Gas turbine combustion apparatus
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0979738
(2004-11-03)
|
등록번호 |
US-7299618
(2007-11-27)
|
우선권정보 |
JP-2003-409792(2003-12-09) |
발명자
/ 주소 |
- Terazaki,Masao
- Kanezawa,Yoshiyuki
- Horikawa,Hideto
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출원인 / 주소 |
- Mitsubishi Heavy Industries, Ltd.
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대리인 / 주소 |
Westerman, Hatorri, Daniels & Adrian, LLP.
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인용정보 |
피인용 횟수 :
8 인용 특허 :
9 |
초록
▼
A gas turbine combustion apparatus has a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each combustor comprising a combustor inner tube and a combustor transition pipe, but lacks a turbine bypass mechanism for controlling the amou
A gas turbine combustion apparatus has a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each combustor comprising a combustor inner tube and a combustor transition pipe, but lacks a turbine bypass mechanism for controlling the amount of compressed air discharged from a compressor into the turbine casing chamber. The combustion apparatus comprises an exhaust port member fitted into a manhole opening in the casing and communicating with the outside of the turbine casing chamber, bleeding pipes for uniformly bleeding compressed air discharged into the turbine casing chamber, a circular pipe for recovering compressed air bled by the bleeding pipes and discharging the compressed air to the exhaust port member, and an opening and closing valve for controlling the amount of exhaust which the circular pipe discharges to the outside of the turbine casing chamber via the exhaust port member, thereby possessing a turbine bypass mechanism.
대표청구항
▼
What is claimed is: 1. A gas turbine combustion apparatus having a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each of said combustors comprising a combustor inner tube and a combustor transition pipe, and comprising: one or mo
What is claimed is: 1. A gas turbine combustion apparatus having a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each of said combustors comprising a combustor inner tube and a combustor transition pipe, and comprising: one or more exhaust ports opening in said casing and communicating with an outside of said turbine casing chamber and having an exhaust pipe; one or more bleeding means for uniformly bleeding compressed air discharged into said turbine casing chamber; one or more recovery means for recovering compressed air bled by said bleeding means and discharging said compressed air to said exhaust ports; and exhaust control means for controlling an amount of exhaust which said recovery means discharge to said exhaust ports, wherein said recovery means is a circular pipe extending along said circumferential direction within said turbine casing chamber, and formed in a toroidal shape. 2. A gas turbine combustion apparatus having a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each of said combustors comprising a combustor inner tube and a combustor transition pipe, and comprising: one or more exhaust ports opening in said casing and communicating with an outside of said turbine casing chamber; one or more bleeding means for uniformly bleeding compressed air discharged into said turbine casing chamber; one or more recovery means for recovering compressed air bled by said bleeding means and discharging said compressed air to said exhaust ports; and exhaust control means for controlling an amount of exhaust which said recovery means discharge to said exhaust ports, wherein said exhaust control means is an opening and closing valve provided in said exhaust pipe; and wherein said recovery means is a circular pipe extending along said circumferential direction within said turbine casing chamber, and formed in a toroidal shape. 3. The gas turbine combustion apparatus according to claim 1 or claim 2, wherein said one or more bleeding means is arranged in said circumferential direction within said turbine casing chamber. 4. The gas turbine combustion apparatus according to claim 3, wherein said one or more bleeding means comprises one or more bleeding pipe opening in an extending direction of said combustors. 5. The gas turbine combustion apparatus according to claim 4, wherein said one or more bleeding pipe comprises one or more bleeding port and each pipe and each port is arranged on a same circumference. 6. The gas turbine combustion apparatus according to claim 5, wherein each of said one or more bleeding pipe is provided between a combustor of said plurality of combustors and another combustor of said plurality of combustors adjacent to said combustor. 7. The gas turbine combustion apparatus according to claim 6, wherein said one or more bleeding pipe is provided between a combustor of said plurality of combustors and another combustor of said plurality of combustors. 8. The gas turbine combustion apparatus according: to claim 7, wherein said exhaust port is a manhole used during work within said turbine casing chamber. 