JP6035021B2 - 燃料の霧化を改善したデュアルオリフィス燃料ノズル - Google Patents
燃料の霧化を改善したデュアルオリフィス燃料ノズル Download PDFInfo
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- JP6035021B2 JP6035021B2 JP2011272888A JP2011272888A JP6035021B2 JP 6035021 B2 JP6035021 B2 JP 6035021B2 JP 2011272888 A JP2011272888 A JP 2011272888A JP 2011272888 A JP2011272888 A JP 2011272888A JP 6035021 B2 JP6035021 B2 JP 6035021B2
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- pilot
- annular
- fuel
- swirler
- fuel nozzle
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
- F23D11/383—Nozzles; Cleaning devices therefor with swirl means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
- F23D11/386—Nozzle cleaning
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/36—Supply of different fuels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00004—Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03042—Film cooled combustion chamber walls or domes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Description
57 パイロット燃料噴射装置先端部
58 一次パイロット燃料ノズル
59 二次パイロット燃料ノズル
98 一次出口
100 二次出口
114 外側パイロットスワラ
116 スワラスプリッタ
136 一次燃料スワラ
137 二次燃料スワラ
142 第1の下流端
143 第2の下流端
158 一次燃料供給通路
159 二次燃料供給通路
164 燃料噴射孔
180 環状の配列
182 螺旋回転スロット
190 噴射装置冷却流路
192 後部環状プレナム
206 環状の冷却流路入口
208 上流前端
210 環状の面取りした前縁
212 円錐形の面取り面
226 径方向外側の壁
230 内側に先細りする円錐形の壁部
232 円錐面
Claims (5)
- 燃料ノズルアセンブリ(12)であって、
パイロットミキサ(102)への環状のパイロット入口(54)の中心軸(120)を中心に事実上心合わせされたパイロット燃料噴射装置先端部(57)と、
前記パイロット燃料噴射装置先端部(57)の事実上同心の一次および二次パイロット燃料ノズル(58、59)と
を備え、
前記一次および二次パイロット燃料ノズル(58、59)が、円形の一次出口(98)および環状の二次出口(100)において拡開する円錐形オリフィスをそれぞれ有し、
前記円形の一次出口(98)が、前記環状の二次出口(100)の軸方向後方に下流に配置され、
前記燃料ノズルアセンブリ(12)は、さらに、
前記パイロット燃料噴射装置先端部(57)の径方向外側にそれに隣接して配置された、内側パイロットスワラ(112)と、
前記内側スワラ(112)の径方向外側に配置された、外側パイロットスワラ(114)と、
前記外側パイロットスワラ(114)の半径方向外側を囲い軸方向後方又は下流に延びる噴射装置冷却流路(190)と、
前記外側パイロットスワラ(114)と前記噴射装置冷却流路(190)への環状冷却流路入口(206)との間に設けられた環状壁部(208)と、
半径方向内側に面する円錐形面取り面(212)を有する、前記環状壁部(208)の環状面取り前縁(210)と、
前記二次パイロット燃料ノズル(59)の前記環状の二次出口(100)に燃料を流すように動作する、環状の二次燃料供給通路(159)と、
前記二次燃料供給通路(159)の環状の二次燃料スワラ(137)と
を含み、
前記二次燃料スワラ(137)が、螺旋回転スロット(182)の環状の配列(180)を含む、燃料ノズルアセンブリ(12)。 - 燃料ノズルアセンブリ(12)であって、
パイロットミキサ(102)への環状のパイロット入口(54)の中心軸(120)を中心に事実上心合わせされたパイロット燃料噴射装置先端部(57)と、
前記パイロット燃料噴射装置先端部(57)の事実上同心の一次および二次パイロット燃料ノズル(58、59)と
を備え、
前記一次および二次パイロット燃料ノズル(58、59)が、円形の一次出口(98)および環状の二次出口(100)において拡開する円錐形オリフィスをそれぞれ有し、
前記円形の一次出口(98)が、前記環状の二次出口(100)の軸方向後方に下流に配置され、
前記燃料ノズルアセンブリ(12)は、さらに、
前記パイロット燃料噴射装置先端部(57)の径方向外側にそれに隣接して配置された、内側パイロットスワラ(112)と、
前記内側スワラ(112)の径方向外側に配置された、外側パイロットスワラ(114)と、
前記外側パイロットスワラ(114)の半径方向外側を囲い軸方向後方又は下流に延びる噴射装置冷却流路(190)と、
前記外側パイロットスワラ(114)と前記噴射装置冷却流路(190)への環状冷却流路入口(206)との間に設けられた環状壁部(208)と、
半径方向内側に面する円錐形面取り面(212)を有する、前記環状壁部(208)の環状面取り前縁(210)と、
前記パイロットミキサを半径方向で囲う中央ボディ(103)を含むパイロットハウジング(99)と
を含み、
前記軸方向後方又は下流に延びる噴射装置冷却流路(190)が、前記パイロットハウジング(99)に且つ半径方向で前記中央ボディ(103)と燃料ノズル内側ケーシング(79)との間に配置され、
