EP2402655A1 - Module de brûleur - Google Patents

Module de brûleur Download PDF

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Publication number
EP2402655A1
EP2402655A1 EP10168215A EP10168215A EP2402655A1 EP 2402655 A1 EP2402655 A1 EP 2402655A1 EP 10168215 A EP10168215 A EP 10168215A EP 10168215 A EP10168215 A EP 10168215A EP 2402655 A1 EP2402655 A1 EP 2402655A1
Authority
EP
European Patent Office
Prior art keywords
fuel
plate
cavities
module according
burner
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Withdrawn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
EP10168215A
Other languages
German (de)
English (en)
Inventor
Matthias Hase
Nicolas Savilius
Oliver Schneider
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 EP10168215A priority Critical patent/EP2402655A1/fr
Priority to PCT/EP2011/057820 priority patent/WO2012000712A1/fr
Priority to EP11720444.6A priority patent/EP2588806B1/fr
Publication of EP2402655A1 publication Critical patent/EP2402655A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • F23D14/24—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00012—Liquid or gas fuel burners with flames spread over a flat surface, either premix or non-premix type, e.g. "Flächenbrenner"

Definitions

  • the invention relates to a burner module according to the preamble of claim 1.
  • micro flame burners Another approach to gas turbine combustion is the use of micro flame burners.
  • the number of flames is significantly increased compared to the design in the prior art (number depending on the power (> 1000)).
  • the size of the flames is only a few millimeters to a few centimeters.
  • the shorter residence time at high temperatures drastically reduces the formation of thermal NOx. Due to the good burnout, the formation of CO is minimized.
  • the DE 2023 060 shows a burner for gaseous fuels with a perforated porous outlet plate which is adjacent to a combustion zone on one side and to a base plate on the other.
  • the base plate is connected to the exit plate such that the perforations or holes in the exit plate are congruent with the perforations or holes in the base plate. So air can flow through them.
  • the exit points have such a distance from the base plate between the holes that fuel passageways are formed. These provide the flow of fuel gas with a resistance that is low compared to the flow resistance through the outlet plate.
  • the burner as a whole is designed so that during the Using the burner gaseous fuel flows through the fuel passages and from there through the porous discharge plate in the combustion zone, where it burns with the sucked through the perforations or holes air.
  • the EP 1 001 216 A1 shows a disc, with openings passing through the disc. Channels are arranged transversely to the openings through which fuel is passed. Through these channels fuel can be supplied to the openings.
  • microflame burners a major drawback is that the high number of microflame burners adds enormously to the cost of manufacturing the entire gas turbine unless an efficient manufacturing process of a correspondingly simple design is used. At the same time, however, each individual burner must ensure adequate mixing of air and fuel / fuel gas. In addition, a certain control range for the power control of the gas turbine is desirable, which must be achieved differently for small flames than for large ones.
  • the object of the present invention is therefore to provide a burner module which avoids the above disadvantages while maintaining the above-mentioned conditions.
  • burner module according to the invention thus individual parts of the combustion chamber or the entire combustion chamber can be replaced by such burner modules.
  • the design and manufacture of the individual modules is very cost-efficient and can also be used in small applications and also reduce costs here.
  • the burner module according to the invention reduces the required residence time in the combustion chamber.
  • the combustion chamber compared to the combustion chambers in the prior art can be significantly reduced.
  • the costs and the effort can be reduced here as well.
  • the reduction of the combustion chamber simultaneously allows a shortening of the rotor or the entire gas turbine.
  • material costs are saved to a great extent and the dynamic behavior of the machine with respect to vibrations and mass inertia is improved.
  • the surface of the combustion chamber to be cooled also decreases. Cooling air can be saved here, which improves the efficiency of the overall process.
  • Fig. 1 shows a section along an axis II of a burner module according to the invention according to a first embodiment.
  • Fig. 2 shows the section of the first embodiment along the axis II to II extending perpendicular to II.
  • the burner module consists of a plate 90 with a bottom 91. On this bottom 91, a top 92 is fixed by soldering or welding, the centering is accomplished with index holes and pinnacles. In the bottom 91 at least two, however, usually more cavities are introduced.
  • the cavities may be a laser cut or an erosion or an embossing or a pressing, but are not limited to this manufacturing method.
  • the cavities are supplied with fuel 110 (not shown). These cavities are in the first embodiment grooves 95 (FIG. Fig.2 ).
  • grooves 95 laser cutting, milling, EDM or embossing / pressing.
  • Fig. 2 shown - several such grooves 95 on a burner module, they are preferably parallel to each other, that is arranged in rows.
  • fuel 110 is provided in the grooves 95 .
  • the grooves 95 open into a collection channel (not shown) at the end of the burner module and are then connected to a fuel supply system (not shown) via a suitable flange construction.
  • a passageway 98 is now attached, which extends from the bottom 91 to the top 92.
  • the passageway 98 has a passageway end 111 in the top 92.
  • the plate 90 consists of a plurality of passageways 98 and a plurality of cavities.
  • the passageways 98 serve to guide air 100 through the plate 90.
  • the air 100 may also be an air-fuel mixture.
