Gas turbine combustor
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
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출원번호 |
US-0382877
(2003-03-07)
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우선권정보 |
JP-0000643 (2002-03-08) |
발명자
/ 주소 |
- Hayashi, Shigeru
- Yamada, Hideshi
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출원인 / 주소 |
- National Aerospace Laboratory of Japan
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대리인 / 주소 |
Westerman Hattori Daniels &
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인용정보 |
피인용 횟수 :
7 인용 특허 :
2 |
초록
▼
The present invention provides a gas turbine combustor which makes it possible to achieve both a high combustion efficiency and low NOx emissions characteristics over a wide output power range without using a device that can vary the flow rate of the air used for combustion, by burning a lean mixtur
The present invention provides a gas turbine combustor which makes it possible to achieve both a high combustion efficiency and low NOx emissions characteristics over a wide output power range without using a device that can vary the flow rate of the air used for combustion, by burning a lean mixture using high-temperature burned gas. The gas turbine combustor 10 comprises pre-mixture injection tubes 16 which conduct a mixture of fuel and air into a combustion chamber 11. The mixture from the pre-mixture injection tubes 16 is injected toward burned gas 19a present on the downstream side of the flame 19, which is injected from burners 15 that open into the combustion chamber 11, and this mixture is mixed with the burned gas 19a. Even in a mixture which is leaner than the lower limit of inflammability, the radicals in the burned gas 19a are effective in initiating reactions, so that the combustion of the mixture can be started. Since the burned gas has a lower oxygen concentration than fresh mixture, and since the pre-mixture is dispersed in space, the generation of NOx can be suppressed.
대표청구항
▼
1. A gas turbine combustor comprising:burners whose discharge ports open into a combustion chamber; and pre-mixture injection tubes which inject a mixture of fuel and air into said combustion chamber, wherein said mixture that is supplied from said pre-mixture injection tubes is injected into burned
1. A gas turbine combustor comprising:burners whose discharge ports open into a combustion chamber; and pre-mixture injection tubes which inject a mixture of fuel and air into said combustion chamber, wherein said mixture that is supplied from said pre-mixture injection tubes is injected into burned gas of a mixture discharged from said burners, and mixed with said burned gas to react, wherein said pre-mixture injection tubes include a flow-deflecting body which turns said mixture to one side at outlet ports of said pre-mixture injection tubes in order to inject said mixture into said burned gas to react, and wherein said flow-deflecting body is a bridge body that is installed across said pre-mixture injection tubes, and said bridge body has a wall surface with a U-form or V-form cross sectional shape in which the sharp edge faces upstream in order to split said mixture and simultaneously turn the mixture to one side. 2. The gas turbine combustor according to claim 1, wherein said wall surface of said bridge body is formed as a plane or smoothly curved surface with a straight line extending in the direction that cuts across said pre-mixture injection tube as a generatrix.3. The gas turbine combustor according to claim 1, wherein said pre-mixture injection tubes each comprise a straight tube part and a bent opening part which is bent from said straight tube part and extends to said outlet port, said bridge body is installed so that this bridge body cuts across said bent opening part from the inside of the bend to the outside of the bend of said bent opening part, and said bridge body is formed so that this bridge body becomes wider toward the outside of said bend.4. The gas turbine combustor according to claim 1, wherein said pre-mixture injection tubes each have open edges which recede in the axial direction of the pre-mixture injection tube as they move away from the connecting part with said bridge body, on both sides facing said bridge body.5. The gas turbine combustor according to claim 1, wherein said pre-mixture injection tubes each have bent side wall parts that widen and open to the side as they approach the open edges of said outlet port on both sides facing said bridge body.6. The gas turbine combustor according to claim 1, wherein a slit is formed in each of said bridge bodies such that the slit extends in the bridging direction in the center of the bridge body with respect to the direction of width.7. The gas turbine combustor according to claim 1, wherein each of said bridge bodies is constructed from at least three bridge branching parts that extend radially from the center of the cross section of said outlet port of said pre-mixture injection tube.8. The gas turbine combustor according to claim 1, wherein said combustion chamber has a dome wall part to which said burners are attached, and a tubular wall part that extends downstream from said dome wall part, and said pre-mixture injection tubes are attached in said dome wall part in a state in which the pre-mixture injection tubes are substantially parallel to said burners, and said outlet ports of the pre-mixture injection tubes open at points further downstream than said discharge ports of said burners.9. The gas turbine combustor according to claim 1, wherein said combustion chamber has a dome wall part to which said burners are attached, and a tubular wall part that extends downstream from said dome wall part, and said pre-mixture injection tubes are attached in said tubular part in a state in which the pre-mixture injection tubes are inclined with respect to said burners, and said outlet ports of the pre-mixture injection tubes open at points further downstream than said discharge ports of said burners.10. The gas turbine combustor according to claim 1, wherein said combustion chamber has a dome wall part comprising a base end portion and an expanded portion on the upstream side, and a tubular wall part that extends downstream from said dome wall part, said burners are attached to said expanded portion, and said pre-mixture injection tubes are attached in said base end portion in a state in which said outlet ports of the pre-mixture injection tubes open at points further downstream than said discharge ports of said burners.11. The gas turbine combustor according to claim 1, wherein said burners are disposed at intervals in the circumferential direction, and one or a plurality of said pre-mixture injection tubes are disposed between adjacent burners.
이 특허에 인용된 특허 (2)
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Keller Jakob (Dottikon CHX), Combustion chamber of a gas turbine including pilot burners having precombustion chambers.
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Tsukahara Satoshi (Hitachi JPX) Inoue Hiroshi (Hitachi JPX) Hayashi Noriyuki (Hitachi JPX) Iwai Kazumi (Mito JPX) Innami Tamio (Tsuchiura JPX) Ishibashi Yoji (Hitachi JPX) Kuroda Michio (Hitachi JPX), Combustor for gas turbine.
이 특허를 인용한 특허 (7)
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Patel, Bhawan B.; Morenko, Oleg, Combustion system for a gas turbine engine and method of operating same.
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Kashihara, Hiroyuki; Yoshino, Yasushi; Matsumoto, Kiyoshi; Kimura, Takeshi; Kitajima, Junichi; Horikawa, Atsushi, Combustor.
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Kim, Kwanwoo; Johnson, Thomas Edward; Uhm, Jong Ho; Kraemer, Gilbert Otto, Combustor and combustor screech mitigation methods.
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Bruck,Gerald J.; Laster,Walter R., Concentric catalytic combustor.
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Saitoh, Toshihiko; Ohta, Masataka; Akamatsu, Shinji; Nose, Masakazu, Gas turbine combustor having multiple independently operable burners and staging method thereof.
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Andersson, Mats; Bonaldo, Alessio, Method to operate a combustor of a gas turbine.
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Homitz, Joseph; Sykes, David M.; O'Brien, Walter F.; Vandsburger, Uri; LePera, Steve, Premixing injector for gas turbine engines.
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