EP1856447B1 - Vormischbrenner zum betreiben einer brennkammer - Google Patents

Vormischbrenner zum betreiben einer brennkammer Download PDF

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Publication number
EP1856447B1
EP1856447B1 EP06708627.2A EP06708627A EP1856447B1 EP 1856447 B1 EP1856447 B1 EP 1856447B1 EP 06708627 A EP06708627 A EP 06708627A EP 1856447 B1 EP1856447 B1 EP 1856447B1
Authority
EP
European Patent Office
Prior art keywords
burner
burner shell
shell section
premix
section
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.)
Not-in-force
Application number
EP06708627.2A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1856447A1 (de
Inventor
Martin Andrea Von Planta
Christian Dr. Steinbach
Thomas Ruck
Weiqun Dr. Geng
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1856447A1 publication Critical patent/EP1856447A1/de
Application granted granted Critical
Publication of EP1856447B1 publication Critical patent/EP1856447B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23D14/02—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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • 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 producing an ignitable fuel-air mixture, with a swirl generator, which provides at least two supplementing to a flow body burner shells, each having a part cone shaped first burner shell portion and together define an axially conically widening swirl space, and the in axial longitudinal cone extension limit mutually tangential air inlet slots, passes through the combustion air supply into the swirl space, in which an axially spreading swirl flow is formed, and with means for injection of fuel, which are arranged at least partially along the tangential air inlet slots.
  • a swirl generator which provides at least two supplementing to a flow body burner shells, each having a part cone shaped first burner shell portion and together define an axially conically widening swirl space, and the in axial longitudinal cone extension limit mutually tangential air inlet slots, passes through the combustion air supply into the swirl space, in which an axially spreading swirl flow is formed, and with means for injection of fuel, which are arranged at least partially along the tangential air inlet slots.
  • Premix burners of the abovementioned type are known from a large number of published publications, for example, from EP 0 210 462 A1 as well as the EP 0 321 809 B1 , to name just a few.
  • Premix burners of this type is based on the general operating principle, within a mostly designed as a conical swirl generator, which provides at least two with corresponding overlap overlapping Operakegelschalen to produce a consisting of a fuel-air mixture swirl flow, which within a downstream of the premix burner combustion chamber under training a spatially stable as possible premix flame is made to ignite.
  • the spatial position of the premix flame is determined by the aerodynamic behavior of the swirl flow, whose swirl increases with increasing propagation along the burner axis, thus becomes unstable and ultimately bursting through an unsteady cross-sectional transition between the burner and combustion chamber in an annular swirling flow to form a remindströmzone, in whose front-flow area, the premix flame forms.
  • thermoacoustic oscillations or pulsations within the combustion system occur, which considerably affect the overall combustion and the heat release.
  • Vormischbrennersysteme be limited to sizes whose maximum burner diameter at the burner outlet is only 180 mm.
  • premix burners have a relatively sharp, i. small cone angle of less than or equal to 18 °, so that the burner length in relation to the down-turned burner diameter rather large, but for assembly and maintenance purposes is still quite manageable.
  • the partial cone shells intended for switching or deflecting the supply air into the swirl generator which are also referred to as burner bowls, are designed as thin-walled deflectors which have the shape of the lateral surface of conical halves or smaller conical segments and the swirl space on the radial side limit, the burner shells by their spatial arrangement each mutually tangential to the burner axis oriented air inlet slots with each other.
  • a burner for operating a heat generator can be seen, with a swirl generator whose oriented in the flow direction inlet cross-section is rectangular and for reasons of improved mixing downstream of a flow in the square or round flow cross-section provides, which is preferably followed by a cross-section round mixing section.
  • a swirl generator shown in perspective is shown, whose swirl space is bounded by curved burner shells 156 radially.
  • the burner shell or swirl blade 156 shown in cross-section has three burner shell sections, which are integrally connected to one another, wherein the respective partial cone-shaped first burner shell section is flush with a second burner shell section curved in the opposite direction to the first burner shell section and a third burner shell section adjoins the second burner shell section flush with a curvature tangential to the second burner shell section.