9. A gas turbine combustion apparatus having a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each of said combustors comprising a combustor inner tube and a combustor transition pipe, and comprising: one or more exhaust ports opening in said casing and communicating with an outside of said turbine casing chamber; one or more bleeding means for uniformly bleeding compressed air discharged into said turbine casing chamber; one or more recovery means for recovering compressed air bled by said bleeding means and discharging said compressed air to said exhaust ports; and exhaust control means for controlling an amount of exhaust which said recovery means discharge to said exhaust ports, wherein said bleeding means are arranged in said circumferential direction within said turbine casing chamber. 10. A gas turbine combustion apparatus having a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each of said combustors comprising a combustor inner tube and a combustor transition pipe, and comprising: one or more exhaust ports opening in said casing and communicating with an outside of said turbine casing chamber and having an exhaust pipe; one or more bleeding means for uniformly bleeding compressed air discharged into said turbine casing chamber; one or more recovery means for recovering compressed air bled by said bleeding means and discharging said compressed air to said exhaust ports; and exhaust control means for controlling an amount of exhaust which said recovery means discharge to said exhaust ports, wherein said exhaust control means is an opening and closing valve provided in said exhaust pipe, wherein said bleeding means are arranged in said circumferential direction within said turbine casing chamber. 11. The gas turbine combustion apparatus according to claim 9 or claim 10, wherein said bleeding means are bleeding pipes opening in an extending direction of said combustors. 12. The gas turbine combustion apparatus according to claim 11, wherein said bleeding pipes comprise bleeding ports which are arranged on a same circumference. 13. The gas turbine combustion apparatus according to claim 12, wherein each of said bleeding pipes is provided between said combustor and said combustor adjacent thereto. 14. The gas turbine combustion apparatus according to claim 13, wherein said bleeding pipes are provided between said combustors. 15. The gas turbine combustion apparatus according: to claim 14, wherein said exhaust port is a manhole used during work within said turbine casing chamber.
이 특허에 인용된 특허 (9)
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Scalzo Augustine J. (Longwood FL), Coal fired gas turbine system with integral topping combustor.
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Johnson Robert H. (Bolton Landing NY) Wilkes Colin (Scotia NY), Combustion control system.
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Slocum Gale V. (Clifton Park NY) Myers Albert (Amsterdam NY) Beebe Kenneth W. (Saratoga NY), Combustor external air staging device.
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Bunker, Ronald Scott, Double wall combustor liner segment with enhanced cooling.
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Suenaga, Kiyoshi; Mandai, Shigemi; Tanaka, Katsunori, Gas turbine combustor having bypass and annular gas passage for reducing uneven temperature distribution in combustor tail cross section.
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Butt Graham P. (Ancaster CAX), Gas turbine combustor transition duct forced convection cooling.
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Nagata, Shouichi; Komiyama, Hiroya, Gas turbine plant and method of controlling gas turbine plant.
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Widener,Stanley Kevin; McMahan,Kevin Weston; Johnson,Thomas Edward, One-piece can combustor.
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Cleary Edward N. G. (San Diego CA), Primary zone air proportioner.
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Kitamura, Tsuyoshi; Masaki, Shinichiro, Aircraft gas turbine.
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Ziminsky, Willy Steve; Wolfe, Christopher Edward; Meshkov, Sergey Anatolievich; Oskin, Sergey Adolfovich, Apparatus and method for a combustor.
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Kreutzer, Philipp; Larson, Marco; Sternemann, Ansgar, Cooling air line for removing cooling air from a manhole of a gas turbine.
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Hessler, William K.; Popovic, Predrag; Nyberg, Charles, Method and apparatus for cooling and dilution tuning a gas turbine combustor liner and transition piece interface.
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Araki, Masato; Iwasaki, Yoshifumi, Method of preventing deformation in gas turbine casing, purging device for executing this method, and gas turbine provided with this device.
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Intile, John Charles; Kirtley, Kevin Richard, Method of recovering energy in a steam-cooled gas turbine.
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Nenmeni, Vijay Anand Raghavendran; Alexander, Michael Joseph; Plummer, Paul William; Janssen, Timothy Lee, System and method for air extraction from gas turbine engines.
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Miller, Harold Edward, System and method for removing heat from a turbomachine.
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