JP6329360B2 - ガス・タービン・エンジン・システム及び関連する方法 - Google Patents
ガス・タービン・エンジン・システム及び関連する方法 Download PDFInfo
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- JP6329360B2 JP6329360B2 JP2013239475A JP2013239475A JP6329360B2 JP 6329360 B2 JP6329360 B2 JP 6329360B2 JP 2013239475 A JP2013239475 A JP 2013239475A JP 2013239475 A JP2013239475 A JP 2013239475A JP 6329360 B2 JP6329360 B2 JP 6329360B2
- Authority
- JP
- Japan
- Prior art keywords
- combustor
- nozzle
- section
- mixture
- injector
- 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.)
- Expired - Fee Related
Links
- 238000000034 method Methods 0.000 title claims description 13
- 239000000446 fuel Substances 0.000 claims description 46
- 239000000203 mixture Substances 0.000 claims description 45
- 230000007704 transition Effects 0.000 claims description 44
- 238000002485 combustion reaction Methods 0.000 claims description 40
- 239000000567 combustion gas Substances 0.000 claims description 29
- 239000007789 gas Substances 0.000 claims description 27
- 238000001816 cooling Methods 0.000 claims description 13
- 238000002347 injection Methods 0.000 claims description 13
- 239000007924 injection Substances 0.000 claims description 13
- 230000002708 enhancing effect Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 9
- 239000003085 diluting agent Substances 0.000 description 9
- 238000006243 chemical reaction Methods 0.000 description 6
- 230000002093 peripheral effect Effects 0.000 description 6
- 229930195733 hydrocarbon Natural products 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 238000010517 secondary reaction Methods 0.000 description 3
- 239000004215 Carbon black (E152) Substances 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 2
- 229910002091 carbon monoxide Inorganic materials 0.000 description 2
- 238000005755 formation reaction Methods 0.000 description 2
- 150000002430 hydrocarbons Chemical class 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 1
- 238000003915 air pollution Methods 0.000 description 1
- 238000003491 array Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 125000001183 hydrocarbyl group Chemical group 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 239000000376 reactant Substances 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 239000007858 starting material Substances 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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
-
- 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
- F23R3/42—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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Description
12:吸込部
14:圧縮機
16:燃焼器
18:主燃焼器区画
19:第一の燃焼ガス
20:副燃焼器区画
22:タービン
24:排気部
26:負荷
28:尾筒ノズル
30:ケーシング
32:端部カバー
34:始動用燃料ノズル
36:予備混合燃料ノズル
38:キャップ・アセンブリ
40:流れスリーブ
42:燃焼ライナ
44:衝突スリーブ
46:円環プレナム
48:動翼
50:ディフューザ
52:スワーラ
54:スポーク
56:一次反応帯
58:噴射器
60:二次反応帯
61:間隙
62:副燃焼器区画の周縁
63:第二の燃焼ガス
64:動翼
66:燃焼炎が生成される領域に対応する点
68:燃焼炎
70:オフセット方向
72:中心軸
74:熱スポット
75:側壁
76:出口
77:周縁面
78:一体型ベーン
80:尾筒区画
82:燃焼器
84:噴射器
86:尾筒ノズル
88:一体型ベーン
90:尾筒区画
91:第一の燃焼ガス
92:熱スポット
93:第二の燃焼ガス
94:出口
95:側壁
96:主燃焼器区画
97:中心軸
98:副燃焼器区画
99:周縁面
Claims (11)
- ガス・タービン・エンジン・システムであって、
圧縮機と、
該圧縮機に結合されて該圧縮機の下流に配設された燃焼器であって、
主燃焼器区画と、
該主燃焼器区画に結合されて該主燃焼器区画の下流に配設された副燃焼器区画と、
該副燃焼器区画に結合されて該副燃焼器区画の下流に配設された尾筒ノズルと、
前記副燃焼器区画に結合されて前記副燃焼器区画に混合気を噴射する噴射器と
を含んでいる燃焼器と、
該燃焼器に結合されて前記尾筒ノズルの下流に配設されたタービンであって、前記尾筒ノズルは当該タービンに対して実質的に接線方向に配向している、タービンと、
を備え、前記噴射器が、前記混合気を前記副燃焼器区画に非一様に噴射するための複数の噴射孔を含んでいて、幾つかの噴射孔が、前記副燃焼器区画のある区域に他の区域に比較して少ない又は多い何れかの燃料を分配するように構成されている、ガス・タービン・エンジン・システム。 - 前記噴射器は翼型形状である、請求項1に記載のガス・タービン・エンジン・システム。
- 前記噴射器は、前記第二段燃焼区画の範囲内に前記混合気の分配を強化するための彎曲部を有している、請求項1又は請求項2に記載のガス・タービン・エンジン・システム。
- 前記尾筒ノズルは、燃焼炎が前記副燃焼区画において生成される位置に対応する点から前記タービンへ向けて延在している、請求項1乃至請求項3のいずれか1項に記載のガス・タービン・エンジン・システム。
- 前記尾筒ノズルが複数の尾筒区画として形成されるように、前記尾筒ノズルの内部に配設された一体型ベーンをさらに含んでいる、請求項1乃至請求項4のいずれか1項に記載のガス・タービン・エンジン・システム。
- 前記一体型ベーンを用いて冷却空気を前記圧縮機から前記尾筒ノズルの内部に供給する、請求項5に記載のガス・タービン・エンジン・システム。
- 前記尾筒ノズルは、前記タービンに対して実質的に接線方向での熱した燃焼ガスの流れの転回を提供する、請求項1乃至請求項6のいずれか1項に記載のガス・タービン・システム。
- 主燃焼器区画において第一の混合気を燃焼させて第一の燃焼ガスを生成するステップと、
