EP2179222B1 - Brûleur pour une chambre de combustion d'un turbogroupe - Google Patents
Brûleur pour une chambre de combustion d'un turbogroupe Download PDFInfo
- Publication number
- EP2179222B1 EP2179222B1 EP08775142.6A EP08775142A EP2179222B1 EP 2179222 B1 EP2179222 B1 EP 2179222B1 EP 08775142 A EP08775142 A EP 08775142A EP 2179222 B1 EP2179222 B1 EP 2179222B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- lance
- interior
- outlet opening
- passage
- 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
- 238000002485 combustion reaction Methods 0.000 title claims description 32
- 239000000446 fuel Substances 0.000 claims description 48
- 239000007788 liquid Substances 0.000 claims description 22
- 238000001816 cooling Methods 0.000 claims description 11
- 238000002347 injection Methods 0.000 claims description 11
- 239000007924 injection Substances 0.000 claims description 11
- 239000002737 fuel gas Substances 0.000 description 8
- 238000002156 mixing Methods 0.000 description 8
- 239000007789 gas Substances 0.000 description 5
- 230000007704 transition Effects 0.000 description 4
- 206010016754 Flashback Diseases 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 241001156002 Anthonomus pomorum Species 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000007921 spray Substances 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
- F23R3/286—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
- F23R3/343—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
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07021—Details of lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
- Spray-Type Burners (AREA)
- Gas Burners (AREA)
Claims (9)
- Brûleur pour une chambre de combustion d'un turbogroupe, comprenant au moins un générateur de tourbillon (2), un mélangeur (3) et un dispositif d'injection de carburant sous la forme d'une lance (4), qui introduit de l'air et des carburants à l'intérieur (5) d'un brûleur en vue d'une réaction de combustion se produisant dans une chambre de combustion (10), dans lequel le générateur de tourbillon (2), qui entoure côté admission l'intérieur de brûleur (5), présente au moins une admission d'air (6) tangentielle par rapport à un axe central longitudinal (7), et le mélangeur (3), qui entoure côté sortie l'intérieur de brûleur (5), présente une ouverture de sortie ouverte vers la chambre de combustion (10), et la lance (4) disposée coaxialement à l'axe central longitudinal (7) s'étend à partir d'une tête de brûleur (14) dans l'intérieur de brûleur (5) pour l'introduction de carburant pilote pendant un fonctionnement pilote du brûleur (1), caractérisé en ce que la lance (4) s'étend, au moins pendant le fonctionnement pilote du brûleur (1), dans l'intérieur de brûleur (5) à un point tel qu'un front de flamme (16) de la réaction de combustion se produisant dans la chambre de combustion (10) s'étende au moins en partie jusque dans une partie d'extrémité de l'intérieur de brûleur (5) entourée par une zone d'extrémité côté sortie du mélangeur (3), du fait que la lance (4) est disposée avec son extrémité côté sortie (15), au moins pendant le fonctionnement pilote du brûleur (1), dans une partie de l'intérieur de brûleur (5) entourée par le mélangeur (3) et qu'une distance (17) de l'extrémité de la lance (15) à l'ouverture de sortie (9) est supérieure à 25 % et inférieure à 50 % de la distance (18), qu'une extrémité côté sortie (19) du générateur de tourbillon (2) présente par rapport à l'ouverture de sortie (9).
- Brûleur selon la revendication 1, caractérisé en ce que la lance (4) est disposée de façon réglable en longueur sur la tête de brûleur (14), de telle manière qu'elle puisse, en fonction des besoins, être introduite plus ou moins profondément dans l'intérieur de brûleur (5) ou retirée plus ou moins largement hors de celui-ci.
- Brûleur selon la revendication 1 ou 2, caractérisé en ce qu'un tube d'admission (20) est disposé sur la tête de brûleur (14), lequel pénètre coaxialement à la lance (4) dans la partie de l'intérieur de brûleur (5) entourée par le générateur de tourbillon (2) et forme un canal d'admission annulaire (21) pour un carburant liquide, qui présente au moins une ouverture de sortie axiale (22).
