JP2018520289A - 機械駆動用途における超低NOx排出ガスタービンエンジン - Google Patents
機械駆動用途における超低NOx排出ガスタービンエンジン Download PDFInfo
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- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/46—Emergency fuel control
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- 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/005—Adaptations for refrigeration plants
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- 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/12—Combinations with mechanical gearing
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
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- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
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- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
- F02C9/50—Control of fuel supply conjointly with another control of the plant with control of working fluid flow
- F02C9/54—Control of fuel supply conjointly with another control of the plant with control of working fluid flow by throttling the working fluid, by adjusting vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N5/00—Systems for controlling combustion
- F23N5/24—Preventing development of abnormal or undesired conditions, i.e. safety arrangements
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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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
- F23R3/286—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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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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
- F23R3/42—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
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/08—Purpose of the control system to produce clean exhaust gases
- F05D2270/082—Purpose of the control system to produce clean exhaust gases with as little NOx as possible
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/09—Purpose of the control system to cope with emergencies
- F05D2270/091—Purpose of the control system to cope with emergencies in particular sudden load loss
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/303—Temperature
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/304—Spool rotational speed
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2231/00—Fail safe
- F23N2231/06—Fail safe for flame failures
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Thermal Sciences (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Control Of Turbines (AREA)
- Supercharger (AREA)
Abstract
【選択図】図1
Description
3 ガス圧縮機、(被駆動)ターボ機械
4 電機
5 プラント
6 配電グリッド
7 熱交換器
8 可変周波数ドライバ
9 凝縮器
11 膨張弁
13 ループ
15 管
17 ギアボックス
17A 入口
17B 出口
21 空気圧縮セクション
23 燃焼器セクション
25 タービンセクション
27 空気圧縮機
27R 圧縮機ロータ
28 ガスタービン軸
31 燃焼器
33 タービン
33R タービンロータ
35 (GT)排気筒
50 (キャップ)中央本体
51 燃焼器ハウジング
52 エンドプレート
53 (燃焼)ライナ、火炎管
53F 前端
55 トランジションピース(トランジションダクト)
55A 後端
55F 前端
57 環状流路
59 混合孔
61 希釈孔
63 希釈孔
65 一次燃料ノズル
69 ベンチュリスロート領域
70 上流燃焼室、一次ゾーン
71 二次燃料ノズル
72 二次ノズルペグ
73 二次ノズル案内管
73A (二次ノズル)案内先端
74 下流燃焼室、二次ゾーン
76 予混合反応ゾーン
78 燃料移送ライン
81 温度センサ
82 スワーラ
83 ガスタービン制御装置
85 速度センサ
87 トルクセンサ
89 工程制御装置
100 多段遠心圧縮機
101 外側ケーシング
101B バレル
101C 端部
103 ロータ
105 軸
107 インペラ
109 圧縮機入口
111 圧縮機出口、ガス出口
113 軸受
115 軸受
117 入口チャネル
119 戻りチャネル
121 ダイヤフラム
123 渦巻き部
A−A 軸線
B−B 軸線
F 燃料
Claims (17)