前記第一の燃焼ガスを主燃焼器区画から副燃焼器区画に供給するステップと、
当該第二の混合気を燃焼させて第二の燃焼ガスを生成するように、前記副燃焼器区画に結合されている噴射器を介して第二の混合気を噴射するステップと、
尾筒ノズルを介してタービンに対して実質的に接線方向に前記第一及び第二の燃焼ガスを噴射するステップと
を含む方法であって、前記噴射器が、前記混合気を前記副燃焼器区画に非一様に噴射するための複数の噴射孔を含んでいて、幾つかの噴射孔が、前記副燃焼器区画のある区域に他の区域に比較して少ない又は多い何れかの燃料を分配するように構成されている、方法。 - 前記第一の混合気はリーンな混合気を含んでいる、請求項8に記載の方法。
- 前記第二の混合気はリッチな希釈混合気を含んでいる、請求項8又は請求項9に記載の方法。
- 冷却空気を圧縮機から前記尾筒ノズルに配設された一体型ベーンを介して供給するステップをさらに含んでいる、請求項8乃至請求項10のいずれか1項に記載の方法。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/691,017 US9551492B2 (en) | 2012-11-30 | 2012-11-30 | Gas turbine engine system and an associated method thereof |
US13/691,017 | 2012-11-30 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2014109433A JP2014109433A (ja) | 2014-06-12 |
JP6329360B2 true JP6329360B2 (ja) | 2018-05-23 |
Family
ID=49759012
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2013239475A Expired - Fee Related JP6329360B2 (ja) | 2012-11-30 | 2013-11-20 | ガス・タービン・エンジン・システム及び関連する方法 |
Country Status (4)
Country | Link |
---|---|
US (1) | US9551492B2 (ja) |
EP (1) | EP2738355B1 (ja) |
JP (1) | JP6329360B2 (ja) |
CN (1) | CN103850796B (ja) |
Families Citing this family (15)
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US20140238034A1 (en) * | 2011-11-17 | 2014-08-28 | General Electric Company | Turbomachine combustor assembly and method of operating a turbomachine |
US10139111B2 (en) * | 2014-03-28 | 2018-11-27 | Siemens Energy, Inc. | Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine |
JP6584634B2 (ja) * | 2015-07-24 | 2019-10-02 | シーメンス アクチエンゲゼルシヤフトSiemens Aktiengesellschaft | 燃焼滞留時間が短縮された遅延希薄噴射を有するガスタービントランジションダクト |
US10260752B2 (en) * | 2016-03-24 | 2019-04-16 | General Electric Company | Transition duct assembly with late injection features |
US10605459B2 (en) * | 2016-03-25 | 2020-03-31 | General Electric Company | Integrated combustor nozzle for a segmented annular combustion system |
US11067279B2 (en) | 2016-05-12 | 2021-07-20 | Siemens Energy Global GmbH & Co. KG | Method of selective combustor control for reduced emissions |
US10337738B2 (en) * | 2016-06-22 | 2019-07-02 | General Electric Company | Combustor assembly for a turbine engine |
US20170370589A1 (en) * | 2016-06-22 | 2017-12-28 | General Electric Company | Multi-tube late lean injector |
US11022313B2 (en) | 2016-06-22 | 2021-06-01 | General Electric Company | Combustor assembly for a turbine engine |
EP3479025B1 (en) * | 2016-08-03 | 2021-11-03 | Siemens Energy Global GmbH & Co. KG | Injector assemblies configured to form a shielding flow of air injected into a combustion stage in a gas turbine engine |
US10894236B2 (en) | 2016-11-30 | 2021-01-19 | Dresser-Rand Company | Radial annular component and helical axial components coupled to and extending from the radial component |
US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
US11255545B1 (en) | 2020-10-26 | 2022-02-22 | General Electric Company | Integrated combustion nozzle having a unified head end |
US11846426B2 (en) | 2021-06-24 | 2023-12-19 | General Electric Company | Gas turbine combustor having secondary fuel nozzles with plural passages for injecting a diluent and a fuel |
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2012
- 2012-11-30 US US13/691,017 patent/US9551492B2/en active Active
-
2013
- 2013-11-20 JP JP2013239475A patent/JP6329360B2/ja not_active Expired - Fee Related
- 2013-11-29 EP EP13194988.5A patent/EP2738355B1/en active Active
- 2013-11-29 CN CN201310628375.8A patent/CN103850796B/zh not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
US9551492B2 (en) | 2017-01-24 |
EP2738355B1 (en) | 2016-09-14 |
JP2014109433A (ja) | 2014-06-12 |
EP2738355A1 (en) | 2014-06-04 |
US20140352321A1 (en) | 2014-12-04 |
CN103850796B (zh) | 2018-03-27 |
CN103850796A (zh) | 2014-06-11 |
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Free format text: JAPANESE INTERMEDIATE CODE: R250 |
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R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
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