- Brûleur selon la revendication 3, caractérisé en ce que le tube d'admission (20) est réalisé à paroi creuse, en ce que le tube d'admission (20) entoure la lance (4) en formant un canal annulaire axialement ouvert (46) pour l'air, et en ce que le canal d'admission (21) est formé dans la paroi creuse (43) du tube d'admission (20).
- Brûleur selon l'une quelconque des revendications 1 à 4, caractérisé en ce que la lance (4) comprend plusieurs tubes (25, 26) disposés de façon concentrique, en ce qu'un tube intérieur central (25) comporte un canal central (27) pour un carburant liquide et présente au moins une ouverture de sortie axiale (28) à l'extrémité (15) de la lance, en ce qu'un tube extérieur à paroi creuse (26) entoure le tube intérieur (25) en formant un canal annulaire intérieur (30) et comporte dans sa paroi creuse (33) au moins un canal extérieur (36, 37) pour un carburant gazeux, et en ce que le canal annulaire intérieur (30) se termine sous forme axialement ouverte à l'extrémité (15) de la lance et sert pour le guidage de l'air.
- Brûleur selon la revendication 5, caractérisé en ce que le canal extérieur (36, 37) est configuré en un canal annulaire dans la paroi creuse (33) du tube extérieur (26), lequel présente à l'extrémité (15) de la lance au moins une ouverture de sortie axiale (28) et/ou la partie d'extrémité de la lance (40) présentant l'extrémité (15) de la lance comporte plusieurs ouvertures de sortie radiales (41).
- Brûleur selon la revendication 5, caractérisé en ce qu'au moins un (premier) canal extérieur (36) est formé dans la paroi creuse (33) du tube extérieur (26), lequel présente à l'extrémité (15) de la lance au moins une ouverture de sortie axiale (28), et/ou en ce qu'au moins un (deuxième) canal extérieur (37) est formé dans la paroi creuse (33) du tube extérieur (26), lequel présente dans une partie d'extrémité de la lance (40) présentant l'extrémité (15) de la lance plusieurs ouvertures de sortie radiales (41).
- Brûleur selon l'une quelconque des revendications 5 à 7, caractérisé en ce que le tube intérieur (25) est saillant axialement au-delà du tube extérieur (26).
- Brûleur selon l'une quelconque des revendications 1 à 8, caractérisé en ce qu'une paroi (49) du mélangeur (3) est équipée d'un refroidissement par film (50).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102007037289 | 2007-08-07 | ||
PCT/EP2008/059321 WO2009019113A2 (fr) | 2007-08-07 | 2008-07-16 | Brûleur pour une chambre de combustion d'un turbogroupe |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2179222A2 EP2179222A2 (fr) | 2010-04-28 |
EP2179222B1 true EP2179222B1 (fr) | 2014-10-22 |
EP2179222B2 EP2179222B2 (fr) | 2021-12-01 |
Family
ID=39865130
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08775142.6A Active EP2179222B2 (fr) | 2007-08-07 | 2008-07-16 | Brûleur pour une chambre de combustion d'un turbogroupe |
Country Status (3)
Country | Link |
---|---|
US (1) | US8069671B2 (fr) |
EP (1) | EP2179222B2 (fr) |
WO (1) | WO2009019113A2 (fr) |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009068425A1 (fr) * | 2007-11-27 | 2009-06-04 | Alstom Technology Ltd | Brûleur à prémélange pour une turbine à gaz |
US8413446B2 (en) * | 2008-12-10 | 2013-04-09 | Caterpillar Inc. | Fuel injector arrangement having porous premixing chamber |