  • the invention has the object of developing a premix burner according to the features of the preamble of claim 1 such that despite enlarging the burner dimensions, the burner properties optimized in previously known premix burners should remain virtually unchanged.
  • it is necessary to solve the aerodynamic problems occurring in premix burners with multiple shell arrangements and to eliminate the associated disadvantages and dangers.
  • it is necessary to take measures that no reignition phenomena which cause gas accumulating in return flow zones occur.
  • the burner shells bounding the swirl space radially are burner bowls describing aerodynamically exclusively vanes that describe a partial conical shape, so that the supply air flow flowing through the air inlet slots into the swirl chamber is largely loss-free, i. without any edge vortex formation, between two the air inlet slot bounding burner shells is performed. Due to the burner shell geometry, which are formed in the usual way as a thin inlet air flow diverting baffles, a supply air flow flowing through the air inlet slots along a supply air flow facing surface of the burner shell is initially accelerated continuously as it enters the air inlet slot and gradually redirected until the air flow through the burner shell leaves to the swirl space.
  • the burner shell geometry has differently shaped, the air inlet slot laterally limiting surface areas through which the radially in the air inlet slot incoming air flow is largely without resistance and without formation of near-surface flow edge vortex in the swirl space to form an axially extending to the burner swirl flow is deflected.
  • any backflow zones which form in previously known premix burners with multi-shell arrangements can be avoided, in which gas accumulations can be formed, which can lead to damage to the premix burner structure and, in particular, to the burner shells by way of spontaneous deflagrations.
  • a burner shell designed in each case according to the invention has three burner shell sections of different shape, which are connected in one piece with each other, wherein the respective first conical cup section is flush with one opposite the first Burner cup portion curved second burner cup portion is added and a third burner cup portion is flush with the second burner cup portion, with a tangent to the second burner cup portion curvature.
  • the third burner shell section limits one side of each one of the tangential air inlet slots and provides a leading edge for the combustion air supply.
  • the determined by the partial cone shape curvature of the partially conical first burner shell section is continuous, ie transitionless, in the curvature of the second Brennerschalenabiteses and all places of a curvature change describe a line, the so-called inflection point line along which the means are provided for fuel injection.
  • such a trained burner shell can be produced in the context of a casting process or by way of a forming or material removal process.
  • FIG. 1 is a burner shell according to the invention formed schematically with a first burner shell section 1, which is described by the shell shape of a cone part.
  • a sub-segment 2 of a conical body is shown as an auxiliary construction, along the conical mantle surface 3 of the first burner shell section 1 conforms.
  • the first burner shell section 1 corresponds to the shape of those burner shells which have been in use up to now, the embodiments according to FIGS FIG. 1 longer trained side edge 4 of the trailing edge of the burner shell corresponds, as well as indicated by the polyline 5 leading edge of the burner shell section 1 of the leading edge corresponds to a previously common burner shell.
  • FIG. 1 shown burner shell along its curved upper side edge 6 and its lower side edge 7 attached for purposes of attachment to corresponding premix burner components.
  • the burner shell according to the invention provides two further burner shell sections 8, 9, which are seamless and integral to the line-shaped end region of the first, partially conical shape indicated by the line 5 connect the trained burner bowl section 1.
  • the second burner bowl section 8 immediately adjacent to the first burner bowl section 1 has a curvature that is oriented opposite to the curvature of the first part-cone-shaped burner shell section 1. From the graphical representation of the embodiment according to FIG. 1 it can be seen that the first burner shell section 1 is convex and the second and third burner shell sections 8, 9 are curved concavely to the plane of the drawing. In this case, the second burner shell section has the curvature of a quarter ellipse.
  • FIG. 1 To illustrate the concave curvature of the second burner shell section 8 is in FIG. 1 a prismatic body 10 shown, the second burner shell section 8 facing surface of the curvature corresponds to a quarter ellipse.
