EP2171354A2 - Brûleur - Google Patents

Brûleur

Info

Publication number
EP2171354A2
EP2171354A2 EP08775346A EP08775346A EP2171354A2 EP 2171354 A2 EP2171354 A2 EP 2171354A2 EP 08775346 A EP08775346 A EP 08775346A EP 08775346 A EP08775346 A EP 08775346A EP 2171354 A2 EP2171354 A2 EP 2171354A2
Authority
EP
European Patent Office
Prior art keywords
inlet
burner
fuel
section
channel
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
EP08775346A
Other languages
German (de)
English (en)
Other versions
EP2171354B1 (fr
Inventor
Harald Schütz
Guido Schmitz
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
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 Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Publication of EP2171354A2 publication Critical patent/EP2171354A2/fr
Application granted granted Critical
Publication of EP2171354B1 publication Critical patent/EP2171354B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23R3/286—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
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F23D14/64—Mixing devices; Mixing tubes with injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2203/00—Gaseous fuel burners
    • F23D2203/007—Mixing tubes, air supply regulation

Definitions

  • the invention relates to a burner with an inlet, which has inlets for fuel and air, and a mixing section adjoining the inlet.
  • EP 0 463 218 B1 describes a burner having an inlet with coaxial inlet for fuel and air.
  • the burner inlet is followed by a mixing section in which fuel and air mix before the mixture enters a combustion chamber.
  • Fuel and air have such a flow impulse that combustion takes place only in the combustion chamber.
  • DE 23 52 204 A1 describes a cylindrical combustion chamber which is surrounded by a gas inlet annular chamber and by a heat exchanger. The combustion gases leaving the combustion chamber are passed through the heat exchanger.
  • a rectangular burner and flame tube member having a cylindrical main combustion chamber or a cylindrical burner and flame tube member having a rectangular main combustion chamber may be combined to form an overall plant.
  • EP 1 112 972 A1 describes a combustion device with a rectangular or round burner block, which is surrounded by a nozzle ring, from which an inert gas emerges.
  • the inert gas generates an annular protective gas jacket of rectangular cross-section around the flame.
  • a pulverized coal combustor is described in EP 0 672 863 A2, in which a restrictor is provided through the fuel-air mixture to concentrate the flow.
  • the combustion temperature is regulated by an excess of combustion air through the burner.
  • the mixing behavior of a burner can now be characterized by the extent to which occurring ⁇ inhomogeneities in the burner are reduced before entering the combustion chamber. In the best case, one obtains a homogeneous profile with the A value of the associated global mixture.
  • the corresponding adiabatic combustion temperature of the global mixture may thus be considered to be the lower limit of the optimum maximum combustion temperature to be achieved, provided there is no additional heat extraction.
  • the degree of approximation to this ideal state characterizes the quality of mixing of each burner.
  • the invention has for its object to provide a burner with improved mixing behavior to reduce nitrogen oxide formation.
  • the burner according to the invention is defined by the patent claim 1. It has an inlet with a substantially rectangular cross-section, wherein two parallel walls define a clear width:
  • the mixing section forms a round channel whose width is greater than the clear width between the parallel walls, so that in the flow direction widening transition stages are formed.
  • transverse flows are initiated at the transition stages, by means of which the mixing process is greatly improved by increasing the turbulently diffuse transport and the induction of a convective secondary transport.
  • Rectangular channel and round channel are "inline", ie arranged on the same burner axis and form on their transition surface two mutually parallel stages (transition stages) .
  • the result is a convective-diffusive transport of the fuel-air mixture and a strong and uniform spread of the fuel in
  • the maximum fuel concentration at the outlet of the mixing section is low and the distribution of the fuel across the cross section of the mixing channel is improved, resulting in a reduction in thermal nitrogen oxide generation.
  • Transitional steps between square and circular cross sections induce the induction of four secondary vortices each rotate about a parallel to the burner axis, but radially offset, extending vortex axis. The rotations of adjacent secondary vortexes have opposite directions of rotation.