EP2199674B1 (fr) * | 2008-12-19 | 2012-11-21 | Alstom Technology Ltd | Brûleur d'une turbine à gaz avec une configuration spéciale de lance |
US20100175380A1 (en) * | 2009-01-13 | 2010-07-15 | General Electric Company | Traversing fuel nozzles in cap-less combustor assembly |
WO2011054771A2 (fr) | 2009-11-07 | 2011-05-12 | Alstom Technology Ltd | Brûleur à prémélange pour chambre de combustion de turbine à gaz |
EP2496885B1 (fr) | 2009-11-07 | 2019-05-29 | Ansaldo Energia Switzerland AG | Brûleur avec un système de refroidissement permettant d'accroître le rendement d'une turbine à gaz |
EP2496880B1 (fr) | 2009-11-07 | 2018-12-05 | Ansaldo Energia Switzerland AG | Système d'injection pour brûleur de réchauffage |
EP2496882B1 (fr) * | 2009-11-07 | 2018-03-28 | Ansaldo Energia Switzerland AG | Système d'injection pour brûleur de réchauffage avec lances à combustible |
JP6134732B2 (ja) * | 2011-12-05 | 2017-05-24 | ゼネラル・エレクトリック・カンパニイ | マルチゾーン燃焼器 |
US9016039B2 (en) * | 2012-04-05 | 2015-04-28 | General Electric Company | Combustor and method for supplying fuel to a combustor |
EP2685160B1 (fr) | 2012-07-10 | 2018-02-21 | Ansaldo Energia Switzerland AG | Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz |
US8943834B2 (en) * | 2012-11-20 | 2015-02-03 | Niigata Power Systems Co., Ltd. | Pre-mixing injector with bladeless swirler |
US9441543B2 (en) * | 2012-11-20 | 2016-09-13 | Niigata Power Systems Co., Ltd. | Gas turbine combustor including a premixing chamber having an inner diameter enlarging portion |
EP3133342A1 (fr) * | 2015-08-20 | 2017-02-22 | Siemens Aktiengesellschaft | Brûleur à double carburant prémélangé avec un composant d'injection éfilé de carburant liquide principal |
EP3299720B1 (fr) | 2016-09-22 | 2020-11-04 | Ansaldo Energia IP UK Limited | Ensemble avant de chambre de combustion pour turbine à gaz |
US11175035B2 (en) | 2016-10-10 | 2021-11-16 | King Abdullah University Of Science And Technology | Burners for conversion of methane to olefins, aromatics, and nanoparticles |
US10907832B2 (en) | 2018-06-08 | 2021-02-02 | General Electric Company | Pilot nozzle tips for extended lance of combustor burner |
GB2585025A (en) * | 2019-06-25 | 2020-12-30 | Siemens Ag | Combustor for a gas turbine |
US11774093B2 (en) | 2020-04-08 | 2023-10-03 | General Electric Company | Burner cooling structures |
WO2022079523A1 (fr) * | 2020-10-14 | 2022-04-21 | King Abdullah University Of Science And Technology | Injecteur réglable de carburant pour commande de dynamique de flamme |
US11692711B2 (en) | 2021-08-13 | 2023-07-04 | General Electric Company | Pilot burner for combustor |
Family Cites Families (31)
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CH672541A5 (fr) * | 1986-12-11 | 1989-11-30 | Bbc Brown Boveri & Cie | |
CH674561A5 (fr) * | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
JP2713627B2 (ja) * | 1989-03-20 | 1998-02-16 | 株式会社日立製作所 | ガスタービン燃焼器、これを備えているガスタービン設備、及びこの燃焼方法 |
US5408825A (en) * | 1993-12-03 | 1995-04-25 | Westinghouse Electric Corporation | Dual fuel gas turbine combustor |
DE4435266A1 (de) * | 1994-10-01 | 1996-04-04 | Abb Management Ag | Brenner |
US5943866A (en) * | 1994-10-03 | 1999-08-31 | General Electric Company | Dynamically uncoupled low NOx combustor having multiple premixers with axial staging |
DE4446842B4 (de) * | 1994-12-27 | 2006-08-10 | Alstom | Verfahren und Vorrichtung zum Zuleiten eines gasförmigen Brennstoffs in einen Vormischbrenner |
