booster compressor.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) a port having a device associated therewith for initiating a detonation in said detonation passages. 42. 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 having a plurality of detonation passages disposed therethrough, wherein said cylindrical member is connected to said drive shaft; and, (2) a stator configured in spaced arrangement to 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 detonation passages as said cylindrical member rotates; wherein detonation cycles are performed in said detonation passages so that combustion gases exit said cylindrical member in a substantially tangential direction with respect to said outer circumferential surface to create a torque which causes said cylindrical member to rotate and power said compressor and said load.43. The gas turbine engine of claim 42, 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) a port having a device associated therewith for initiating a detonation in said detonation passages.
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