EP0956475B1 - Bruleur pour combustibles fluides - Google Patents

Bruleur pour combustibles fluides Download PDF

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Publication number
EP0956475B1
EP0956475B1 EP97951835A EP97951835A EP0956475B1 EP 0956475 B1 EP0956475 B1 EP 0956475B1 EP 97951835 A EP97951835 A EP 97951835A EP 97951835 A EP97951835 A EP 97951835A EP 0956475 B1 EP0956475 B1 EP 0956475B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
vortex element
air
duct
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.)
Expired - Lifetime
Application number
EP97951835A
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German (de)
English (en)
Other versions
EP0956475A2 (fr
Inventor
Gerwig Poeschl
Stefan Hoffmann
Ingo Ganzmann
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
Publication of EP0956475A2 publication Critical patent/EP0956475A2/fr
Application granted granted Critical
Publication of EP0956475B1 publication Critical patent/EP0956475B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • 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
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Definitions

  • the invention relates to a burner for fluid fuels, especially for use in a gas turbine plant.
  • a burner for fluid fuels such as the one in particular used in a gas turbine plant is from the DE 42 12 810 A1 known. From this it can be seen that air passes through an air supply ring duct system and fuel through another Ring channel system are fed to the combustion. there fuel is injected from the fuel duct into the air duct, either directly or from hollow blades Swirl blades.
  • this is to ensure that the mixture of Fuel and air can be reached to be a low nitrogen oxide
  • the lowest possible nitrogen oxide production is for reasons of environmental protection and corresponding legal guidelines for pollutant emissions an essential Combustion requirements, especially the Combustion in the gas turbine plant of a power plant.
  • the formation of nitrogen oxides increases exponentially with that Flame temperature of the combustion. With an inhomogeneous mixture there is a certain amount of fuel and air Distribution of flame temperatures in the combustion area. Determine the maximum temperatures of such a distribution after the exponential relationship of nitrogen oxide formation and flame temperature determine the amount of the formed Nitrogen oxides.
  • the combustion of a homogeneous fuel-air mixture therefore achieved at the same mean flame temperature lower nitrogen oxide emissions than combustion of an inhomogeneous mixture.
  • the cited publication is a good mix of air and fuel.
  • EP 561 591 A2 there is a rotating grid for production a turbulent flow for use in a burner, especially in a premix burner of a gas turbine, disclosed.
  • the rotating grille serves two concentric, generate oppositely rotating currents, so that in the inner flow during a partial load operation of the Gas turbine plant a reduced amount of fuel in one reduced air volume due to the division into two flows burned and thus stable combustion even in partial load operation can be maintained. It also creates Rotating grid directly adjacent to the rotating grid Backflow areas, the combustion areas for a stable Represent combustion.
  • EP 619 134 A1 discloses a mixing chamber for mixing Fabrics, e.g. in chemistry, food or pharmaceutical production.
  • the substances to be mixed are in separate channels swirled by a vortex generator and then merged.
  • the vortex generator is called elongated half pyramids trained deflection elements formed.
  • DE 44 15 916 A1 describes a method and a device for the combustion of a flowable fuel, in particular in the burner of a gas turbine.
  • a burner generating a turbulence is used, so that combustion air is swirled.
  • Combustion air is admitted fuel so that a particularly good mixture of fuel and Combustion air results.
  • the swirl is represented by a number achieved obtuse flow obstacles, in particular through bars or discs.
  • a swirl element called a static mixer is known from DE 41 23 161 A1. It exhibits a variety of in relation to the diameter of a pipeline or one Flow channel in which or in which it can be used, small Deflection elements on the axis of the flow channel or the pipe are inclined. The inclination of the in Rows aligned deflection elements is within one Row in the same direction and from row to row in opposite directions.
  • On such a swirling element covers a simply coherent Area, e.g. B. a circular or rectangular Cross-section. It serves to flow a medium through swirling the pipeline or flow channel a thorough mixing with one introduced into the medium Substance is available.
  • large swirl elements are also in EP 0 634 207 B1 and in WO 95/26226 A1 described. The main area of application of such Swirling elements are the nitrogen oxide reduction of flue gas by admixing ammonia in flow channels of typically a few square meters of cross-sectional area.
  • the object of the invention is to provide a burner for fluid Provide fuels that have a good mixture of combustion air and fuel at the same time, at most, at the least Impairment of other combustion parameters.
  • a major advantage of the invention is that the turbulent flow of the combustion air is a special one good mixture of combustion air and fuel can be achieved is, at the same time by the swirling element caused pressure loss is low. It is through the Mixture of fuel and combustion air in the turbulent Flow improved spatial homogeneity of the mixture achieved.
  • the temporal Fluctuation of the mixing ratio in extensive tests determined. Locally occurring fluctuations in time of the Mixing ratio, as well as the spatial inhomogeneities, to a distribution of the flame temperature the adverse effects on the Nitrogen oxide emission. The results of the tests showed that the fuel / air mixture generated a short time Fluctuation in the mixing ratio.
