WO2005078348A1 - Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion - Google Patents

Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion Download PDF

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Publication number
WO2005078348A1
WO2005078348A1 PCT/EP2005/050579 EP2005050579W WO2005078348A1 WO 2005078348 A1 WO2005078348 A1 WO 2005078348A1 EP 2005050579 W EP2005050579 W EP 2005050579W WO 2005078348 A1 WO2005078348 A1 WO 2005078348A1
Authority
WO
WIPO (PCT)
Prior art keywords
wall
flow
premix burner
swirl
burner according
Prior art date
Application number
PCT/EP2005/050579
Other languages
German (de)
English (en)
Inventor
Elena De Marcos
Christian Steinbach
Nicolas Ulibarri
Martin Andrea Von Planta
Original Assignee
Alstom Technology Ltd
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 Alstom Technology Ltd filed Critical Alstom Technology Ltd
Priority to BRPI0507640-4A priority Critical patent/BRPI0507640A/pt
Priority to CA002555481A priority patent/CA2555481A1/fr
Priority to EP05726413A priority patent/EP1714081B1/fr
Priority to MXPA06008994A priority patent/MXPA06008994A/es
Priority to DE502005003648T priority patent/DE502005003648D1/de
Publication of WO2005078348A1 publication Critical patent/WO2005078348A1/fr
Priority to US11/503,163 priority patent/US20070042307A1/en