DE19510744A1 (de) * | 1995-03-24 | 1996-09-26 | Abb Management Ag | Brennkammer mit Zweistufenverbrennung |
DE19520291A1 (de) * | 1995-06-02 | 1996-12-05 | Abb Management Ag | Brennkammer |
DE19527453B4 (de) † | 1995-07-27 | 2009-05-07 | Alstom | Vormischbrenner |
DE19545309A1 (de) † | 1995-12-05 | 1997-06-12 | Asea Brown Boveri | Vormischbrenner |
DE19545310B4 (de) † | 1995-12-05 | 2008-06-26 | Alstom | Vormischbrenner |
DE19547913A1 (de) † | 1995-12-21 | 1997-06-26 | Abb Research Ltd | Brenner für einen Wärmeerzeuger |
DE19640198A1 (de) † | 1996-09-30 | 1998-04-02 | Abb Research Ltd | Vormischbrenner |
US5735466A (en) * | 1996-12-20 | 1998-04-07 | United Technologies Corporation | Two stream tangential entry nozzle |
JP3448190B2 (ja) * | 1997-08-29 | 2003-09-16 | 三菱重工業株式会社 | ガスタービンの燃焼器 |
AU2001272682A1 (en) † | 2000-06-15 | 2001-12-24 | Alstom Power N.V. | Method for operating a burner and burner with stepped premix gas injection |
DE10050248A1 (de) † | 2000-10-11 | 2002-04-18 | Alstom Switzerland Ltd | Brenner |
DE10051221A1 (de) † | 2000-10-16 | 2002-07-11 | Alstom Switzerland Ltd | Brenner mit gestufter Brennstoff-Eindüsung |
DE10104695B4 (de) † | 2001-02-02 | 2014-11-20 | Alstom Technology Ltd. | Vormischbrenner für eine Gasturbine |
DE10164099A1 (de) * | 2001-12-24 | 2003-07-03 | Alstom Switzerland Ltd | Brenner mit gestufter Brennstoffeinspritzung |
DE10205839B4 (de) * | 2002-02-13 | 2011-08-11 | Alstom Technology Ltd. | Vormischbrenner zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen |
DE10334228A1 (de) * | 2002-08-19 | 2004-03-04 | Alstom (Switzerland) Ltd. | Verfahren zum Betrieb eines Vormischbrenners sowie Vorrichtung zur Durchführung des Verfahrens |
US6786046B2 (en) * | 2002-09-11 | 2004-09-07 | Siemens Westinghouse Power Corporation | Dual-mode nozzle assembly with passive tip cooling |
US7284378B2 (en) * | 2004-06-04 | 2007-10-23 | General Electric Company | Methods and apparatus for low emission gas turbine energy generation |
DE10345137B4 (de) * | 2003-09-29 | 2014-02-13 | Alstom Technology Ltd. | Verfahren zum Betrieb einer Brennstoffeinspritzvorrichtung sowie eine Brennstoffeinspritzvorrichtung zur Durchführung des Verfahrens |
US6935117B2 (en) * | 2003-10-23 | 2005-08-30 | United Technologies Corporation | Turbine engine fuel injector |
MX2007004119A (es) * | 2004-10-18 | 2007-06-20 | Alstom Technology Ltd | Quemador para turbina de gas. |
DE102005015152A1 (de) * | 2005-03-31 | 2006-10-05 | Alstom Technology Ltd. | Vormischbrenner für eine Gasturbinenbrennkammer |
EP1943464A1 (fr) † | 2005-11-04 | 2008-07-16 | ALSTOM Technology Ltd | Lance à combustible |
US8127546B2 (en) * | 2007-05-31 | 2012-03-06 | Solar Turbines Inc. | Turbine engine fuel injector with helmholtz resonators |
-
2008
- 2008-07-16 EP EP08775142.6A patent/EP2179222B2/fr active Active
- 2008-07-16 WO PCT/EP2008/059321 patent/WO2009019113A2/fr active Application Filing
-
2010
- 2010-01-27 US US12/694,506 patent/US8069671B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
EP2179222A2 (fr) | 2010-04-28 |
WO2009019113A3 (fr) | 2009-06-11 |
EP2179222B2 (fr) | 2021-12-01 |
US20100146983A1 (en) | 2010-06-17 |
US8069671B2 (en) | 2011-12-06 |
WO2009019113A2 (fr) | 2009-02-12 |
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