EP1524473A1 - Procédé et dispositif pour brûler du carburant - Google Patents

Procédé et dispositif pour brûler du carburant Download PDF

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Publication number
EP1524473A1
EP1524473A1 EP03023210A EP03023210A EP1524473A1 EP 1524473 A1 EP1524473 A1 EP 1524473A1 EP 03023210 A EP03023210 A EP 03023210A EP 03023210 A EP03023210 A EP 03023210A EP 1524473 A1 EP1524473 A1 EP 1524473A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
fuel
mixture
combustion
circulation flow
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.)
Withdrawn
Application number
EP03023210A
Other languages
German (de)
English (en)
Inventor
Gerald Lauer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP03023210A priority Critical patent/EP1524473A1/fr
Priority to US10/575,514 priority patent/US20070141519A1/en
Priority to EP04790361A priority patent/EP1673576B1/fr
Priority to ES04790361T priority patent/ES2303104T3/es
Priority to DE502004007082T priority patent/DE502004007082D1/de
Priority to CN2004800283630A priority patent/CN1860334B/zh
Priority to PCT/EP2004/011490 priority patent/WO2005038348A1/fr
Priority to JP2006530150A priority patent/JP4499734B2/ja
Publication of EP1524473A1 publication Critical patent/EP1524473A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/36—Supply of different fuels
    • 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