  • the dimension of the inlet is rectangular to the clear width greater than the width of the channel. This means that the inlet overhangs the round channel laterally.
  • the aspect ratio of the round channel-congruent portion of the face of the inlet should be about 2/3 of the area of the round channel.
  • the cross sections of the surface of the inlet and the surface of the round channel should be about the same size.
  • the ratio of the lengths of the mutually perpendicular sides of the inlet is preferably 2.5 to 3.5.
  • the inlet contains a fuel lance that ends at a distance in front of the mixing section.
  • FIG. 4 is a perspective view of the four forming in the mixing chamber and in this progressive secondary vortex
  • Fig. 5 is a representation of the flow vectors in a transverse plane of the round channel
  • Fig. 6 is an end view into the combustion chamber of a ring burner system with numerous burners.
  • the burner according to the figures 1-5 has an inlet 10, which consists of a tube of substantially rectangular cross-section.
  • the inlet 10 has two pairs of parallel walls.
  • a fuel lance 12 is arranged along the longitudinal axis of the inlet 10, which forms the burner axis 11, a fuel lance 12 is arranged. This consists of a tube of round cross-section.
  • the fuel I anze 12 is supplied with fuel 13, while the fuel lance 12 surrounding space of the inlet 10 is supplied with air 14.
  • As fuel for example, methane (CH 4 ) is used. Both the fuel and the air are supplied at high pressures.
  • the fuel lance 12 terminates at a distance in front of the outlet end 15 of the inlet 10.
  • a mixing section 20 connects.
  • This consists of a tube 21 of round cross section, which forms the channel.
  • the cylindrical tube 21 is arranged coaxially with the burner axis 17 and sealingly connected to the outlet end of the inlet 10.
  • the outlet end 22 of the mixing section 20 is open.
  • the mixing section opens here into a combustion chamber 23, in which a flame 24 is formed.
  • the inner diameter D of the tube 21 is greater than the clear width W of the inlet 10, which is defined by the mutual distance between two parallel walls of the inlet. Therefore, at each of the four parallel walls of the inlet 10 at the outlet end 15, a transition stage 25 is formed in which the respective side wall recedes in the flow path of the gas mixture.
  • the walls of the inlet 10 project beyond the contour of the channel 17 towards opposite sides.
  • the surfaces of the inlet 10 and of the channel 17 behave approximately as 1: 1.
  • the aspect ratio of the circular channel is The dimension W r of the inlet 10 at right angles to the clear width W is greater than the width D of the channel 17. This channel design results behind the outlet end 15 of the inlet 10 a radial pulse on the mixture flow.
  • a total of four vortices are distributed around the circumference in the mixing tube, which will be explained below.
  • the total length Ll of the inlet 10 is 14 mm and the length of the fuel lance 12 is 11 mm, so that the fuel lance ends at a distance of 3 mm in front of the outlet end 15.
  • the length of the mixing section 20 in this example is 30-40 mm.
  • FIGS. 4 and 5 show the flow conditions in the mixing section 20.
  • the air temperature is 720K, bringing the adiabatic flame temperature to about 1750K. With ideal, ie complete mixing, this results in a NO x emission of about 2 ppm.
  • the streamline profile in FIG. 5 shows that the flow from the rectangular inlet preferably flows into the region of the largest step height. In the further course of the flow in the mixing section this is compensated for continuity reasons by the formation of four axisymmetric secondary vortices Wl - W4.
  • A 8%
  • the secondary vortices Wl - W4 are each located in a quadrant of the cross section of the mixing section 20. The directions of rotation of two adjacent secondary vortices are opposite. The secondary vortex carries the fuel outwards and makes the fuel distribution even.
  • the transition stages 25 cause a
  • FIG. 6 shows an annular burner system, as used for example in stationary gas turbines.
  • Numerous burners B of the type described above are arranged in a ring, so that they are in a common Open combustion chamber 23.
  • the inlet 10 of the individual burner B are delimited from each other. They are curved to give the overall ring structure.
  • the burner according to the invention is particularly suitable for gas turbines both for energy production and in aircraft. But it can also be used for heating purposes.