- 機械駆動構成におけるガスタービン駆動システムであって、被駆動ターボ機械(3)に駆動可能に接続されたガスタービンエンジン(1)であって、乾式低NOx排出燃焼器(31)を含むガスタービンエンジン(1)と、ガスタービン制御装置(83)とを備え、前記ガスタービン制御装置(83)が、前記被駆動ターボ機械(3)に関する過渡事象が起こった場合に、前記燃焼器(31)の希薄吹消えが防止されるように、前記ターボ機械(3)の少なくとも1つの制御パラメータにより、燃焼温度を調節するように配置され、かつ構成されており、前記過渡事象が、前記被駆動ターボ機械(3)の回転速度の変化である、ガスタービン駆動システム。
- 前記過渡事象が、
前記被駆動ターボ機械(3)の負荷の変化と、前記ガスタービン(33)の排出における温度の変化と、燃料ストローク基準と
のうちの1つをさらに含む、請求項1に記載のガスタービン駆動システム。 - 前記過渡事象が、前記負荷が10%以上変動した場合に起きる、請求項1又は2に記載のガスタービン駆動システム。
- 前記過渡事象が、前記負荷が1分当たり8%又はそれより高速に変動する場合に起きる、請求項1又は2に記載のガスタービン駆動システム。
- 前記過渡事象が、負荷変動が前記被駆動ターボ機械(3)において1%以上の速度の変動を引き起こす場合に起きる、請求項1乃至4のいずれか1項に記載のガスタービン駆動システム。
- 前記超低乾式低NOx排出燃焼器(31)が、前記ガスタービン(33)の軸線(A−A、B−B)の周囲に環状に並んで配置された複数の燃焼器(31)を備え、前記燃焼器(31)のそれぞれが、
接合領域で互いに流体連通している上流燃焼室(70)及び下流燃焼室(74)と、
前記上流燃焼室(70)に燃料を供給するために配置された複数の一次燃料ノズル(65)であって、前記上流燃焼室(70)が、前記上流燃焼室(70)における空気燃料混合気の均質性を向上させるための混合孔構成部(59)を備える一次燃料ノズル(65)と、
前記下流燃焼室(74)に燃料を供給するために配置された二次燃料ノズル(71)と、
前記下流燃焼室(74)を、前記ガスタービンエンジン(1)のタービンセクション(25)の入口に流体接続させるトランジションピース(55)とを備える、請求項1乃至5のいずれか1項に記載のガスタービン駆動システム。 - 前記接合領域が、ベンチュリスロート(69)を備える、請求項6に記載のガスタービン駆動システム。
- 前記二次燃料ノズル(71)が細長い本体を備え、前記細長い本体に沿って二次ノズル案内管(73)が延び、前記二次ノズル案内管(73)が案内先端(73A)で止まり、二次ノズルペグ(72)が、前記細長い本体に沿った中間位置に配置されており、燃料ガスが、前記二次ノズル案内管(73)及び前記二次ノズルペグ(72)に別々に送られる、請求項6又は7に記載のガスタービン駆動システム。
- 前記二次燃料ノズル(71)が、前記上流燃焼室(70)内に延びる中央本体(50)に配置されている、請求項8に記載のガスタービン駆動システム。
- 前記二次燃料ノズル(71)の前記細長い本体が、前記中央本体(50)と実質的に同軸に延び、前記二次ノズルペグ(72)が、前記二次燃料ノズル(71)を囲む前記中央本体(50)の予混合反応ゾーン(76)に燃料ガスを送るように構成され、かつ配置されており、前記予混合反応ゾーン(76)が、前記中央本体(50)の出口端部と流体連通しており、前記出口端部から、前記予混合反応ゾーン(76)で生成された燃料/空気混合気が、前記下流燃焼室(74)内に流れる、請求項9に記載のガスタービン駆動システム。
- スワーラ構成部(83)が、前記予混合反応ゾーン(76)と前記中央本体(50)の前記出口との間に配置されている、請求項10に記載のガスタービン駆動システム。
- 前記上流燃焼室(70)が、通常動作中、前記一次燃料ノズル(65)によって供給される前記燃料が、前記上流燃焼室(70)に供給された空気と予め十分に混合され、かつ前記空気/燃料混合気が、NOx及びCOの排出を抑えた燃焼のために前記下流燃焼室(74)に送られるように構成されている、請求項7乃至11のいずれか1項に記載のガスタービン駆動システム。
- 前記ガスタービン制御装置(83)が、前記被駆動ターボ機械(3)に関する前記過渡事象が起こった場合、事象ベースのアクションを引き起こすように構成され、かつ配置されている、請求項1乃至12のいずれか1項に記載のガスタービン駆動システム。
- 前記事象ベースのアクションが、前記燃料弁のより高速な制御、前記燃焼器(31)における前記一次燃料ノズル(65)への燃料流量と前記二次燃料ノズル(71)への燃料流量との比の変更、及び前記ガスタービンエンジン(1)の可変IGVの操作からなる群より選択される、請求項13に記載のガスタービン駆動システム。
- 被駆動ターボ機械(3)に駆動可能に接続されたガスタービンエンジン(1)の燃焼を制御する方法であって、前記ガスタービンエンジン(1)が、乾式低NOx排出燃焼器(31)及びガスタービン制御装置(83)を含み、前記被駆動ターボ機械(3)に関する過渡事象が起こった場合に、前記燃焼器(31)の希薄吹消えが防止されるように、前記ターボ機械(3)の少なくとも1つの制御パラメータにより、前記燃焼温度を調節するステップであって、前記過渡事象が、前記被駆動ターボ機械(3)の回転速度の変化であるステップを含む方法。
- 前記被駆動ターボ機械(3)に関する前記過渡事象が起こった場合、事象ベースのアクションを引き起こすステップをさらに含む、請求項12に記載の方法。
- 前記事象ベースのアクションが、前記燃料弁のより高速な制御、前記燃焼器(31)における前記一次燃料ノズル(65)への燃料流量と前記二次燃料ノズル(71)への燃料流量との比の変更、及び前記ガスタービンエンジン(1)の可変IGVの操作からなる群より選択される、請求項16に記載の方法。
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Application Number | Priority Date | Filing Date | Title |
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ITFI20150128 | 2015-04-30 | ||
ITFI2015A000128 | 2015-04-30 | ||
PCT/EP2016/059563 WO2016174175A1 (en) | 2015-04-30 | 2016-04-28 | Ultra-low nox emission gas turbine engine in mechanical drive applications |
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US (1) | US20180283287A1 (ja) |
EP (1) | EP3289186A1 (ja) |
JP (1) | JP2018520289A (ja) |
AU (1) | AU2016254323B2 (ja) |
BR (1) | BR112017023073A2 (ja) |
WO (1) | WO2016174175A1 (ja) |
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EP3530913A1 (en) | 2018-02-23 | 2019-08-28 | Siemens Aktiengesellschaft | Controller and method |
US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
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US6912856B2 (en) | 2003-06-23 | 2005-07-05 | General Electric Company | Method and system for controlling gas turbine by adjusting target exhaust temperature |