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
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • 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
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the invention relates to a premix burner for operating a combustion chamber with a gaseous and / or liquid fuel with a swirl generator for a combustion supply air flow to form a swirl flow and means for injecting fuel into the swirl flow, the swirl generator having at least two partial cone shells which complement one another to form a flow body which together enclose a conical swirl chamber with a cone angle y and tangential air inlet slots in the longitudinal direction of the cone.
  • Premix burners of the aforementioned type are known from a large number of previously published documents, for example from EP 0210462 A1 and EP 0 321 809 B1, to name just a few.
  • Premix burners of this type are based on the general principle of operation, within a swirl generator, which is usually designed as a cone and which provides at least two partial cone shells with corresponding mutual overlap, to produce a swirl flow consisting of a fuel-air mixture, which is formed within a combustion chamber following the premix burner under formation a premixing flame which is as stable as possible is ignited becomes.
  • the spatial position of the premixing flame is determined by the aerodynamic behavior of the swirl flow, the swirl number of which increases with increasing propagation along the burner axis, so that it becomes unstable and ultimately bursts due to an unstable cross-sectional transition between burner and combustion chamber into an annular swirl flow with the formation of a backflow zone in the latter , the premixing flame forms in the direction of flow at the front.
  • the aerodynamic stability of the backflow zone that forms is of particular importance, but depends in a highly sensitive manner on the design, shape and size of the swirl generator. If, for example, it is not possible to spatially stabilize the foremost front of the backflow zone that is formed in the direction of flow, thermoacoustic oscillations or pulsations occur increasingly within the combustion system, which significantly impair the entire combustion and the heat release.
  • premix burner systems are limited to sizes whose maximum burner diameter at the burner outlet is only 180 mm.
  • Such premix burners also have a relatively pointed, i.e. small cone angle of less than or equal to 18 °, so that the burner length is rather large in relation to the downstream burner diameter, but is still quite manageable for assembly and maintenance purposes.
  • multiple burner arrangements have been used so far, which provide for the use of the above premix burners.
  • Such multiple burner arrangements can be found, for example, in DE 4223 828 A1 or DE 44 12 315 A1.
  • a sophisticated arrangement of the large number of premix burners, each serving as a main or pilot burner is required in order to ultimately be able to operate the combustion chamber with the lowest possible emission values in the entire load range.
  • Premix burner arrangements are also known (for example US 5,588,826) which, in contrast to the premix burner described above, have a transition geometry interposed between the swirl generator and the combustion chamber, for example in the form of a hollow cylindrical mixing tube.
  • transition geometries are extremely aerodynamically sensitive, since flow separations in this zone can lead to a flashback or self-ignition.
  • Such transition geometries also make a decisive contribution to the production costs due to their complex production.
  • the invention is based on the object of developing a premix burner in accordance with the features of the preamble of claim 1 in such a way that, despite enlarging the burner dimensions, the burner properties which have been optimized in previously known premix burners are to be maintained almost unchanged. It is therefore necessary to increase the burner size of previously known premix burner systems in order to reduce the number of burners in multiple burner arrangements, as described at the beginning, and also to reduce the system costs associated therewith. It should also be possible with the larger premix burner systems to replace previously known diffusion single burners, such as those used for firing silo combustion chambers, by a single premix burner.
  • a premix burner is developed in such a way that, at least at the downstream end region of the swirl generator, a shaped element enclosing the partial cone shells with a Partial conical shells facing inner wall is provided, and that the partial conical shells run out flush with the shape of the inner wall.
  • shape-preserving means that the part-conical shape of the partial cone shells remains unchanged in the region of contact with the inner wall of the shaped element surrounding the partial cone shells, as if the partial cone shells penetrated the shaped element radially outward unhindered.
  • the inner wall of the shaped element also serves to form a flow channel downstream of the partial cone shells.
  • this is also used as a mixing tube or as a joining element, in the sense of a flange piece, by means of which the swirl generator is connected to an in Direction of flow downstream combustion chamber, such as a silo combustion chamber, or another channel structure can be connected.
  • cone angles of at least 11 °, but preferably in the range of 20 ° and larger are used, under which the partial cone shells surround the swirl space in a conically widening manner. This enables burners with a burner diameter in the outlet area of, for example, greater than 500 mm to be made possible, which have a burner length well below one meter.
  • FIG. 5 sectional view through a premix burner with a frustoconical shaped element
  • FIG. 6 + 7 perspective view of a premix burner with a funnel-shaped inlet area having a shaped element.
  • FIGS. 1 and 2 show a perspective illustration of a premix burner, looking in the direction from the downstream side into the swirl space of a swirl generator 2 spanned by a plurality of partial cone shells 1.
  • 2 shows the same premix burner, but from a different angle, namely from the outside onto the swirl generator 2, which is spanned by eight partial cone shells 1 in the exemplary embodiment shown.
  • the further external guides with respect to the exemplary embodiment shown in FIGS. 1 and 2 are made uniformly, so that no further distinction is made between FIGS. 1 and 2.
  • the premix burner shown has a central receiving unit 3, which is designed in the form of a receiving sleeve and is provided for inserting and holding a central fuel supply unit, for example in the form of a fuel nozzle for liquid fuels or a fuel lance for a pilot flame (not shown).
  • the partial cone shells 1 connected with their upstream ends to the receiving unit 3 mutually enclose air inlet slots 4 and are positioned relative to a burner axis A running centrally through the premix burner in such a way that they limit a swirl space that widens conically in the direction of flow at a cone angle y.
  • Each individual partial cone shell 1 also has, depending on the type of fuel, at least one fuel feed line 5, via which fuel can be mixed into the combustion air supply stream passing through the air inlet slots 2.
  • the individual partial cone shells 1 open with their downstream end to maintain shape on an inner wall 6 of a cylindrical shaped element 7 surrounding the partial conical shells 1.
  • the individual partial cone shells 1 are connected to the inner wall 6 of the shaped element 7 along a cutting line 8, which is defined by a virtual penetration each individual partial cone shell 1 with the inner wall 6 of the cylindrical shaped element 7 results.
  • the swirl flow formed in the interior of the swirl generator 2 does not experience any disturbance after overflowing the individual partial cone shells 1.
  • a second shaped element 9 is provided, which is also hollow-cylindrical and has a larger inner diameter than the first shaped elements 7.
  • the inner diameter transition between the shaped elements 7 and 9 takes place via a discontinuous stage 10, on which the fuel supply lines 5 of each individual partial cone shell 1 adjoin.
  • the downstream contour of the shaped element 7 is cylindrical and offers the possibility of a structurally simple connection, for example with a combustion chamber (not shown) arranged according to the premix burner shown in the flow direction.
  • FIGS. 3 and 4 show a perspective view of a further embodiment of a premix burner designed according to the invention, in which, in contrast to the embodiment shown in FIGS. 1 and 2, the area of the shaped element 7 as a truncated cone section which tapers conically in the direction of flow is trained.
  • the exemplary embodiment shown in FIGS. 3 and 4 has in the region of the shaped element 7 an inner wall 6 shown hatched in the perspective representations, on which the downstream ends of the partial cone shells 1 adjoin in a shape-maintaining manner.
  • FIGS. 6 and 7 show a further exemplary embodiment of a premix burner with a shaped element 7 which provides an upstream region, the so-called inflow region 12, which has an inner wall 6 which tapers in the direction of the flow in a funnel shape.
  • the curvature of the inner wall 6 in this inflow region 12 corresponds approximately to the contour of a quarter ellipse.
  • a flow region 12 ′ adjoins within the frame of the shaped element 7 with a largely constant flow cross section, to which an inlet flange of a combustion chamber can ultimately be attached (not shown).
  • the partial cone shells 1 of the swirl generator 2 run flush with the adjacent inner wall 6 of the shaped element 7 while maintaining their partial cone shell shape, as if the partial cone shells penetrated the inner wall 6 unhindered, but the partial cone shells 1 each connect via the cutting lines 8 the inner wall 6 from.
  • the downstream end regions of the partial cone shells 1 nestle against the ellipse curvature of the inner wall 6 in this region 12.
  • each individual partial cone shell with its downstream end region maintaining shape with an inner wall of a shaped element surrounding the partial cone shells leads to the slightest irritation of the swirl flow passing through the partial cone shells.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Feeding And Controlling Fuel (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