  • an air flow direction L is formed by the air 100 flowing through the passageways 98. Downstream of the plate 90 in the air flow direction L is a combustion chamber (not shown).
  • the air 100 is transported through the passageways 98 into the combustion chamber.
  • the through-passages 98 like the cavities, are introduced into the plate 90, for example by punching, drilling or laser drilling.
  • the passageway 98 is also not limited to this type of manufacture, but these represent a particularly simple method of manufacture.
  • the passageway 98 has at least two mutually opposite channel openings 101 (FIG. Fig. 2 ) on; that is, they are arranged at the same height in the passageway 98. This allows a better turbulence of the fuel with the air 100 take place.
  • the plate 90 also has two fuel connections 105 leading from the grooves 95 to the channel openings 101.
  • the fuel connections 105 are at the same height with the channel openings 101.
  • the fuel connections 105 are introduced, for example, by punching, eroding or laser drilling.
  • the fuel 110 may thus be injected from the grooves 95 via the fuel connections 105 into the flow of the air 100 of the passageway 98 and thus mix.
  • the fuel connections 105 can be arranged in such a way to the through-passage 98, which here essentially sets a 90 ° angle. This results in a particularly good mixing ratio of fuel with the air 100.
  • compressed air 100 flows through the passageways 98 into the combustion chamber.
  • Fuel 110 enters the air 100 from the grooves 95 through the fuel connections 105. After appropriate mixing then burns a flame essentially as a premix flame or partially pre-mixed flame behind the flame bottom.
  • the channel openings 101 are placed directly under the top side 92 ( Fig. 1 ), this results in the combustion of a premixed or partially premixed flame.
  • the upper side 92 then contains exclusively the through-channel end 111 (seen in the air flow direction L) (FIG. Fig.1 ).
  • the through-channel end 111 is designed as a diffuser for mixing air 100 with fuel 110. This results in a change in the flow rate of the flow present in the passageway 98, resulting in improved mixing and inflow into the combustion chamber.
  • Fig. 3 shows a second embodiment of a burner module according to the invention.
  • the plate 90 consists of a bottom 91 and a top 92.
  • hollow areas 120 are introduced as cavities.
  • the plate 90 has a plurality of hollow regions 120 and through channels 98.
  • Hollow regions 120 also include fuel (not shown).
  • the hollow regions 120 are formed as honeycomb-shaped ( Fig. 5 ) or square ( Fig. 4 ) Pattern distributed in the plate 90.
  • the pattern can be made by milling grooves over cross or embossing.
  • the hollow regions 120 can thereby be triangular with a side surface b and arranged at a distance a from each other ( Fig. 5 ).
  • the hollow regions 120 can also be made quadrangular with a side surface b and arranged at a distance a from each other ( Figure 4 ).
  • the geometric arrangement of the hollow regions 120 in the plate is not limited to these geometric shapes.
  • the hollow regions 120 may have any other shape.
  • Passage channels 98 are also provided with channel openings 101.
  • the passageways 98 have honeycomb-shaped ( Fig. 5 ) or square ( Fig. 4 ) Distribution of the hollow regions 120 preferably three channel openings 101 or four channel openings 101.
  • the three or four channel openings 101 each relate to a passage channel 98.
  • the channel openings 101 may be arranged in the upper side 92, so that the fuel either first in the combustion chamber with the air 100 mixes (that is, the channel openings are on the surface 92 is arranged) or in the passageway 98, just before entry of the air 100 into the combustion chamber.
  • the fuel connections 105 directed to the passageway 98 obliquely radially inward, possibly employed tangentially to the passageway 98.
  • the two fuel connections 105 to the through-passage 98 can have an angle between> 0 and 90 °. This will increase the mix.
  • Fuel which is guided in the hollow region 120 thus escapes into the flow of the air 100 of the through-channel 98 via the fuel connections 105, which are oriented obliquely radially inward, possibly tangentially engaged. The flame then burns after appropriate mixing essentially as a diffusion flame behind the flame bottom.
  • a combustion chamber is formed by a plurality of burner modules.
  • the combustion chamber can be significantly reduced in size, as a conventional combustion chamber with e.g. Pilot burner.
  • the described construction and method of manufacture allows the advantages of micro flame burners to be used cost-effectively also in gas turbines for large scale industrial applications.
  • the concept of construction and production described here can also find use in small applications and also reduce costs here.
  • the design allows for a fast and intensive mixing of fuel and air 100, with just the supply of fuel, with tangential or at 90 ° angle, arranged for air flow fuel compounds leads to excellent mixing ratios. Due to the concept, the required residence time in the combustion chamber is reduced or the combustion chamber can be downsized. Thus, the costs and the effort can be reduced here as well.
  • the reduction of the combustion chamber also allows a shortening of the rotor or the entire gas turbine, here are largely saved material costs, the dynamic behavior of the machine with respect to vibration and inertia improved. By reducing the size of the combustion chamber, the surface of the combustion chamber to be cooled also decreases. Cooling air can be saved here, which improves the efficiency of the overall process.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP10168215A 2010-07-02 2010-07-02 Module de brûleur Withdrawn EP2402655A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP10168215A EP2402655A1 (fr) 2010-07-02 2010-07-02 Module de brûleur
PCT/EP2011/057820 WO2012000712A1 (fr) 2010-07-02 2011-05-16 Module brûleur
EP11720444.6A EP2588806B1 (fr) 2010-07-02 2011-05-16 Module de brûleur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10168215A EP2402655A1 (fr) 2010-07-02 2010-07-02 Module de brûleur