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 brûleur doté d'une entrée (10) et d'un parcours de mélange (20) et configuré de telle sorte que l'entrée (10) présente une section transversale rectangulaire. Le parcours de mélange (20) qui s'y raccorde a une section transversale circulaire et un plus grand diamètre, de sorte que l'on forme quatre épaulements de transition (25). Les épaulements de transition (25) ont pour effet la formation de quatre tourbillons secondaires qui améliorent la répartition du combustible dans la direction radiale. Le brûleur a pour effet une combustion qui émet peu de substances nocives et peu d'oxyde d'azote.
EP08775346A 2007-08-04 2008-07-24 Brûleur Active EP2171354B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007036953A DE102007036953B3 (de) 2007-08-04 2007-08-04 Brenner
PCT/EP2008/059744 WO2009019140A2 (fr) 2007-08-04 2008-07-24 Brûleur

Publications (2)

Publication Number Publication Date
EP2171354A2 true EP2171354A2 (fr) 2010-04-07
EP2171354B1 EP2171354B1 (fr) 2012-06-20

Family

ID=40341804

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08775346A Active EP2171354B1 (fr) 2007-08-04 2008-07-24 Brûleur

Country Status (4)

Country Link
US (1) US8246345B2 (fr)
EP (1) EP2171354B1 (fr)
DE (1) DE102007036953B3 (fr)
WO (1) WO2009019140A2 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008032265B4 (de) 2008-07-09 2010-06-10 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verbrennungsvorrichtung
US9587823B2 (en) * 2009-03-25 2017-03-07 Wallace Horn Laminar flow jets
GB2533293A (en) * 2014-12-15 2016-06-22 Edwards Ltd Inlet assembly
FR3031771B1 (fr) * 2015-01-20 2017-03-03 Commissariat Energie Atomique Systeme de combustion presentant une tenue en temperature amelioree
PL422320A1 (pl) * 2017-07-24 2019-01-28 Instytut Lotnictwa Wtryskiwacz przebogaconej mieszanki paliwowo-powietrznej do komory spalania silników spalinowych
DE102021103800A1 (de) 2021-02-18 2022-08-18 Viessmann Climate Solutions Se Verfahren zum Betrieb eines Gasbrenners

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2352204B2 (de) * 1973-10-18 1976-01-22 Katec Katalytische Lufttechnik Betz & Co, 6461 Neuenhaßlau Verbrennungseinrichtung zur verbrennung von stoerstoffen in abgasen
US4383820A (en) * 1980-10-10 1983-05-17 Technology Application Services Corporation Fuel gas burner and method of producing a short flame
EP0463218B1 (fr) * 1990-06-29 1994-11-23 Joachim Dr.-Ing. Wünning Procédé et dispositif de combustion du combustible dans une chambre de combustion
DE4329237C2 (de) * 1993-08-24 1998-04-16 Ver Energiewerke Ag Verfahren und Anordnung zur Vergleichmäßigung der Staubbeladung eines Kohlenstaub-Trägergas-Gemischstromes im Kanal vor einem Kohlenstaubbrenner
JPH07260106A (ja) * 1994-03-18 1995-10-13 Hitachi Ltd 微粉炭燃焼バーナ及び微粉炭燃焼装置
US6383461B1 (en) * 1999-10-26 2002-05-07 John Zink Company, Llc Fuel dilution methods and apparatus for NOx reduction
US6383462B1 (en) * 1999-10-26 2002-05-07 John Zink Company, Llc Fuel dilution methods and apparatus for NOx reduction
US6367288B1 (en) * 1999-12-29 2002-04-09 Corning Incorporated Method and apparatus for preventing burner-hole build-up in fused silica processes
DE10128063A1 (de) * 2001-06-09 2003-01-23 Alstom Switzerland Ltd Brennersystem
US6652268B1 (en) * 2003-01-31 2003-11-25 Astec, Inc. Burner assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009019140A3 *

Also Published As

Publication number Publication date
DE102007036953B3 (de) 2009-04-02
US20110229836A1 (en) 2011-09-22
US8246345B2 (en) 2012-08-21
WO2009019140A2 (fr) 2009-02-12
EP2171354B1 (fr) 2012-06-20
WO2009019140A3 (fr) 2009-05-28

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