  • FIG. 1 illustrated sub-segment body 2 as well as the prismatic body 10 represent exclusively auxiliary body, which serve to better illustrate the geometric shape of the burner shell.
  • the third burner shell section which adjoins the virtually extending boundary line 11 of the second burner shell section 8, is flush, which provides a curvature which adjoins the second burner section tangentially.
  • the third burner shell section 9 essentially has a triangular-shaped basic shape with a front boundary edge 12, which at the same time also serves as the leading edge of the burner shell designed in accordance with the invention.
  • burner shell to a combination of a pure cone-shaped burner shell portion, a curved sheet with a Surface shape of a quarter ellipse and a tangential extension, which is represented by the third burner shell portion 9.
  • burner shell which is otherwise made of a heat-resistant sheet material and preferably along its entire surface extent has a substantially constant thickness, enclosing radially a portion of the conically extending swirl space of a premix burner.
  • the viewer of the in FIG. 1 shown burner shell facing surface is thus remote from the swirl space.
  • fuel line which serves for a fuel supply through each provided along the inflection point line 5 passage openings 13.
  • FIG. 2 shows an upper part of the solution according to trained burner shell.
  • the curvature behavior of the respective burner shell sections 1, 8 and 9 can be seen from the curvature profile of the uppermost side edge of the burner shell.
  • the third burner shell section 9 closes at the upper end of the burner shell under a acute angle to the second burner section 8 and extends substantially the curvature of the second burner shell section 8 at the location of the transition line 11 in a tangential continuation.
  • FIG. 2 are taken from the burner cup passing through openings 13, which are arranged along the inflection point line 5, is injected through the gaseous fuel.
  • FIG. 3 shows a three-dimensional view of a burner shell described above from a viewing angle, which shows the surface of the burner shell facing the swirl space.
  • a burner shell in plan view facing view is the FIG. 4 to be referred to in the following together with FIG. 3 Reference is made.
  • a stylized by the flow arrow radially incident on the leading edge 12 of the burner shell air flow L is accelerated in the third and second burner section 9, 8 in the flow direction and further deflected by the partially conical first burner shell section 1 successively until the flow L the burner shell over leaves the burner bowl section 1 towards the burner chamber or swirl space.
  • gaseous fuel is added through the openings 13 to the air flow L, resulting in an effective mixing of fuel and air already in this flow region.
  • the burner shell geometry according to the solution thus avoids any backflow zones within the air flow along the surface of the burner shell facing the air flow L.
  • the burner shell geometry is also designed such that the manufacture of the burner shells is possible without special tools, for example without special press-forming tools.
  • the shell geometry is always described by a family of straight lines, which are oriented axially or in the longitudinal extent of the burner shell, whereby the burner shell can be produced by means of a CNC bending machine.
  • FIG. 5 a premix burner is shown in three-dimensional representation, the eight an inner swirl space radially defining burner shells B, which are individually formed in the manner described above.
  • Two mutually adjacent burner shells B include an air inlet slot LS, through which an air flow can penetrate into the swirl space. It is obvious that the absorption capacity of the premix burner by providing eight individual air inlet slots LS is much greater than in the case of so-called double-cone burners in which only two partial cone shells limit the swirl space.
  • the individual burner shells B are firmly connected on the one hand with their upper boundary edge with a cylindrically shaped centrally arranged holding structure 15, through which means for axial fuel feed can be used in the axial direction.
  • the burner shells B are connected along their lower boundary edge with a mold element 16 through which the swirl flow forming within the swirl generator is transferred to a mixing tube (not further shown) or directly into a combustion chamber (not shown) for further mixing or ignition.
  • a mixing tube not further shown
  • a combustion chamber not shown
  • gaseous fuel is fed into the region of the air inlet slots LS through the linearly arranged openings 13 to form a fuel-air mixture.
EP06708627.2A 2005-03-09 2006-03-03 Vormischbrenner zum betreiben einer brennkammer Not-in-force EP1856447B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4092005 2005-03-09
PCT/EP2006/060437 WO2006094939A1 (de) 2005-03-09 2006-03-03 Vormischbrenner zum betreiben einer brennkammer