  • the swirling element is preferably designed such that that the turbulent flow of combustion air generated on Swirling element essentially no areas flowing back Combustion air has. So that is achieved that no ignitable fuel-air mixture to the swirling element can flow back and therefore no combustion is stabilized on the swirling element, causing damage of the swirling element could result.
  • the burner is preferably designed such that the outflow side from the swirling element swirl blades in the air duct are arranged. This ensures that a swirl element with the advantageous described above Effects on the homogeneity of the mixture of fuel and combustion air used in conjunction with swirl blades that is favorable to the stability of the combustion act.
  • At least one of the swirl blades is preferably a hollow blade trained from which fuel is admitted.
  • this configuration makes it possible to achieve uniform injection of fuel from a hollow vane Swirl blade with a further homogenizing effect on the fuel / air mixture in combination with the above advantages explained.
  • the burner as one Premix or hybrid burners for use in gas turbine plants, with an air supply duct, especially one itself tapering ring channel, which at least three more, in particular Ring channels arranged concentrically to the air supply channel for the supply of fluidic media, wherein two of these channels serve to supply a pilot burner and wherein a pilot flame is maintained by the pilot burner the combustion can be generated.
  • the connecting area is preferably less than half of those enclosed by the larger perimeter ring Circular area. Also preferred is the diameter of the larger limiting ring smaller than one meter, in particular 40 cm to 60 cm. This is the swirl element for use in small flow channels, e.g. Air ducts of gas turbine burners.
  • they are one Circle-associated deflection elements are equally spaced from one another. This creates one over the entire interface even turbulence achieved.
  • each deflecting element is made of the connection surface to a tear-off edge to produce Whirls rejuvenated. It preferably has trapezoidal or Triangular shape. This configuration makes it special intense turbulence reached.
  • FIG. 1 shows a hybrid burner 1 which is approximately rotationally symmetrical with respect to an axis 12.
  • a pilot burner 9 directed along the axis 12 with a fuel supply channel 8 and an air supply ring channel 7 concentrically surrounding it is surrounded concentrically by a fuel ring channel 3.
  • This fuel ring channel 3 is at the bottom, ie partially concentrically enclosed by an air supply ring channel 2.
  • a ring of swirl blades 5, which is shown schematically, is installed in this air supply ring channel 2. At least one of these swirl blades 5 is designed as a hollow blade 5a. It has an inlet 6 formed by a plurality of openings for a fuel supply.
  • the fuel ring channel 3 opens into this hollow blade 5a.
  • a swirling element 4 - shown schematically - is installed in the air duct 2.
  • the hybrid burner 1 can be used as a diffusion burner via the pilot burner 9 operate. But usually it is called Premix burners used, that means fuel and air are mixed first and then fed to the combustion.
  • the pilot burner 9 serves to maintain a pilot flame, the combustion during premix burner operation with a possibly changing fuel-air ratio stabilized.
  • Combustion air 10 and fuel 11 mixed in the air duct 2 and then fed to the combustion.
  • the fuel 11 from the fuel channel 3 in a hollow blade 5a of the swirl blade ring 5 passed and from there via the inlet 6 into the combustion air 10 initiated in the air duct 2.
  • FIG. 2 is a top view of a swirling element 4 shown.
  • Fig. 3 shows the same with the same reference numerals Swirling element 4 in a side view.
  • From an inner Limiting ring 52 lead evenly distributed over the ring circumference a plurality of webs 54 to an outer boundary ring 53.
  • the center of the outer perimeter ring 53 lies on the symmetry axis 59 of the inner limiting ring 52 and the webs 54 are normal to the inner limiting ring 52 directed.
  • the connecting surface 56 provides the lateral surface of a truncated cone between the inner boundary ring 52 and outer limiting ring 53.
  • On each Web 54 are trapezoidal, pointing into the interior of the truncated cone, flat deflection elements 51 arranged.
  • each deflection element 51 is connected to a web 4.
  • the deflection elements 51 are along three, to the axis of symmetry 59 concentric circles 55a, 55b, 55c to each other equally spaced.
  • the deflection elements 51 are inclined to a normal of the connecting surface 56, wherein each of the deflection elements 51 along a circle 55a, 55b, 55c in the same direction, from a circle 55a, 55b, 55c to one adjacent circle 55a, 55b, 55c inclined in opposite directions are.
  • a flow of combustion air through the swirling element 4 10, normal to the interface 56 in the interior of the truncated cone has the consequence that on the narrow sides 51b of the deflection elements 51 form vertebrae 57.
  • introduced fuel 11 is caused by this turbulence intensively mixed with the combustion air 10.
  • the inclination the deflection elements 51 also characterize the main flow secondary flows 58 in addition to the locally good Mixing the swirling homogenizes the mixture over the entire cross-sectional area of an air supply ring duct, in which the swirling element is installed (see Fig 1), enable.
  • the design of the swirling element 4 has the consequence that the by the Swirling pressure loss is low.