Definitions

  • the invention relates to a method and a device for Combustion of fuel in a combustion chamber.
  • So-called standard low-NOx systems are with a premix of fuel and combustion air before entering one Provided combustion chamber. Inside the combustion chamber will be below a forming flame stabilizes and the oxidation reaction controlled by it. Due to remaining Blends occur locally within the combustion chamber high temperatures, resulting in an undesirably high NOx emission being able to lead. Therefore, in standard low-NOx systems the flame is usually primarily aerodynamically stabilized, whereby hot combustion gases are recirculated, so that they mix with the mixture entering the combustion chamber Fuel and combustion air react. The aerodynamic stabilization is supported by the use of hot support flames (so-called piloting), leading to further inhomogenization the temperature distribution in the combustion chamber being able to lead. Such an inhomogeneous temperature distribution can be an additional source of nitric oxide be. It is therefore common for standard low-NOx systems the primary NOx emissions from a catalytic Emission control can be lowered.
  • catalytic combustion systems are currently limited so that, for example, for high-temperature combustion systems, such as. stationary gas turbines state-of-the-art Type, no catalytic burns are used can. Only in smaller stationary gas turbines become catalytic Combustion systems already used.
  • Flameless Oxidation Burner known, as for example in EP 0 463 218 B1 are described.
  • Combustion air is preheated by means of the exhaust gas and in a Radial edge region of a combustion chamber fed with a high pulse.
  • a fuel gas injected In the center of the combustion chamber is separately a fuel gas injected.
  • the preheated combustion air mixes in the edge area the combustion chamber with recirculating exhaust and inside with the separately supplied fuel gas.
  • the invention is based on the object, a method and a device for burning fuel in one Combustion chamber in particular for gas turbines to create in which a stable and complete combustion as well as distinct Reduced NOx emissions can be achieved.
  • the object is according to the invention with a method for Burning of fuel dissolved in a combustion chamber, at the fuel and combustion air before entering the combustion chamber be mixed while avoiding auto-ignition, a first part of the mixture is introduced into the combustion chamber is that it circulates in the combustion chamber, in the Circulation flow of the first part of the mixture further Fuel is supplied until a warm up to ignition conditions guaranteed, and at least a second part the mixture is introduced into the combustion chamber, that he is with an outflow from the circulation flow, hot fuel gas mixes, heats up and up to his Exit from the combustion chamber burns.
  • the task is further comprising a device for burning fuel in a combustion chamber dissolved, with a mixing device for mixing of fuel and combustion air before entering the Combustion chamber, avoiding auto-ignition, a first Mixture introduction device for introducing a first part of the mixture into the combustion chamber, such that the first part of the mixture circulates in the combustion chamber, a fuel introduction device for supplying further fuel into the circulation flow of the first part of the mixture, until a warm-up to ignition conditions would be ensured, and at least one second mixture introduction device for Introducing at least a second part of the mixture into the combustion chamber, such that the at least one second part of the mixture with a flowing out of the circulation flow, hot fuel gas mixes, heats up and up burns out of the combustion chamber.
  • a first quantity of fuel e.g. Fuel gas 1
  • combustion air before entering the combustion chamber premixed while avoiding autoignition.
  • a comparatively low temperature level which is lower as the mean temperature level of comparable Combustion reactions.
  • the burning of this part of the Mixture therefore leads to a relatively low NOx formation.
  • the mixture of fuel and combustion air is according to the invention so introduced into the combustion chamber that a first part of the mixture is circulated in a recirculation vortex and at least a second part of the mixture itself with the effluent from the vortex hot exhaust gas or fuel gas mixed.
  • By mixing with the hot exhaust gas is this part of the mixture is heated in sufficient form and burned to the combustion chamber outlet.
  • a separate pilot in conventional form, however, according to the invention avoided and on aerodynamic stabilization measures by swirl generator can also be dispensed with.
  • the inventive addition of the remaining fuel in one or more further stages (s) for example fuel gas 2 so much energy is provided in the recirculation vortex, that a warming of the entire air / fuel mixture would be guaranteed on ignition conditions or until ignition conditions are present.
  • the further fuel is admixed according to the invention such that a homogeneous Interference in the fuel gas at low temperature level he follows. In this way, according to the invention temperature peaks avoided within the combustion chamber. A special low NOx formation from this area of the reacting Fuel gas flow is the result.
  • the fuel and the combustion air before a Entrance to the combustion chamber mixed so that the ratio combustion air to fuel above the average air / fuel ratio combustion in the combustion chamber lies.
  • the device according to the invention can be particularly advantageous be configured by the first and / or the second Part of the mixture (and / or other parts in a multi-stage Fuel addition) from fuel and combustion air a centrally disposed in the combustion chamber body introduced becomes.
  • a central Zuström emotions arranged the first and / or the second mixture-introduction device.
  • the inventively desired circulation flow of the first part of the mixture and the introduction of the second part of the mixture in outflowing, hot fuel gas can then be relatively easily realized fluidically become.
  • a central inflow body for the first and / or the second Part of the mixture of fuel and combustion air offers further advantageously the possibility that a device for Introducing liquid fuel integrated into the combustion chamber becomes.
  • a centrally arranged mixture introduction device is further characterized by the flowing in her mixture of fuel and combustion air cooled, whereby the mixture minimally heated becomes. The heating has a further homogenization of the temperature level within the circulation flow according to the invention result.
