EP1673576A1 - Procede et dispositif de combustion d'un combustible - Google Patents

Procede et dispositif de combustion d'un combustible

Info

Publication number
EP1673576A1
EP1673576A1 EP04790361A EP04790361A EP1673576A1 EP 1673576 A1 EP1673576 A1 EP 1673576A1 EP 04790361 A EP04790361 A EP 04790361A EP 04790361 A EP04790361 A EP 04790361A EP 1673576 A1 EP1673576 A1 EP 1673576A1
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.)
Granted
Application number
EP04790361A
Other languages
German (de)
English (en)
Other versions
EP1673576B1 (fr
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP04790361A priority Critical patent/EP1673576B1/fr
Publication of EP1673576A1 publication Critical patent/EP1673576A1/fr
Application granted granted Critical
Publication of EP1673576B1 publication Critical patent/EP1673576B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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 burning fuel in a combustion chamber.
  • combustion systems are known, which are divided into three groups:
  • Standard low-NOx systems are pre-mixed with fuel and combustion air before they enter a combustion chamber. A developing flame is subsequently stabilized within the combustion chamber and the oxidation reaction is thereby controlled. Due to the remaining immiscibility, locally high temperatures occur within the combustion chamber, which can lead to an undesirably high NOx emission. For this reason, the flame in standard low-NOx systems is generally primarily aerodynamically stabilized, as a result of which hot combustion gases are recirculated so that they react with the mixture of fuel and combustion air entering the combustion chamber. The aerodynamic stabilization is supported by the use of hot support flames (so-called piloting), which can lead to a further inhomogeneity of the temperature distribution in the combustion chamber. Such an inhomogeneous temperature distribution can be an additional source of nitrogen oxides. be that. It is therefore common for standard low NOx systems to reduce the NOx emissions that are primarily generated by catalytic exhaust gas purification.
  • catalytic combustion systems are currently limited, so that, for example, for high-temperature combustion systems, such as State-of-the-art stationary gas turbines, no catalytic combustion can be used.
  • Catalytic combustion systems are only used in smaller stationary gas turbines.
  • So-called flame-less oxidation burners are known for industrial combustion systems, as described, for example, in EP 0 463 218 B1.
  • combustion air is preheated with the help of the exhaust gas and fed to a combustion chamber with a high pulse in a radial edge region.
  • a fuel gas is injected separately into the center of the combustion chamber.
  • the preheated combustion air mixes with recirculating exhaust gas in the edge area of the combustion chamber and inside with the separately supplied fuel gas.
  • the object of the invention is to create a method and a device for burning fuel in a combustion chamber, in particular for gas turbines, in which stable and complete combustion and significantly reduced NOx emissions are achieved.
  • the object is achieved according to the invention with a method for burning fuel in a combustion chamber, in which fuel and combustion air are mixed before entering the combustion chamber while avoiding auto-ignition, a first part of the mixture is introduced into the combustion chamber in such a way that it Combustion chamber circulates, into the circulation flow of the first part of the mixture further fuel is fed until warming up to ignition conditions would be guaranteed and at least a second part of the mixture is introduced into the combustion chamber in this way, that it mixes with a hot fuel gas flowing out of the circulation flow, heats up and burns until it exits the combustion chamber.
  • the object is further achieved with a device for burning fuel in a combustion chamber, with a mixing device for mixing fuel and combustion air before entering the combustion chamber while avoiding auto-ignition, and 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 warming up to ignition conditions would be guaranteed, 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 a second part of the mixture mixes with a hot fuel gas flowing out of the circulation flow, heats up and burns until it emerges from the combustion chamber.
  • a first amount of fuel for example a fuel gas 1
  • combustion air before it enters the combustion chamber, avoiding auto-ignition.
  • the mixture of fuel and combustion air is introduced into the combustion chamber in such a way that a first part of the mixture circulates in a recirculation vortex and at least a second part of the mixture mixes with the hot exhaust gas or fuel gas flowing out of the vortex.
  • the addition of the remaining fuel according to the invention in one or more further stages (for example fuel gas 2) into the recirculation vortex provides so much energy that heating of the entire air / fuel mixture to ignition conditions would be ensured or until ignition conditions available.
  • the further fuel is mixed in such a way that it is mixed homogeneously into the fuel gas at a low temperature level. In this way, temperature peaks within the combustion chamber are avoided according to the invention. The result is a particularly low formation of NOx from this area of the reacting fuel gas flow.
  • the fuel and the combustion air are mixed before entering the combustion chamber in such a way that the ratio of combustion air to fuel is above the average air / fuel ratio of the combustion in the combustion chamber.
  • the high air / fuel ratio according to the invention ensures a comparatively low temperature level, as a result of which the NOx formation is reduced.
  • the device according to the invention can be designed particularly advantageously by introducing the first and / or the second part of the mixture (and / or further parts in the case of a multi-stage addition of fuel) from fuel and combustion air through a body arranged centrally in the combustion chamber.
  • the first and / or the second mixture introduction device are arranged in such a central inflow body.
  • the circulation flow of the first part of the mixture aimed at according to the invention and the introduction of the second part of the mixture into outflowing, hot fuel gas can then be achieved relatively simply in terms of flow technology.
  • a central inflow body for the first and / or the second part of the mixture of fuel and combustion air also advantageously offers the possibility of integrating a device for introducing liquid fuel into the combustion chamber.
  • a centrally arranged mixture introduction device is further cooled by the mixture of fuel and combustion air flowing in it, as a result of which the mixture is minimally heated. The heating results in a further homogenization of the temperature level within the circulation flow according to the invention.
  • the circulation flow itself is advantageous according to the invention in a peripheral region of the combustion chamber, i.e. formed in a radially outer section of the combustion chamber.
  • a recirculation vortex designed in this way advantageously forms the basis for the most homogeneous possible mixing of further fuel into the combustion chamber.
  • the combustion chamber is essentially cylindrical and the first part of the mixture of fuel and combustion air is introduced essentially radially into the combustion chamber.
