JP6971596B2 - 後期噴射機構を有するトランジションダクトアセンブリ - Google Patents
後期噴射機構を有するトランジションダクトアセンブリ Download PDFInfo
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- JP6971596B2 JP6971596B2 JP2017044485A JP2017044485A JP6971596B2 JP 6971596 B2 JP6971596 B2 JP 6971596B2 JP 2017044485 A JP2017044485 A JP 2017044485A JP 2017044485 A JP2017044485 A JP 2017044485A JP 6971596 B2 JP6971596 B2 JP 6971596B2
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- 230000007704 transition Effects 0.000 title claims description 203
- 239000007924 injection Substances 0.000 title claims description 47
- 238000002347 injection Methods 0.000 title claims description 47
- 230000007246 mechanism Effects 0.000 title description 8
- 239000012530 fluid Substances 0.000 claims description 62
- 239000000446 fuel Substances 0.000 claims description 52
- 238000011144 upstream manufacturing Methods 0.000 claims description 21
- 238000004891 communication Methods 0.000 claims description 15
- 239000007789 gas Substances 0.000 description 43
- 238000002485 combustion reaction Methods 0.000 description 11
- 239000000567 combustion gas Substances 0.000 description 8
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 7
- 230000008901 benefit Effects 0.000 description 6
- 238000009826 distribution Methods 0.000 description 6
- 229910010293 ceramic material Inorganic materials 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 239000003978 infusion fluid Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000007667 floating Methods 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 1
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 239000011153 ceramic matrix composite Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010494 dissociation reaction Methods 0.000 description 1
- 230000005593 dissociations Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Images
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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/425—Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
-
- 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
- F23R2900/03041—Effusion 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
12 圧縮機セクション
14 燃焼器セクション
15 燃焼器
16 タービンセクション
18 シャフト
21 ケーシング
22 燃焼器ライナ
24 燃焼領域
26 トランジションピース
30 流れスリーブ
32 流路
34 インピンジメントスリーブ
36 流路
38 外部環状部
40 燃料ノズル
50 トランジションダクト
52 入口
54 出口
56 通路
57 内部
90 長手方向軸線
92 接線方向軸線
94 半径方向軸線
98 長手方向軸線
102 シュラウド
104 高温ガス経路
106 シュラウドブロック
112 バケット
114 ノズル
122 第1段バケットアセンブリ
123 第2段ノズルアセンブリ
124 第2段バケットアセンブリ
125 第3段ノズルアセンブリ
126 第3段バケットアセンブリ
130 第1トランジションダクト
132 第2トランジションダクト
134 接触面
142 正圧面
144 負圧面
146 後縁
150 流れスリーブ
152 環状通路
154 インピンジメント孔
162 入口
164 出口
166 通路
170 上流部
172 下流部
174 後方端部
176 先端部
180 下部支持リング
181 嵌合ボア孔
182 上部支持リング
183 嵌合ボア孔
184 チャネル
186 接触面
200 機械的ファスナ
202 内側フランジ
203 ボア孔
204 外側フランジ
205 ボア孔
210 後期噴射アセンブリ
212 入口管
214 入口
216 燃料ポート
218 燃料導管
220 燃料源
222 出口
224 第1導管
226 第2導管
228 マニホールド
229 分配導管
230 オス型機構
232 メス型機構
Claims (15)
- ターボ機械(10)であって、当該ターボ機械(10)が、
環状列状に配置され、第1トランジションダクト(130)及び第2トランジションダクト(132)を含む複数のトランジションダクト(50)であって、該複数のトランジションダクト(50)の各々が、入口(52)と出口(54)と通路(56)とを備えており、該通路(56)が、内部(57)を画成するとともに、前記入口(52)と前記出口(54)との間に延在して長手方向軸線、半径方向軸線及び接線方向軸線を画定しており、前記出口(54)の各々が、前記長手方向軸線及び前記接線方向軸線に沿って、前記入口(52)からオフセットしている、複数のトランジションダクト(50)と、
高温ガス経路(104)に沿って前記複数のトランジションダクト(50)の下流にある支持リングアセンブリ(180、182)と、