La présente invention concerne un brûleur de prémélange qui sert à faire fonctionner une chambre de combustion avec un combustible gazeux et/ou liquide, ledit brûleur comprenant un générateur de tourbillon (2) destiné à produire un tourbillon à partir d'un courant d'apport d'air de combustion, et des éléments (5) pour injecter du carburant dans le tourbillon. Selon l'invention, le générateur de tourbillon (2) présente au moins deux coques en forme de cône primitif (1) qui se complètent pour former un corps de circulation et qui ensemble renferment un espace de tourbillon de forme conique ayant un angle de cône (ξ) et présentant des encoches d'entrée d'air (4) tangentielles à la direction longitudinale du cône. L'invention se caractérise en ce qu'un élément profilé (7) qui entoure les coques en forme de cône primitif (1) et présente une paroi interne (6) dirigée vers les coques en forme de cône primitif (1), est présent au moins au niveau de la partie d'extrémité aval du générateur de tourbillon (2), et en ce que les coques en forme de cône primitif (1) viennent à fleur de la paroi interne (6), de façon indéformable.
PCT/EP2005/050579 2004-02-12 2005-02-09 Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion WO2005078348A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
BRPI0507640-4A BRPI0507640A (pt) 2004-02-12 2005-02-09 arranjo de queimador de pré-mistura para operar uma cámara de combustão e método para operar a cámara de combustão
CA002555481A CA2555481A1 (fr) 2004-02-12 2005-02-09 Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion
EP05726413A EP1714081B1 (fr) 2004-02-12 2005-02-09 Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion
MXPA06008994A MXPA06008994A (es) 2004-02-12 2005-02-09 Arreglo de quemador de premezclado para operar una camara de combustion y metodo para operar una camara de combustion.
DE502005003648T DE502005003648D1 (de) 2004-02-12 2005-02-09 Vormischbrenneranordnung zum betreiben einer brennkammer sowie verfahren zum betreiben einer brennkammer
US11/503,163 US20070042307A1 (en) 2004-02-12 2006-08-14 Premix burner arrangement for operating a combustion chamber and method for operating a combustion chamber

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH00210/04 2004-02-12
CH2102004 2004-02-12

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US11/503,163 Continuation US20070042307A1 (en) 2004-02-12 2006-08-14 Premix burner arrangement for operating a combustion chamber and method for operating a combustion chamber