  • the circulation flow aimed at according to the invention is excited and maintained by the radial introduction of the first part of the mixture.
  • an annular combustion chamber with a correspondingly designed fuel supply can be provided.
  • the further fuel is advantageously introduced essentially axially into the combustion chamber.
  • Such addition of residual fuel (fuel gas 2) into the recirculation vortex provides the necessary amount of energy so that the desired warming up of the entire air / fuel mixture to ignition conditions would be guaranteed.
  • Another advantage of an axia The introduction of the additional fuel is such that the added additional fuel also contributes to cooling the combustion chamber end wall and the additional fuel is thus slightly preheated.
  • the first and the second part of the mixture of fuel and combustion air are advantageously introduced into the combustion chamber as a common stream and only divided within the combustion chamber.
  • FIG. 1 shows a longitudinal section of an exemplary embodiment of a device according to the invention for combusting fuel in a combustion chamber.
  • the device 10 for burning fuel in a combustion chamber in the form of a burner for a stationary gas turbine.
  • the device 10 has a combustion chamber 12, which in the Is essentially circular cylindrical along an axis 14.
  • the combustion chamber 12 is formed with a first end wall 16, shown above with reference to FIG. 1, an outer wall 18 extending downward therefrom and a second end wall 20 lying below with respect to FIG.
  • the first end wall 16 is penetrated by a centrally arranged body 22, which is essentially circular-cylindrical and also extends along the axis 14.
  • the body 22 is designed with an outer tube 24 and an inner tube 26 arranged concentrically therein.
  • the outer tube 24 is penetrated by radially outwardly directed nozzles 28 which, based on FIG. 1, are located at the lower end region of the outer tube 24. Otherwise, the outer tube 24 is closed at this end region.
  • an air supply 30, which is not illustrated in any more detail, and a fuel gas supply 32, also not shown in detail, is provided in the interior of the outer tube.
  • Air or a first fuel gas is fed into the outer tube 24 through the air feed 30 and the fuel gas feed 32, in which a mixture 34 of fuel gas and combustion air subsequently forms in the direction of flow onto the nozzles 28.
  • a first partial flow 36 of this mixture 34 emerges from a part of the nozzles 28 into the surroundings of the outer tube 24 and thus into the interior of the combustion chamber 12.
  • a second partial flow 38 of the mixture 34 emerges through further nozzles 28 ′, which are arranged further down on the outer tube 24 with respect to the above-mentioned nozzles 28 of the first partial flow 36 and with reference to FIG. 1.
  • the outer tube 24 is essentially surrounded by a recirculation chamber 40, to which a further combustion chamber 42 is connected within the combustion chamber 12.
  • Flow guide surfaces 44 are arranged on the inside of the outer wall 18 between the recirculation space 40 and the further combustion space 42. With the help of these flow guide surfaces 44 and the introduction of the first partial flow 36 (and also the second partial flow 38), which is explained in more detail below, a circulation flow 46 is excited and stabilized within the recirculation space 40, which flow is initially directed radially outwards from the nozzles 28, is subsequently directed towards the first end wall 16 and radially inward along the latter and finally reaches the nozzles 28 again from the first end wall 16.
  • a further fuel gas supply 48 is provided on the first end wall 16. Through this further fuel gas supply 48, further fuel gas enters the circulation flow 46.
  • fuel gas 50 flowing out of the circulation flow 46 emerges in the area in front of the nozzles 28 "and passes through the further combustion chamber 42 to an outlet 52 which is formed in the end wall 20 as an essentially central opening.
  • this opening is annular.
  • a mixture 34 of fuel gas and fuel air is fed through the outer tube 24, the air feed 30 and the fuel gas feed 32 to the nozzles 28 and 28 ′, in which the ratio of air and fuel gas above the average air / Fuel gas ratio of the later combustion is within the combustion chamber 12. In this way, self-ignition of the mixture 34 is avoided.
  • the mixture 34 is introduced as the first partial flow 36 and the second partial flow 38 essentially radially into the combustion chamber 12.
  • the nozzles 28 are arranged and shaped in such a way that the first partial flow 36 essentially enters the circulation flow 46 and thus excites a recirculation vortex within the recirculation space.
  • Addition of further fuel gas by means of the further fuel gas supply 48 in an essentially axial direction additionally supports the recirculation vortex and provides so much energy that, in principle, the entire mixture is warmed up to ignition conditions.
  • such a quantity of gas is mixed in per time unit that the mixing in the recirculation vortex is as homogeneous as possible and temperature peaks are avoided.
  • the mixing takes place at a comparatively low temperature level, so that although the fuel gas reacts with the combustion air, this reaction only leads to very low NOx emissions.
  • the fuel gas supply 48 also contributes to cooling the first end wall 16 of the combustion chamber 12.
  • the second partial flow 38 of the mixture 34 and, if appropriate, further partial flows directly enter the outflowing fuel gas 50 through the nozzles 28 ', for example in the form of tubes, or can also recirculate in whole or in part in an exemplary embodiment not shown.
  • the outflowing fuel gas 50 is comparatively hot, so that the second partial flow 38 is heated in sufficient form and also reacts completely up to the outlet 52.
  • the centrally arranged body 22 and the inner tube 26 formed therein offers the possibility of integrating liquid fuel nozzles, so that the device 10 can be used as a whole as a two-fuel system.
  • the device 10 can thus also be used to oxidize liquid fuel in a comparatively low-pollutant manner, which has hitherto not been possible in conventional systems with catalysts.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne un procédé et un dispositif (10) destinés à la combustion d'un combustible dans une chambre de combustion (12), ce procédé et ce dispositif permettant d'obtenir une combustion caractérisée par des émissions de NOx particulièrement faibles. A cet effet, le combustible et l'air comburant sont mélangés sans inflammation spontanée avant d'entrer dans la chambre de combustion (12), une première partie (36) du mélange (34) est introduite dans la chambre de combustion (12) de façon à circuler dans celle-ci, une quantité supplémentaire de combustible est acheminée dans le flux de circulation (46) de la première partie (36) du mélange (34) jusqu'à ce que la température atteigne des conditions d'allumage, puis au moins une deuxième partie (38) du mélange (34) est introduite dans la chambre de combustion (12) de sorte qu'elle se mélange à un gaz combustible chaud (50) provenant du flux de circulation (46), se réchauffe et brûle jusqu'à ce qu'elle sorte de la chambre de combustion (12).
EP04790361A 2003-10-13 2004-10-13 Procede et dispositif de combustion d'un combustible Expired - Lifetime EP1673576B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04790361A EP1673576B1 (fr) 2003-10-13 2004-10-13 Procede et dispositif de combustion d'un combustible