  • the circulation flow itself is advantageous according to the invention in a peripheral region of the combustion chamber, i. in one formed radially outer portion of the combustion chamber.
  • One thus formed recirculation vortex forms advantageous the basis for the most homogeneous possible interference of further fuel into the combustion chamber.
  • the Combustion chamber is designed substantially cylindrical and the first part of the mixture of fuel and combustion air substantially is introduced radially into the combustion chamber.
  • the radial introduction of the first part of the mixture is the inventively desired circulation flow excited and maintained.
  • an annular combustion chamber provided with a correspondingly designed fuel supply be.
  • the other Fuel advantageously substantially axially into the combustion chamber brought in.
  • Such addition of residual fuel (Fuel gas 2) in the recirculation vortex provides the required Amount of energy ready, thus the desired warming up of the entire air / fuel mixture to ignition conditions would be guaranteed.
  • Another advantage of an axial Introducing the other fuel is that the supplied more fuel at the same time also for cooling the combustion chamber end wall contributes and thereby the further Fuel is slightly preheated.
  • the circulation flow according to the invention and operated the combustion produced stable can be beneficial in it per unit of time about 5% to 25%, in particular between about 10% and 20%, the total fuel supplied during a unit time Combustion air mass (total gas mass) recirculated.
  • Fig. 1 is a device 10 for burning fuel in a combustion chamber in the form of a burner for a stationary gas turbine shown.
  • the device 10 has as an essential component of a combustion chamber 12, which in the Essentially circular cylindrical formed along an axis 14 is.
  • the combustion chamber 12 is one with respect to FIG. 1 shown above, first end wall 16, one of them starting downwardly extending outer wall 18 and a, 1, bottom, second end wall 20 formed.
  • the first end wall 16 is arranged centrally Body 22 passes through, which is essentially circular cylindrical is and also extends along the axis 14.
  • the body 22 is concentric with an outer tube 24 and one therein arranged inner tube 26 designed.
  • the outer tube 24 is penetrated by radially outwardly directed nozzles 28, with reference to FIG. 1 at the lower end of the outer tube 24 are located. Otherwise, the outer tube 24 is at this End area closed.
  • the upper end of the outer tube 24 is a further not further illustrated air supply 30 and in Inside the outer tube also not shown in detail Fuel gas supply 32 is provided.
  • Fuel gas supply 32 is provided.
  • a first partial stream 36 of this mixture 34 exits a portion of the nozzles 28 into the environment the outer tube 24 and thus into the interior of the combustion chamber 12th out.
  • a second partial stream 38 of the mixture 34 passes through further nozzles 28 ', based on the above-mentioned nozzles 28 of the first partial flow 36 and with reference to FIG. 1 on are arranged at the bottom of the outer tube 24.
  • the outer tube 24 is substantially of a recirculation space 40 surrounded at the inside of the combustion chamber 12th another combustion chamber 42 connects. Between the recirculation room 40 and the other combustion chamber 42 are on the inside the outer wall 18 flow guide 44 arranged.
  • first partial flow 36th (as well as the second partial flow 38) is within the recirculation space 40 a circulation flow 46 excited and stabilized, starting from the nozzles 28 initially radially directed outwards, subsequently towards the first end wall 16 and directed radially inwardly along this is and finally from the first end wall 16 again reaches the nozzles 28.
  • Fuel gas supply 48 is provided. Through this further Fuel gas supply 48 passes further fuel gas in the circulation flow 46th
  • the air supply 30 and the fuel gas supply 32 to the Nozzles 28 and 28 'a mixture 34 of fuel gas and combustion air supplied, in which the ratio of air and fuel gas over the average air / fuel gas ratio of the later combustion is within the combustion chamber 12. That way is a self-ignition of the mixture 34 avoided.
  • the mixture 34 is the first partial flow 36 and second partial flow 38 introduced substantially radially into the combustion chamber 12.
  • the nozzles 28 are arranged and shaped in this way, that the first partial flow 36 substantially in the Circulation 46 flows and thus within the recirculation space stimulates a recirculation vortex.
  • Addition of further fuel gas through the further fuel gas supply 48 in a substantially axial direction becomes the recirculation vortex additionally supported and so much energy provided that, in principle, a warm-up of the entire Mixture is ensured on ignition conditions.
  • the second partial stream 38 of the mixture 34 and optionally further partial flows occurs / occur through the example as Tubes designed nozzles 28 'directly into the outflowing Fuel gas 50 or can at a not shown Recycle full or partial embodiment also.
  • the outflowing fuel gas 50 is comparatively hot, so that the second partial flow 38 is heated in sufficient form and also fully reacted to the exit 52.
  • the centrally arranged body 22 and the inner tube 26 formed therein the possibility integration of liquid fuel nozzles so that the device 10 as a whole two-fuel system can be used.
  • the device 10 can also liquid fuel in a comparatively low-pollution manner and oxidized, which in conventional systems with Catalysts is not possible so far.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP03023210A 2003-10-13 2003-10-13 Procédé et dispositif pour brûler du carburant Withdrawn EP1524473A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP03023210A EP1524473A1 (fr) 2003-10-13 2003-10-13 Procédé et dispositif pour brûler du carburant
US10/575,514 US20070141519A1 (en) 2003-10-13 2004-10-13 Method and device for the combustion of fuel
EP04790361A EP1673576B1 (fr) 2003-10-13 2004-10-13 Procede et dispositif de combustion d'un combustible
ES04790361T ES2303104T3 (es) 2003-10-13 2004-10-13 Procedimiento para la combustion de combustible.
DE502004007082T DE502004007082D1 (de) 2003-10-13 2004-10-13 Verfahren und vorrichtung zum verbrennen von brennstoff
CN2004800283630A CN1860334B (zh) 2003-10-13 2004-10-13 燃烧燃料的方法和设备
PCT/EP2004/011490 WO2005038348A1 (fr) 2003-10-13 2004-10-13 Procede et dispositif de combustion d'un combustible
JP2006530150A JP4499734B2 (ja) 2003-10-13 2004-10-13 燃料の燃焼方法と装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03023210A EP1524473A1 (fr) 2003-10-13 2003-10-13 Procédé et dispositif pour brûler du carburant