前記中央ボディの上流前縁が、該前縁の前記環状面取り前縁(210)を含んでいる、燃料ノズルアセンブリ(12)。 - 燃料ノズルアセンブリ(12)であって、
パイロットミキサ(102)への環状のパイロット入口(54)の中心軸(120)を中心に事実上心合わせされたパイロット燃料噴射装置先端部(57)と、
前記パイロット燃料噴射装置先端部(57)の事実上同心の一次および二次パイロット燃料ノズル(58、59)と
を備え、
前記一次および二次パイロット燃料ノズル(58、59)が、円形の一次出口(98)および環状の二次出口(100)において拡開する円錐形オリフィスをそれぞれ有し、
前記円形の一次出口(98)が、前記環状の二次出口(100)の軸方向後方に下流に配置され、
前記燃料ノズルアセンブリ(12)は、さらに、
前記パイロット燃料噴射装置先端部(57)の径方向外側にそれに隣接して配置された、内側パイロットスワラ(112)と、
前記内側スワラ(112)の径方向外側に配置された、外側パイロットスワラ(114)と、
前記外側パイロットスワラ(114)の半径方向外側を囲い軸方向後方又は下流に延びる噴射装置冷却流路(190)と、
前記外側パイロットスワラ(114)と前記噴射装置冷却流路(190)への環状冷却流路入口(206)との間に設けられた環状壁部(208)と、
半径方向内側に面する円錐形面取り面(212)を有する、前記環状壁部(208)の環状面取り前縁(210)と、
前記燃料ノズル内側ケーシングに少なくとも一部が支持され、前記第1及び第2パイロット燃料ノズルの半径方向外側に位置し径方向外側に開口した燃料噴射オリフィス(63)の円形または環状の配列を含む、主燃料ノズル(61)と
を含む、燃料ノズルアセンブリ(12)。 - 径方向において、前記内側パイロットスワラ(112)と外側パイロットスワラ(114)との間に配置された、スプリッタ(116)とをさらに備え、
前記内側パイロットスワラ(112)が、内側に先細りする環状の円錐形流路部(224)の上流に軸方向前方に、前記スプリッタ(116)と前記パイロット燃料噴射装置先端部(57)の径方向外側の壁(226)との間に、概して円筒形の内側パイロットスワラ流路部(222)を含む、請求項1乃至3のいずれか1項に記載の燃料ノズルアセンブリ(12)。 - 前記内側に先細りする円錐形流路部(224)の径方向内側の境界を定める前記径方向外側の壁(226)の内側に先細りする環状の円錐形壁部(230)と、
前記内側に先細りする円錐形壁部(230)によって画定される円錐面(232)と
をさらに備え、
前記円形の一次出口(98)および環状の二次出口(100)が、前記円錐面(232)に、または前記円錐面(232)の軸方向前方もしくは上流に配置される、請求項4に記載の燃料ノズルアセンブリ(12)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US12/971,597 | 2010-12-17 | ||
US12/971,597 US8726668B2 (en) | 2010-12-17 | 2010-12-17 | Fuel atomization dual orifice fuel nozzle |
Publications (3)
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JP2012132671A JP2012132671A (ja) | 2012-07-12 |
JP2012132671A5 JP2012132671A5 (ja) | 2015-01-29 |
JP6035021B2 true JP6035021B2 (ja) | 2016-11-30 |
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JP2011272888A Expired - Fee Related JP6035021B2 (ja) | 2010-12-17 | 2011-12-14 | 燃料の霧化を改善したデュアルオリフィス燃料ノズル |
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US (1) | US8726668B2 (ja) |
EP (1) | EP2466207A3 (ja) |
JP (1) | JP6035021B2 (ja) |
CA (1) | CA2760046A1 (ja) |
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JP4733195B2 (ja) * | 2009-04-27 | 2011-07-27 | 川崎重工業株式会社 | ガスタービンエンジンの燃料噴霧装置 |
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-
2010
- 2010-12-17 US US12/971,597 patent/US8726668B2/en active Active
-
2011
- 2011-12-01 CA CA2760046A patent/CA2760046A1/en not_active Abandoned
- 2011-12-02 EP EP11191658.1A patent/EP2466207A3/en not_active Withdrawn
- 2011-12-14 JP JP2011272888A patent/JP6035021B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
US8726668B2 (en) | 2014-05-20 |
EP2466207A2 (en) | 2012-06-20 |
EP2466207A3 (en) | 2017-11-15 |
US20120151930A1 (en) | 2012-06-21 |
CA2760046A1 (en) | 2012-06-17 |
JP2012132671A (ja) | 2012-07-12 |
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