US7854121B2 (en) | 2005-12-12 | 2010-12-21 | General Electric Company | Independent pilot fuel control in secondary fuel nozzle |
US20100018211A1 (en) | 2008-07-23 | 2010-01-28 | General Electric Company | Gas turbine transition piece having dilution holes |
US8020385B2 (en) | 2008-07-28 | 2011-09-20 | General Electric Company | Centerbody cap for a turbomachine combustor and method |
US8156743B2 (en) | 2006-05-04 | 2012-04-17 | General Electric Company | Method and arrangement for expanding a primary and secondary flame in a combustor |
US8474268B2 (en) * | 2007-08-16 | 2013-07-02 | General Electric Company | Method of mitigating undesired gas turbine transient response using event based actions |
US7997083B2 (en) * | 2007-08-28 | 2011-08-16 | General Electric Company | Method and system for detection of gas turbine combustion blowouts utilizing fuel normalized power response |
US20100162711A1 (en) | 2008-12-30 | 2010-07-01 | General Electric Compnay | Dln dual fuel primary nozzle |
US20100205970A1 (en) | 2009-02-19 | 2010-08-19 | General Electric Company | Systems, Methods, and Apparatus Providing a Secondary Fuel Nozzle Assembly |
IT1396515B1 (it) | 2009-11-27 | 2012-12-14 | Nuovo Pignone Spa | Soglia basata su temperatura di scarico per metodo di controllo e turbina |
IT1396517B1 (it) | 2009-11-27 | 2012-12-14 | Nuovo Pignone Spa | Metodo di controllo di modo basato su temperatura di scarico per turbina a gas e turbina a gas |
IT1396514B1 (it) | 2009-11-27 | 2012-12-14 | Nuovo Pignone Spa | Metodo di controllo di turbina basato su rapporto tra temperatura di scarico e pressione di turbina |
IT1396516B1 (it) | 2009-11-27 | 2012-12-14 | Nuovo Pignone Spa | Metodo di controllo di modo basato su temperatura di scarico per turbina a gas e turbina a gas |
US20110131998A1 (en) | 2009-12-08 | 2011-06-09 | Vaibhav Nadkarni | Fuel injection in secondary fuel nozzle |
US20110247340A1 (en) | 2010-04-13 | 2011-10-13 | Predrag Popovic | Apparatus and method for minimizing and/or eliminating dilution air leakage in a combustion liner assembly |
US9927818B2 (en) * | 2010-05-24 | 2018-03-27 | Ansaldo Energia Ip Uk Limited | Stabilizing a gas turbine engine via incremental tuning during transients |
US8464537B2 (en) * | 2010-10-21 | 2013-06-18 | General Electric Company | Fuel nozzle for combustor |
ITFI20120245A1 (it) * | 2012-11-08 | 2014-05-09 | Nuovo Pignone Srl | "gas turbine in mechanical drive applications and operating methods" |
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2016
- 2016-04-28 AU AU2016254323A patent/AU2016254323B2/en not_active Ceased
- 2016-04-28 BR BR112017023073A patent/BR112017023073A2/pt not_active Application Discontinuation
- 2016-04-28 JP JP2017556130A patent/JP2018520289A/ja active Pending
- 2016-04-28 EP EP16720802.4A patent/EP3289186A1/en not_active Withdrawn
- 2016-04-28 WO PCT/EP2016/059563 patent/WO2016174175A1/en active Application Filing
- 2016-04-28 US US15/570,599 patent/US20180283287A1/en not_active Abandoned
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AU2016254323B2 (en) | 2019-11-28 |
US20180283287A1 (en) | 2018-10-04 |
EP3289186A1 (en) | 2018-03-07 |
AU2016254323A1 (en) | 2017-11-09 |
BR112017023073A2 (pt) | 2018-07-10 |
WO2016174175A1 (en) | 2016-11-03 |
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