Publications (1)

Publication Number Publication Date
EP1524473A1 true EP1524473A1 (fr) 2005-04-20

Family

ID=34354445

Family Applications (2)

Application Number Title Priority Date Filing Date
EP03023210A Withdrawn EP1524473A1 (fr) 2003-10-13 2003-10-13 Procédé et dispositif pour brûler du carburant
EP04790361A Not-in-force EP1673576B1 (fr) 2003-10-13 2004-10-13 Procede et dispositif de combustion d'un combustible

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP04790361A Not-in-force EP1673576B1 (fr) 2003-10-13 2004-10-13 Procede et dispositif de combustion d'un combustible

Country Status (7)

Country Link
US (1) US20070141519A1 (fr)
EP (2) EP1524473A1 (fr)
JP (1) JP4499734B2 (fr)
CN (1) CN1860334B (fr)
DE (1) DE502004007082D1 (fr)
ES (1) ES2303104T3 (fr)
WO (1) WO2005038348A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1924762A2 (fr) * 2005-09-13 2008-05-28 Rolls-Royce Canada Limited Systemes de combustion pour turbine a gaz
ITMI20131931A1 (it) * 2013-11-20 2015-05-21 Tenova Spa Bruciatore industriale autorigenerativo e forno industriale per la conduzione di processi di combustione autorigenerativa

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04118023A (ja) * 1990-06-07 1992-04-20 Kawasaki Steel Corp みみずの糞土を使用した脱臭方法及びその装置
EP1645805A1 (fr) * 2004-10-11 2006-04-12 Siemens Aktiengesellschaft brûleur pour combustible fluide et procédé pour uriliser un tel brûleur
KR20090099051A (ko) * 2006-10-18 2009-09-21 린 플레임 인코포레이티드 에너지 방출/변환 장치와 조합하여 사용되는 가스/연료 예비 혼합 장치
EP1950494A1 (fr) * 2007-01-29 2008-07-30 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
US9625147B2 (en) 2008-02-01 2017-04-18 Ihi Corporation Combustion heater
JP2009186023A (ja) * 2008-02-01 2009-08-20 Ihi Corp 燃焼加熱器
MY169951A (en) 2009-09-13 2019-06-19 Lean Flame Inc Inlet premixer for combustion apparatus
EP2884175A4 (fr) * 2012-08-13 2015-10-21 Hino Motors Ltd Brûleur
US9909755B2 (en) * 2013-03-15 2018-03-06 Fives North American Combustion, Inc. Low NOx combustion method and apparatus
EP2789915A1 (fr) * 2013-04-10 2014-10-15 Alstom Technology Ltd Procédé de fonctionnement d'une chambre de combustion et chambre de combustion
JP6159145B2 (ja) * 2013-05-14 2017-07-05 三菱日立パワーシステムズ株式会社 燃焼器
CN111520762A (zh) * 2020-03-17 2020-08-11 西北工业大学 基于涡控扩压器原理的新型燃烧室

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB824306A (en) * 1956-04-25 1959-11-25 Rolls Royce Improvements in or relating to combustion equipment of gas-turbine engines
US3820324A (en) * 1970-09-11 1974-06-28 Lucas Industries Ltd Flame tubes for gas turbine engines
US4455839A (en) * 1979-09-18 1984-06-26 Daimler-Benz Aktiengesellschaft Combustion chamber for gas turbines
US4474014A (en) * 1981-09-17 1984-10-02 United Technologies Corporation Partially unshrouded swirler for combustion chambers
EP0463218B1 (fr) 1990-06-29 1994-11-23 Joachim Dr.-Ing. Wünning Procédé et dispositif de combustion du combustible dans une chambre de combustion
US5450725A (en) * 1993-06-28 1995-09-19 Kabushiki Kaisha Toshiba Gas turbine combustor including a diffusion nozzle assembly with a double cylindrical structure
US5619855A (en) * 1995-06-07 1997-04-15 General Electric Company High inlet mach combustor for gas turbine engine
US5647215A (en) * 1995-11-07 1997-07-15 Westinghouse Electric Corporation Gas turbine combustor with turbulence enhanced mixing fuel injectors
US5857339A (en) * 1995-05-23 1999-01-12 The United States Of America As Represented By The Secretary Of The Air Force Combustor flame stabilizing structure
EP1010945A2 (fr) * 1998-12-18 2000-06-21 General Electric Company Dispositif d'injection de carburant pour chambres de combustion de turbines à gaz
US20020112482A1 (en) * 2000-06-28 2002-08-22 Johnson Arthur Wesley Methods for decreasing combustor emissions