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03023210A EP1524473A1 (fr) 2003-10-13 2003-10-13 Procédé et dispositif pour brûler du carburant
PCT/EP2004/011490 WO2005038348A1 (fr) 2003-10-13 2004-10-13 Procede et dispositif de combustion d'un combustible
EP04790361A EP1673576B1 (fr) 2003-10-13 2004-10-13 Procede et dispositif de combustion d'un combustible

Publications (2)

Publication Number Publication Date
EP1673576A1 true EP1673576A1 (fr) 2006-06-28
EP1673576B1 EP1673576B1 (fr) 2008-05-07

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 Expired - Lifetime EP1673576B1 (fr) 2003-10-13 2004-10-13 Procede et dispositif de combustion d'un combustible

Family Applications Before (1)

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

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)

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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
WO2007033306A2 (fr) 2005-09-13 2007-03-22 Rolls-Royce Corporation, Ltd. Systemes de combustion pour turbine a gaz
AU2007310971A1 (en) * 2006-10-18 2008-04-24 Lean Flame, Inc. Premixer for gas and fuel for use in combination with energy release/conversion device
EP1950494A1 (fr) * 2007-01-29 2008-07-30 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
CA2713030C (fr) 2008-02-01 2013-07-23 Ihi Corporation Rechauffeur a combustion
JP2009186023A (ja) * 2008-02-01 2009-08-20 Ihi Corp 燃焼加熱器
US8689562B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Combustion cavity layouts for fuel staging in trapped vortex combustors
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
ITMI20131931A1 (it) 2013-11-20 2015-05-21 Tenova Spa Bruciatore industriale autorigenerativo e forno industriale per la conduzione di processi di combustione autorigenerativa
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
CN116608488B (zh) * 2022-02-09 2025-07-15 中国航发商用航空发动机有限责任公司 无焰燃烧室、航空发动机及飞行器

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Also Published As

Publication number Publication date
CN1860334A (zh) 2006-11-08
ES2303104T3 (es) 2008-08-01
DE502004007082D1 (de) 2008-06-19
JP2007508515A (ja) 2007-04-05
CN1860334B (zh) 2012-02-01
JP4499734B2 (ja) 2010-07-07
WO2005038348A1 (fr) 2005-04-28
US20070141519A1 (en) 2007-06-21
EP1524473A1 (fr) 2005-04-20
EP1673576B1 (fr) 2008-05-07

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