前記複数のトランジションダクト(50)のうち、少なくとも1つのトランジションダクト(50)を前記支持リングアセンブリ(180、182)に接続する複数の機械的ファスナ(200)と、
前記複数のトランジションダクト(50)のうち、少なくとも1つのトランジションダクト(50)の入口(52)の下流で前記内部(57)に噴射流体を流入させるための流体連通を提供する後期噴射アセンブリ(210)と
を備えており、前記後期噴射アセンブリ(210)の入口管(212)が、前記少なくとも1つのトランジションダクト(50)の出口(54)の下流に配置されている、ターボ機械(10)。 - 前記後期噴射アセンブリ(210)が、さらに、燃料を前記入口管(212)に流入させるための流体連通を提供する燃料ポート(216)を備える、請求項1に記載のターボ機械(10)。
- 前記後期噴射アセンブリ(210)が、さらに、前記燃料ポート(216)を介して前記入口管(212)と流体連通している燃料導管(218)を備える、請求項2に記載のターボ機械(10)。
- 前記入口管(212)の入口(214)が、作動流体を前記入口管(212)に流すように構成されている、請求項1乃至請求項3のいずれか1項に記載のターボ機械(10)。
- 前記少なくとも1つのトランジションダクト(50)の内面が、少なくとも部分的に後縁(146)を画成しており、前記後期噴射アセンブリ(210)の出口(222)が、前記後縁(146)に画成されている、請求項1乃至請求項4のいずれか1項に記載のターボ機械(10)。
- 前記少なくとも1つのトランジションダクト(50)の内面が、正圧面(142)及び負圧面(144)を少なくとも部分的に画成し、前記後期噴射アセンブリ(210)の出口(222)が、前記正圧面(142)又は前記負圧面(144)の一方に画成されている、請求項1乃至請求項4のいずれか1項に記載のターボ機械(10)。
- 前記後期噴射アセンブリ(210)の出口(222)が、前記少なくとも1つのトランジションダクト(50)の内部(57)に画成されたチョーク面の下流に画成されている、請求項1に記載のターボ機械(10)。
- 前記後期噴射アセンブリ(210)の入口管(212)が、前記支持リングアセンブリ(180、182)の半径方向外側に配置されている、請求項1乃至請求項4のいずれか1項に記載のターボ機械(10)。
- 前記後期噴射アセンブリ(210)が、前記入口管(212)から前記支持リングアセンブリ(180、182)を通って延在する第1導管(224)と、前記トランジションダクト(50)を通って延在する第2導管(226)とを備え、前記第1導管(224)と前記第2導管(226)とが流体連通している、請求項1乃至請求項8のいずれか1項に記載のターボ機械(10)。
- 前記第1導管(224)と前記第2導管(226)とが流体的に直接的に流体連通している、請求項9に記載のターボ機械(10)。
- マニホールド(228)が前記支持リングアセンブリ(180、182)内に画成されており、前記マニホールド(228)が、前記第1導管(224)と前記第2導管(226)との間に流体連通している、請求項9に記載のターボ機械(10)。
- 前記複数のトランジションダクト(50)の出口(54)の各々が、前記入口(52)から、前記半径方向軸線に沿ってさらにオフセットしている、請求項1乃至請求項11のいずれか1項に記載のターボ機械(10)。
- 当該ターボ機械(10)が、前記複数のトランジションダクト(50)と連通しているタービンセクション(16)をさらに備え、前記タービンセクション(16)が、前記支持リングアセンブリ(180、182)と、第1段バケットアセンブリ(122)とを備えており、前記第1段バケットアセンブリ(122)の上流に、ノズルが配置されていない、請求項1乃至請求項12のいずれか1項に記載のターボ機械(10)。
- 前記支持リングアセンブリ(180、182)が、前記少なくとも1つのトランジションダクト(50)と前記タービンセクション(16)との間のトランジション部を画成する、請求項13に記載のターボ機械(10)。
- ターボ機械(10)であって、当該ターボ機械(10)が、
環状列状に配置され、第1トランジションダクト(130)及び第2トランジションダクト(132)を含む複数のトランジションダクト(50)であって、該複数のトランジションダクト(50)の各々が、入口(52)と出口(54)と通路(56)とを備えており、該通路(56)が、内部(57)を画成するとともに、前記入口(52)と前記出口(54)との間に延在して長手方向軸線、半径方向軸線及び接線方向軸線を画定しており、前記出口(54)の各々が、前記長手方向軸線及び前記接線方向軸線に沿って、前記入口(52)からオフセットしている、複数のトランジションダクト(50)と、
高温ガス経路(104)に沿って前記複数のトランジションダクト(50)の下流にある支持リングアセンブリ(180、182)と、
前記複数のトランジションダクト(50)のうち、少なくとも1つのトランジションダクト(50)を前記支持リングアセンブリ(180、182)に接続する複数の機械的ファスナ(200)と、
前記複数のトランジションダクト(50)のうち、少なくとも1つのトランジションダクト(50)の内部(57)に噴射流体を流入させるための流体連通を提供する後期噴射アセンブリ(210)であって、後期噴射アセンブリ(210)の出口(54)が、前記少なくとも1つのトランジションダクト(50)の内部(57)に画成されたチョーク面の下流に画成されており、前記後期噴射アセンブリ(210)の入口管(212)が、前記少なくとも1つのトランジションダクト(50)の出口(54)の下流に配置されている、後期噴射アセンブリ(210)と
を備えるターボ機械(10)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/079,091 | 2016-03-24 | ||
US15/079,091 US10260752B2 (en) | 2016-03-24 | 2016-03-24 | Transition duct assembly with late injection features |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2017172952A JP2017172952A (ja) | 2017-09-28 |
JP6971596B2 true JP6971596B2 (ja) | 2021-11-24 |
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Application Number | Title | Priority Date | Filing Date |
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JP2017044485A Active JP6971596B2 (ja) | 2016-03-24 | 2017-03-09 | 後期噴射機構を有するトランジションダクトアセンブリ |
Country Status (4)
Country | Link |
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US (1) | US10260752B2 (ja) |
EP (1) | EP3246631B1 (ja) |
JP (1) | JP6971596B2 (ja) |
CN (1) | CN107288760B (ja) |
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