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4629416A (en) * 1985-06-11 1986-12-16 Voorheis Industries, Inc. Bluff body register
JPH07305849A (ja) * 1994-05-13 1995-11-21 Ishikawajima Harima Heavy Ind Co Ltd 予混合管
JPH0868537A (ja) * 1994-08-31 1996-03-12 Toshiba Corp ガスタービン燃焼器

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB824306A (en) * 1956-04-25 1959-11-25 Rolls Royce Improvements in or relating to combustion equipment of gas-turbine engines
US3820324A (en) * 1970-09-11 1974-06-28 Lucas Industries Ltd Flame tubes for gas turbine engines
US4455839A (en) * 1979-09-18 1984-06-26 Daimler-Benz Aktiengesellschaft Combustion chamber for gas turbines
US4474014A (en) * 1981-09-17 1984-10-02 United Technologies Corporation Partially unshrouded swirler for combustion chambers
EP0463218B1 (fr) 1990-06-29 1994-11-23 Joachim Dr.-Ing. Wünning Procédé et dispositif de combustion du combustible dans une chambre de combustion
US5450725A (en) * 1993-06-28 1995-09-19 Kabushiki Kaisha Toshiba Gas turbine combustor including a diffusion nozzle assembly with a double cylindrical structure
US5857339A (en) * 1995-05-23 1999-01-12 The United States Of America As Represented By The Secretary Of The Air Force Combustor flame stabilizing structure
US5619855A (en) * 1995-06-07 1997-04-15 General Electric Company High inlet mach combustor for gas turbine engine
US5647215A (en) * 1995-11-07 1997-07-15 Westinghouse Electric Corporation Gas turbine combustor with turbulence enhanced mixing fuel injectors
EP1010945A2 (fr) * 1998-12-18 2000-06-21 General Electric Company Dispositif d'injection de carburant pour chambres de combustion de turbines à gaz
US20020112482A1 (en) * 2000-06-28 2002-08-22 Johnson Arthur Wesley Methods for decreasing combustor emissions

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1924762A2 (fr) * 2005-09-13 2008-05-28 Rolls-Royce Canada Limited Systemes de combustion pour turbine a gaz
EP1924762A4 (fr) * 2005-09-13 2009-10-28 Rolls Royce Canada Ltd Systemes de combustion pour turbine a gaz
US7841181B2 (en) 2005-09-13 2010-11-30 Rolls-Royce Power Engineering Plc Gas turbine engine combustion systems
ITMI20131931A1 (it) * 2013-11-20 2015-05-21 Tenova Spa Bruciatore industriale autorigenerativo e forno industriale per la conduzione di processi di combustione autorigenerativa
WO2015075666A1 (fr) * 2013-11-20 2015-05-28 Tenova S.P.A. Brûleur industriel à auto-régénération et four industriel pour réaliser des processus de combustion à auto-régénération
US10288285B2 (en) 2013-11-20 2019-05-14 Tenova S.P.A. Self-regenerating industrial burner and industrial furnace for carrying out self-regenerating combustion processes

Also Published As

Publication number Publication date
CN1860334A (zh) 2006-11-08
JP2007508515A (ja) 2007-04-05
ES2303104T3 (es) 2008-08-01
CN1860334B (zh) 2012-02-01
WO2005038348A1 (fr) 2005-04-28
JP4499734B2 (ja) 2010-07-07
US20070141519A1 (en) 2007-06-21
EP1673576A1 (fr) 2006-06-28
DE502004007082D1 (de) 2008-06-19
EP1673576B1 (fr) 2008-05-07

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