JP6824620B2 - 予混合パイロットノズル - Google Patents
予混合パイロットノズル Download PDFInfo
- Publication number
- JP6824620B2 JP6824620B2 JP2016080777A JP2016080777A JP6824620B2 JP 6824620 B2 JP6824620 B2 JP 6824620B2 JP 2016080777 A JP2016080777 A JP 2016080777A JP 2016080777 A JP2016080777 A JP 2016080777A JP 6824620 B2 JP6824620 B2 JP 6824620B2
- Authority
- JP
- Japan
- Prior art keywords
- fuel nozzle
- fuel
- nozzle assembly
- downstream
- pilot
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000000446 fuel Substances 0.000 claims description 105
- 238000011144 upstream manufacturing Methods 0.000 claims description 19
- 238000001816 cooling Methods 0.000 claims description 18
- 210000003793 centrosome Anatomy 0.000 claims description 15
- 239000012530 fluid Substances 0.000 claims description 14
- 239000002826 coolant Substances 0.000 claims description 11
- 230000000712 assembly Effects 0.000 claims description 10
- 238000000429 assembly Methods 0.000 claims description 10
- 238000004891 communication Methods 0.000 claims description 4
- UHZZMRAGKVHANO-UHFFFAOYSA-M chlormequat chloride Chemical compound [Cl-].C[N+](C)(C)CCCl UHZZMRAGKVHANO-UHFFFAOYSA-M 0.000 claims 1
- 230000000149 penetrating effect Effects 0.000 claims 1
- 239000007789 gas Substances 0.000 description 16
- 238000002485 combustion reaction Methods 0.000 description 14
- 239000000567 combustion gas Substances 0.000 description 8
- 239000000203 mixture Substances 0.000 description 6
- 238000006243 chemical reaction Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000012528 membrane Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000605 extraction Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 241000965606 Saccopharyngidae Species 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 230000003750 conditioning effect Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000010926 purge Methods 0.000 description 1
- 238000000746 purification Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 239000012720 thermal barrier coating Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Classifications
-
- 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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
-
- 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
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/78—Cooling burner parts
-
- 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
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
-
- 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
- F23R2900/03343—Pilot burners operating in premixed mode
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
Description
12 入口セクション
14 作動流体
16 圧縮機
18 圧縮された作動流体
20 燃料
22 燃料供給源
24 燃焼器
26 燃焼ガス
28 タービン
30 シャフト
32 発電機/モータ
34 排ガス
36 排気セクション
38 排気筒
40 ケーシング
42 高圧プレナム
44 エンドカバー
46 ヘッドエンド
48 燃料ノズルアセンブリ
50 抽出空気供給源
52 ライナー
54 燃焼室
56 高温ガス経路
58 流れ/衝突スリーブ
60 環状流路
100 燃料ノズルアセンブリ
102 中心体
104 中心線
106 パイロット燃料回路
108 パイロット空気回路
110 チューブ
112 上流側端部
114 下流側端部
116 外側スリーブ
118 環状通路
120 スワラーベーン
200 予混合パイロットノズル
202 下流側端部−予混合パイロットノズル
204 ステム
206 上流側端部−ステム
208 ベローズ
210 下流側端部−ステム
212 膨張カラー
214 中心線
216 スリーブ/ライナー
218 プレナム/間隙
220 先端/予混合部
222 予混合チューブ
224 内壁−先端部
226 外壁−先端部
228 予混合流路
230 入口
232 上流側壁/表面
234 出口
236 下流側表面/壁
238 燃料ポート
240 下流側端部−内壁
242 下流側端部−外壁
244 冷却チャネル
246 ブリッジ部
248 開口
250 カートリッジ
252 冷却通路
254 下流側端部−カートリッジ
256 パイロット火炎
258 基部
260 冷却媒体
Claims (10)
- 燃料ノズルアセンブリ(100)であって、当該燃料ノズルアセンブリ(100)が、
当該燃料ノズルアセンブリ(100)の中心線に沿って軸方向に延びる中心体(102)であって、該中心体(102)内にパイロット燃料回路(106)とパイロット空気回路(108)とが画定される、中心体(102)と、
前記中心体(102)と同軸に配置された外側スリーブ(116)であって、前記中心体(102)と該外側スリーブ(116)とがそれらの間に環状通路(118)を画定する、外側スリーブ(116)と、
前記環状通路(118)内で前記中心体(102)と前記外側スリーブ(116)との間に延びる複数のスワラーベーン(120)と、