Publications (2)

Publication Number Publication Date
EP1856447A1 EP1856447A1 (de) 2007-11-21
EP1856447B1 true EP1856447B1 (de) 2014-09-24

Family

ID=34974801

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06708627.2A Not-in-force EP1856447B1 (de) 2005-03-09 2006-03-03 Vormischbrenner zum betreiben einer brennkammer

Country Status (5)

Country Link
US (1) US7632091B2 (zh)
EP (1) EP1856447B1 (zh)
CN (1) CN101137869A (zh)
AR (1) AR052687A1 (zh)
WO (1) WO2006094939A1 (zh)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006094939A1 (de) 2005-03-09 2006-09-14 Alstom Technology Ltd Vormischbrenner zum betreiben einer brennkammer
EP1985924A1 (en) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Swirler
EP2154428A1 (de) * 2008-08-11 2010-02-17 Siemens Aktiengesellschaft Brennstoffeinsatz
EP2685160B1 (en) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Premix burner of the multi-cone type for a gas turbine
RU2570989C2 (ru) 2012-07-10 2015-12-20 Альстом Текнолоджи Лтд Осевой завихритель для камеры сгорания газовой турбины
EP2685161B1 (en) * 2012-07-10 2018-01-17 Ansaldo Energia Switzerland AG Combustor arrangement, especially for a gas turbine
KR20150039763A (ko) * 2012-08-06 2015-04-13 지멘스 악티엔게젤샤프트 외부 영역에서 교차되는 블레이드 단부를 갖는 와류 발생기를 구비한 버너 내 공기와 연료 혼합물의 국부적 개선
EP2703721B1 (en) 2012-08-31 2019-05-22 Ansaldo Energia IP UK Limited Premix burner
EP2796789B1 (en) * 2013-04-26 2017-03-01 General Electric Technology GmbH Can combustor for a can-annular combustor arrangement in a gas turbine
US10782017B2 (en) 2018-04-24 2020-09-22 Trane International Inc. Wing vaned flame shaper

Family Cites Families (15)

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Publication number Priority date Publication date Assignee Title
US3217781A (en) * 1963-04-05 1965-11-16 Armco Steel Corp Gas mixer for blast furnace stoves
US4136565A (en) * 1978-04-20 1979-01-30 Eaton Corporation Variable geometry fluid flowmeter
EP0210462B1 (de) 1985-07-30 1989-03-15 BBC Brown Boveri AG Dualbrenner
CH674561A5 (zh) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
CH680946A5 (zh) * 1989-12-19 1992-12-15 Asea Brown Boveri
US5161946A (en) * 1990-12-03 1992-11-10 Industrial Technology Research Institute Swirl generator with axial vanes
DE4223828A1 (de) 1992-05-27 1993-12-02 Asea Brown Boveri Verfahren zum Betrieb einer Brennkammer einer Gasturbine
DE4412315B4 (de) 1994-04-11 2005-12-15 Alstom Verfahren und Vorrichtung zum Betreiben der Brennkammer einer Gasturbine
US5479773A (en) * 1994-10-13 1996-01-02 United Technologies Corporation Tangential air entry fuel nozzle
DE19516798A1 (de) * 1995-05-08 1996-11-14 Abb Management Ag Vormischbrenner mit axialer oder radialer Luftzuströmung
DE19654008B4 (de) * 1996-12-21 2006-08-10 Alstom Brenner
DE59710380D1 (de) * 1997-11-21 2003-08-07 Alstom Brenner für den Betrieb eines Wärmeerzeugers
DE19859829A1 (de) * 1998-12-23 2000-06-29 Abb Alstom Power Ch Ag Brenner zum Betrieb eines Wärmeerzeugers
CN1942710A (zh) * 2004-02-12 2007-04-04 阿尔斯通技术有限公司 用于操作燃烧室的预混和燃烧器装置和操作燃烧室的方法
WO2006094939A1 (de) 2005-03-09 2006-09-14 Alstom Technology Ltd Vormischbrenner zum betreiben einer brennkammer

Also Published As

Publication number Publication date
EP1856447A1 (de) 2007-11-21
US20080070176A1 (en) 2008-03-20
CN101137869A (zh) 2008-03-05
AR052687A1 (es) 2007-03-28
US7632091B2 (en) 2009-12-15
WO2006094939A1 (de) 2006-09-14

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