Publications (1)

Publication Number Publication Date
EP2402655A1 true EP2402655A1 (fr) 2012-01-04

Family

ID=43536656

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10168215A Withdrawn EP2402655A1 (fr) 2010-07-02 2010-07-02 Module de brûleur
EP11720444.6A Active EP2588806B1 (fr) 2010-07-02 2011-05-16 Module de brûleur

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11720444.6A Active EP2588806B1 (fr) 2010-07-02 2011-05-16 Module de brûleur

Country Status (2)

Country Link
EP (2) EP2402655A1 (fr)
WO (1) WO2012000712A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103881760A (zh) * 2014-01-26 2014-06-25 西安交通大学 一种新型微通道循环冷却的气化工艺烧嘴

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1968395A (en) * 1932-02-03 1934-07-31 Carl L Zeller Gas burner
DE2023060A1 (de) 1969-05-19 1971-03-11 British Petroleum Co Brenner fuer gasfoermige Brennstoffe
US5881756A (en) * 1995-12-22 1999-03-16 Institute Of Gas Technology Process and apparatus for homogeneous mixing of gaseous fluids
EP1001216A1 (fr) 1998-11-11 2000-05-17 Siemens Aktiengesellschaft Dispositif pour injecter un fluide dans un conduit
US6267585B1 (en) * 1995-12-19 2001-07-31 Daimlerchrysler Aerospace Airbus Gmbh Method and combustor for combusting hydrogen
EP1741978A2 (fr) * 2005-07-01 2007-01-10 J. Eberspächer GmbH & Co. KG Structure de la paroi d'un brûleur
EP2039996A1 (fr) * 2007-09-21 2009-03-25 Electrolux Home Products Corporation N.V. Brûleur au gaz pour table de cuisson

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8157189B2 (en) * 2009-04-03 2012-04-17 General Electric Company Premixing direct injector

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1968395A (en) * 1932-02-03 1934-07-31 Carl L Zeller Gas burner
DE2023060A1 (de) 1969-05-19 1971-03-11 British Petroleum Co Brenner fuer gasfoermige Brennstoffe
US6267585B1 (en) * 1995-12-19 2001-07-31 Daimlerchrysler Aerospace Airbus Gmbh Method and combustor for combusting hydrogen
US5881756A (en) * 1995-12-22 1999-03-16 Institute Of Gas Technology Process and apparatus for homogeneous mixing of gaseous fluids
EP1001216A1 (fr) 1998-11-11 2000-05-17 Siemens Aktiengesellschaft Dispositif pour injecter un fluide dans un conduit
EP1741978A2 (fr) * 2005-07-01 2007-01-10 J. Eberspächer GmbH & Co. KG Structure de la paroi d'un brûleur
EP2039996A1 (fr) * 2007-09-21 2009-03-25 Electrolux Home Products Corporation N.V. Brûleur au gaz pour table de cuisson

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103881760A (zh) * 2014-01-26 2014-06-25 西安交通大学 一种新型微通道循环冷却的气化工艺烧嘴
CN103881760B (zh) * 2014-01-26 2015-11-25 西安交通大学 一种新型微通道循环冷却的气化工艺烧嘴

Also Published As

Publication number Publication date
EP2588806A1 (fr) 2013-05-08
EP2588806B1 (fr) 2014-08-20
WO2012000712A1 (fr) 2012-01-05

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