前記中心体(102)内で軸方向に延びる予混合パイロットノズル(200)であって、該予混合パイロットノズル(200)が先端部(220)を有し、該先端部(220)が該先端部(220)の内壁(224)の下流側端部(240)と該先端部(220)の外壁(226)の下流側端部(242)との間で延びる下流側表面(236)を備え、前記内壁(224)の下流側端部(240)が前記外壁(226)の下流側端部(242)よりも軸方向上流側で終端し、前記下流側表面(236)の少なくとも一部が曲線を成すとともに、前記下流側表面(236)の少なくとも一部が、前記内壁(224)の下流側端部(240)と前記外壁(226)の下流側端部(242)との間で凹状に延びる、予混合パイロットノズル(200)と
を備えており、
前記先端部(220)が、該先端部(220)の周囲に環状に配置される複数の軸方向に延びる予混合チューブ(222)を更に備え、該予混合チューブ(222)の各々が、前記下流側表面(236)から軸方向にオフセットされる出口(234)を含み、前記予混合チューブ(222)の各々が、前記下流側表面(236)よりも下流側で終端して前記先端部(220)を貫通する予混合流路(228)を画定し、隣接する予混合チューブ(222)が、それらの間に前記下流側表面(236)の凹部に沿って冷却流チャネル(244)を画定する、燃料ノズルアセンブリ(100)。 - 前記下流側表面(236)が前記予混合チューブ(222)の各々の周囲で少なくとも部分的に湾曲する、請求項1に記載の燃料ノズルアセンブリ(100)。
- 前記先端部(220)が、前記燃料ノズルアセンブリ(100)の前記中心体(102)内に前記パイロット燃料回路(106)を少なくとも部分的に画定し、前記予混合チューブ(222)の各々が前記パイロット燃料回路(106)と流体連通する、請求項1又は請求項2に記載の燃料ノズルアセンブリ(100)。
- 前記予混合チューブ(222)の各々が、前記先端部(220)の外壁(226)に接続されるブリッジ部(246)を含む、請求項1乃至請求項3のいずれか1項に記載の燃料ノズルアセンブリ(100)。
- 前記予混合チューブ(222)のうちの少なくとも1つが、前記外壁(226)の下流側端部(242)に隣接して終端する、請求項1乃至請求項4のいずれか1項に記載の燃料ノズルアセンブリ(100)。
- 前記予混合チューブ(222)のうちの少なくとも1つが、前記外壁(226)の下流側端部(242)よりも下流側で終端する、請求項1乃至請求項4のいずれか1項に記載の燃料ノズルアセンブリ(100)。
- 当該燃料ノズルアセンブリ(100)が、前記中心体(102)及び前記予混合パイロットノズル(200)内で軸方向に延びるカートリッジ(250)をさらに備えており、該カートリッジ(250)が、前記予混合パイロットノズル(200)の先端部(220)の下流側表面(236)に冷却媒体(260)を供給するように構成されている、請求項1乃至請求項6のいずれか1項に記載の燃料ノズルアセンブリ(100)。
- 前記カートリッジ(250)が、該カートリッジ(250)の下流側端部(254)又はその近傍に画定される1つ以上の冷却穴(252)を含む、請求項7に記載の燃料ノズルアセンブリ(100)。
- 前記カートリッジ(250)が、前記先端部(220)の内壁(224)内に画定されたカートリッジ開口(248)内に配置される、請求項7又は請求項8に記載の燃料ノズルアセンブリ(100)。
- 燃焼器(24)であって、当該燃焼器(24)が、
エンドカバー(44)と、
中心燃料ノズルと、
前記中心燃料ノズルの周囲に環状に配置される複数の燃料ノズルアセンブリ(100)と
を備えており、前記複数の燃料ノズルアセンブリ(100)の各々が、請求項1乃至請求項9のいずれか1項に記載の燃料ノズルアセンブリであり、前記複数の燃料ノズルアセンブリの各燃料ノズルアセンブリ及び前記中心燃料ノズルが前記エンドカバーに接続固定されている、燃焼器(24)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/691,864 US9803867B2 (en) | 2015-04-21 | 2015-04-21 | Premix pilot nozzle |
US14/691,864 | 2015-04-21 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2016205809A JP2016205809A (ja) | 2016-12-08 |
JP6824620B2 true JP6824620B2 (ja) | 2021-02-03 |
Family
ID=55755473
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2016080777A Active JP6824620B2 (ja) | 2015-04-21 | 2016-04-14 | 予混合パイロットノズル |
Country Status (4)
Country | Link |
---|---|
US (1) | US9803867B2 (ja) |
EP (1) | EP3086043B1 (ja) |
JP (1) | JP6824620B2 (ja) |
CN (1) | CN106066048B (ja) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
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US9714767B2 (en) | 2014-11-26 | 2017-07-25 | General Electric Company | Premix fuel nozzle assembly |
US9982892B2 (en) | 2015-04-16 | 2018-05-29 | General Electric Company | Fuel nozzle assembly including a pilot nozzle |
US10443854B2 (en) * | 2016-06-21 | 2019-10-15 | General Electric Company | Pilot premix nozzle and fuel nozzle assembly |
CN107702147B (zh) * | 2017-09-05 | 2020-07-14 | 中国联合重型燃气轮机技术有限公司 | 燃气轮机的燃料喷嘴 |
CN107741030B (zh) * | 2017-09-18 | 2019-09-20 | 北京航空航天大学 | 一种具有冷却结构的叶片喷射低排放燃烧室头部 |
US11371706B2 (en) | 2017-12-18 | 2022-06-28 | General Electric Company | Premixed pilot nozzle for gas turbine combustor |
US11619388B2 (en) | 2017-12-21 | 2023-04-04 | Collins Engine Nozzles, Inc. | Dual fuel gas turbine engine pilot nozzles |
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-
2015
- 2015-04-21 US US14/691,864 patent/US9803867B2/en active Active
-
2016
- 2016-04-14 JP JP2016080777A patent/JP6824620B2/ja active Active
- 2016-04-15 EP EP16165555.0A patent/EP3086043B1/en active Active
- 2016-04-21 CN CN201610249613.8A patent/CN106066048B/zh active Active
Also Published As
Publication number | Publication date |
---|---|
US9803867B2 (en) | 2017-10-31 |
US20160313006A1 (en) | 2016-10-27 |
EP3086043A1 (en) | 2016-10-26 |
EP3086043B1 (en) | 2018-07-18 |
CN106066048A (zh) | 2016-11-02 |
JP2016205809A (ja) | 2016-12-08 |
CN106066048B (zh) | 2020-04-10 |
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