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  • 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 (1), notamment pour turbine à gaz, dans lequel l'air de combustion (10) est mis à tourbillonner dans un élément de tourbillonnement (4) et du combustible (11) est admis dans l'air de combustion (10) mis en tourbillonnement. Simultanément, la perte de pression due à l'élément de tourbillonnement (4) est minime. L'invention permet de parvenir à une émission réduite de NOx, tout en atteignant un rendement quasiment identique à celui de brûleurs classiques.

Claims (11)

  1. Brûleur (1) pour des combustibles fluides, destiné notamment à être utilisé dans une installation de turbine à gaz, comprenant un canal (2) d'air pour l'apport d'air (10) de combustion et un canal (3) de combustible pour l'apport de combustible (11), dans lequel il est prévu un élément (4) de tourbillonnement destiné à produire de l'air (10) de combustion très turbulent et, en aval de l'élément (4) de tourbillonnement, une entrée (6) de combustible (11) allant du canal (3) pour le combustible au canal (2) d'air, l'élément (4) de tourbillonnement comprenant :
    a) un premier anneau (52) de délimitation ayant un axe (59) de symétrie,
    b) un deuxième anneau (53) plus grand de délimitation, dont le centre est sur l'axe (59) de symétrie,
    c) une surface (56) de liaison qui est serrée par les deux anneaux (52, 53) de délimitation,
    d) le long de cercles (55a, 55b, 55c) se trouvant sur la surface (56) de liaison et dont les centres respectifs sont sur l'axe (59) de symétrie, une pluralité d'éléments (51) plats de déviation qui sont inclinés respectivement par rapport à une normale à la surface (6) de liaison.
  2. Brûleur (1) suivant la revendication 1, dans lequel l'élément (4) de tourbillonnement est constitué de façon que l'écoulement turbulent de l'air (10) de combustion qui peut être produit sur l'élément (4) de tourbillonnement ne comporte sensiblement pas de domaine où l'air (10) de combustion revient.
  3. Brûleur (1) suivant l'une des revendications précédentes, dans lequel il est monté en aval de l'élément (4) de tourbillonnement des aubes (5) de torsion dans le canal (2) d'air.
  4. Brûleur (1) suivant la revendication 3, dans lequel au moins l'une des aubes (5) de torsion est constituée en aube (5a) creuse à partir de laquelle du combustible (11) peut être admis.
  5. Brûleur (1) suivant l'une des revendications précédentes, qui est constitué en brûleur à prémélange ou hybride, destiné à être utilisé dans une installation de turbine à gaz, comprenant un canal (2) d'apport d'air, notamment un canal annulaire se rétrécissant, qui entoure au moins trois autres canaux annulaires disposés notamment concentriquement au canal (2) d'apport d'air et destinés à l'apport de milieux fluides, deux de ces canaux servant à l'alimentation d'un brûleur (9) pilote et une flamme pilote destinée à maintenir la combustion pouvant être produite par le brûleur (9) pilote.
  6. Brûleur (1) suivant l'une des revendications précédentes, dans lequel la surface (56) de liaison de l'élément (4) de tourbillonnement représente moins de la moitié de la surface circulaire entourée par l'anneau (53) le plus grand de délimitation.
  7. Brûleur (1) suivant l'une des revendications précédentes, dans lequel le diamètre de l'anneau (53) le plus grand de délimitation de l'élément (4) de tourbillonnement est plus petit qu'un mètre et mesure notamment entre 40 cm et 60 cm.
  8. Brûleur (1) suivant l'une des revendications précédentes, dans lequel les éléments (51) de déviation de l'élément (4) de tourbillonnement, qui sont associés à un cercle (55a, 55b, 55c) sont équidistants.
  9. Brûleur (1) suivant l'une des revendications précédentes, dans lequel chaque élément (51) de déviation de l'élément (4) de tourbillonnement se rétrécit de la surface (56) de liaison à un bord (51) de décollement pour la production de tourbillons (57), en ayant notamment une forme en trapèze ou en triangle.
  10. Brûleur (1) suivant l'une des revendications précédentes, dans lequel les éléments (51) de déviation de l'élément (4) de tourbillonnement, qui sont associés à un cercle (55a, 55b, 55c) sont inclinés dans le même sens.
  11. Brûleur (1) suivant la revendication 10, dans lequel des éléments (51) de déviation disposés sur des cercles (55a, 55b, 55c) voisins l'un de l'autre de l'élément (4) de tourbillonnement, sont inclinés en sens opposés.
EP97951835A 1996-12-20 1997-12-08 Bruleur pour combustibles fluides Expired - Lifetime EP0956475B1 (fr)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
DE19653474 1996-12-20
DE19653473 1996-12-20
DE19653473 1996-12-20
DE19653474 1996-12-20
PCT/DE1997/002858 WO1998028574A2 (fr) 1996-12-20 1997-12-08 Bruleur pour solides fluides, procede pour actionner un bruleur et element de tourbillonnement