Publications (1)

Publication Number Publication Date
WO2005078348A1 true WO2005078348A1 (fr) 2005-08-25

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PCT/EP2005/050579 WO2005078348A1 (fr) 2004-02-12 2005-02-09 Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion

Country Status (10)

Country Link
US (1) US20070042307A1 (fr)
EP (1) EP1714081B1 (fr)
CN (1) CN1942710A (fr)
AT (1) ATE391887T1 (fr)
BR (1) BRPI0507640A (fr)
CA (1) CA2555481A1 (fr)
DE (1) DE502005003648D1 (fr)
MX (1) MXPA06008994A (fr)
MY (1) MY141577A (fr)
WO (1) WO2005078348A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006094939A1 (fr) * 2005-03-09 2006-09-14 Alstom Technology Ltd Bruleur a premelange pour une chambre de combustion
US9400105B2 (en) 2012-08-31 2016-07-26 General Electric Technology Gmbh Premix burner
EP4089325A1 (fr) * 2021-05-12 2022-11-16 Martin GmbH für Umwelt- und Energietechnik Buse d'injection de gaz dans une installation de combustion dotée d'un tube et d'un générateur tourbillons, conduit de gaz de fumée doté d'une telle buse et procédé d'utilisation d'une telle buse

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ATE479054T1 (de) * 2005-03-09 2010-09-15 Alstom Technology Ltd Vormischbrenner zum erzeugen eines zündfähigen brennstoff-luftgemisches
DE102007043626A1 (de) 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität
CN101709884B (zh) * 2009-11-25 2012-07-04 北京航空航天大学 一种预混预蒸发燃烧室
TW201229437A (en) * 2011-01-11 2012-07-16 Pro Iroda Ind Inc Device for increasing flame height
TW201303226A (zh) * 2011-07-06 2013-01-16 Pro Iroda Ind Inc 具升降裝置之火焰組
CN104185763B (zh) * 2012-03-29 2017-03-08 通用电器技术有限公司 燃气涡轮燃烧器
US8813967B2 (en) * 2012-05-02 2014-08-26 Alstom Technology Ltd Adjustable mill classifier
EP2685163B1 (fr) * 2012-07-10 2020-03-25 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
EP2685161B1 (fr) * 2012-07-10 2018-01-17 Ansaldo Energia Switzerland AG Agencement de chambre de combustion, en particulier pour turbine à gaz
EP2685160B1 (fr) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
RU2570989C2 (ru) 2012-07-10 2015-12-20 Альстом Текнолоджи Лтд Осевой завихритель для камеры сгорания газовой турбины
US20150153066A1 (en) * 2013-12-04 2015-06-04 Victory Energy Operations. L.L.C. Method of providing heat to a heat exchanger apparatus via a burner

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WO2006094939A1 (fr) * 2005-03-09 2006-09-14 Alstom Technology Ltd Bruleur a premelange pour une chambre de combustion
US7632091B2 (en) 2005-03-09 2009-12-15 Alstom Technology Ltd. Premix burner for operating a combustion chamber
US9400105B2 (en) 2012-08-31 2016-07-26 General Electric Technology Gmbh Premix burner
EP4089325A1 (fr) * 2021-05-12 2022-11-16 Martin GmbH für Umwelt- und Energietechnik Buse d'injection de gaz dans une installation de combustion dotée d'un tube et d'un générateur tourbillons, conduit de gaz de fumée doté d'une telle buse et procédé d'utilisation d'une telle buse

Also Published As

Publication number Publication date
CA2555481A1 (fr) 2005-08-25
DE502005003648D1 (de) 2008-05-21
ATE391887T1 (de) 2008-04-15
EP1714081A1 (fr) 2006-10-25
MY141577A (en) 2010-05-14
BRPI0507640A (pt) 2007-07-10
CN1942710A (zh) 2007-04-04
EP1714081B1 (fr) 2008-04-09
US20070042307A1 (en) 2007-02-22
MXPA06008994A (es) 2006-12-14

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