Publications (2)

Publication Number Publication Date
EP0956475A2 EP0956475A2 (fr) 1999-11-17
EP0956475B1 true EP0956475B1 (fr) 2001-09-26

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EP97951835A Expired - Lifetime EP0956475B1 (fr) 1996-12-20 1997-12-08 Bruleur pour combustibles fluides

Country Status (5)

Country Link
US (1) US6189320B1 (fr)
EP (1) EP0956475B1 (fr)
JP (1) JP4127858B2 (fr)
DE (1) DE59704739D1 (fr)
WO (1) WO1998028574A2 (fr)

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WO2014114533A1 (fr) 2013-01-24 2014-07-31 Siemens Aktiengesellschaft Système de brûleur possédant des éléments de turbulence

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DE102012213852A1 (de) * 2012-08-06 2014-02-06 Siemens Aktiengesellschaft Lokale Verbesserung der Mischung von Luft und Brennstoff in Brennern mit Drallerzeugern
WO2015134009A1 (fr) * 2014-03-05 2015-09-11 Siemens Aktiengesellschaft Moteur à turbine à gaz avec système de mélange statique de flux d'échappement de compresseur
WO2015134010A1 (fr) * 2014-03-05 2015-09-11 Siemens Aktiengesellschaft Système de mélange statique de flux d'admission de chambre de combustion pour conditionner l'air introduit dans la chambre de combustion d'un moteur à turbine à gaz
EP3081862B1 (fr) * 2015-04-13 2020-08-19 Ansaldo Energia Switzerland AG Agencement de génération de vortex pour un brûleur à pré-mélange d'une turbine à gaz et turbine à gaz avec un tel agencement de génération de vortex
CN109237514B (zh) * 2018-08-08 2024-02-23 中国华能集团有限公司 一种用于燃气轮机的双管路气体燃料燃烧器
CN117212837B (zh) * 2022-06-02 2026-03-06 中国航发商用航空发动机有限责任公司 燃气涡轮发动机及用于其的混合器组件、燃烧室、燃料雾化方法
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CN119123424B (zh) * 2024-10-31 2025-10-03 合肥综合性国家科学中心能源研究院(安徽省能源实验室) 一种采用废气再循环预热的分级助氨燃烧器

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WO2006040269A1 (fr) * 2004-10-11 2006-04-20 Siemens Aktiengesellschaft Bruleur destine a la combustion d'un gaz combustible a faible pouvoir calorifique et procede pour faire fonctionner un bruleur
CN101040149B (zh) * 2004-10-11 2010-06-16 西门子公司 用于燃烧低热值燃气的燃烧器和燃烧器的工作方法
WO2014114533A1 (fr) 2013-01-24 2014-07-31 Siemens Aktiengesellschaft Système de brûleur possédant des éléments de turbulence

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JP2001507115A (ja) 2001-05-29
WO1998028574A2 (fr) 1998-07-02
JP4127858B2 (ja) 2008-07-30
EP0956475A2 (fr) 1999-11-17
US6189320B1 (en) 2001-02-20
WO1998028574A3 (fr) 1998-09-17
DE59704739D1 (de) 2001-10-31

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