EP1856447A1 - Burner comprising a premix for combustion chamber - Google Patents
Burner comprising a premix for combustion chamberInfo
- Publication number
- EP1856447A1 EP1856447A1 EP06708627A EP06708627A EP1856447A1 EP 1856447 A1 EP1856447 A1 EP 1856447A1 EP 06708627 A EP06708627 A EP 06708627A EP 06708627 A EP06708627 A EP 06708627A EP 1856447 A1 EP1856447 A1 EP 1856447A1
- 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.)
- Granted
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 19
- 239000000446 fuel Substances 0.000 claims abstract description 16
- 239000000203 mixture Substances 0.000 claims abstract description 5
- 239000000463 material Substances 0.000 claims description 4
- 241000237942 Conidae Species 0.000 claims description 3
- 230000008859 change Effects 0.000 claims description 3
- 230000001154 acute effect Effects 0.000 claims description 2
- 238000002347 injection Methods 0.000 claims description 2
- 239000007924 injection Substances 0.000 claims description 2
- 230000007480 spreading Effects 0.000 claims description 2
- 238000003892 spreading Methods 0.000 claims description 2
- 229910000831 Steel Inorganic materials 0.000 claims 1
- 239000007769 metal material Substances 0.000 claims 1
- 238000000926 separation method Methods 0.000 claims 1
- 239000010959 steel Substances 0.000 claims 1
- 239000013589 supplement Substances 0.000 claims 1
- 230000000295 complement effect Effects 0.000 abstract 1
- 239000000243 solution Substances 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 230000035508 accumulation Effects 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009172 bursting Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 230000001502 supplementing effect Effects 0.000 description 1
- 238000012549 training Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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 and EP 0 321 809 B1, to name only a few.
- Vormischbrennem this type is based on the general principle of action, 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 deflector plates, which have the shape of the lateral surface of conical halves or smaller conical segments, and radially on the swirl space limit, the burner shells by their spatial arrangement each mutually tangential to the burner axis oriented air inlet slots with each other.
- the invention has the object of developing a premix burner according to the features of the preamble of claim 1 such that, despite increasing the burner dimensions, the burner properties optimized in previously known premix burners should remain virtually unchanged. Thus, it is necessary to solve the aerodynamic problems occurring in premix burners with multiple shell arrangements and to eliminate the associated disadvantages and dangers.
- the burner shells bounding the swirl space are formed aerodynamically in difference or rather in extension to the burner shells previously in use, exclusively by a partial conical shape such that the incoming air stream flowing through the air inlet slots into the swirl space is largely loss-free, ie without any edge vortex formation two burner shells bounding the air inlet slot are guided.
- the burner shell geometry which are formed in the usual manner as thin the supply air diverting baffles, a supply air flow passing through the air inlet slots along a supply air flow facing surface of the burner shell is initially accelerated continuously on entry into the air inlet slot and gradually redirected until the air flow Burner bowl leaves towards the swirl chamber.
- the burner shell geometry thus has in contrast to previous burner shells differently shaped, the air inlet slot laterally limiting surface areas through which the radially in the air inlet slot incoming air flow is deflected 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 ,
- any backflow zones which form in previously known premix burners with multiple-shell arrangements can be avoided, in which gas accumulations can be formed which can cause damage to the premix burner structure and, in particular, to the burner bowls by means of spontaneous deflagrations.
- a burner shell designed in each case according to the invention has three burner shell sections of different shape, 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 cup portion.
- 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.
- 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.
- a casting process or by way of a forming or material removal process.
- 1 is a schematic perspective view of a solution according to trained burner shell
- FIG. 2 detailed representation of a portion of the quarter-elliptical shaped
- Burner bowl area with adjacent tangentially extended triangular burner bowl area Burner bowl area with adjacent tangentially extended triangular burner bowl area
- FIG. 3 shows a 3D illustration of a burner shell designed in accordance with the invention
- FIG. 4 shows a burner shell in accordance with the invention.
- FIG. 5 3D representation of a swirl generator with multi-shell arrangement.
- FIG. 1 shows schematically a burner shell formed in accordance with the invention with a first burner shell section 1 which can be described by the shell shape of a partial cone.
- 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 used hitherto, wherein the longer side edge 4 in the embodiment according to FIG. 1 corresponds to the trailing edge of the burner shell, as well as the line 5 indicated front edge of the burner shell section 1 of the leading edge corresponds to a previously common burner shell.
- the burner shell shown in Figure 1 is secured along its curved upper side edge 6 and its lower side edge 7 for their attachment to respective 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 adjoining the first burner bowl section 1 has a curvature which is oriented opposite to the curvature of the first partially cone-shaped burner bowl section 1. It can be seen from the graphical representation of the embodiment according to FIG. 1 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.
- a prismatic body 10 is shown in FIG. 1 whose surface facing the second burner shell section 8 corresponds to the curvature of a quarter ellipse.
- both the partial segment body 2 shown in FIG. 1 and also the prismatic body 10 exclusively represent auxiliary bodies which serve to better illustrate the geometric shape of the burner shell.
- the curvature and shape of the second burner shell section form, for example, based on a quarter circle segment or on a similar to the quarter ellipse or quarter circle ajar curved shape.
- 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 shown in Figure 1 is a combination of a pure cone-shaped burner shell portion, a curved surface body with a surface shape of a quarter ellipse and a tangential to extension, which is represented by the third burner shell section 9.
- the burner shell shown in Figure 1 which is otherwise made of a heat-resistant sheet material and preferably along its entire surface extent has a substantially constant thickness, radially encloses a portion of the conically extending swirl space of a premix burner.
- the surface facing the viewer of the burner shell shown in Figure 1 is thus remote from the swirl space.
- facing away from the swirl surface surface is not shown in Figure 1
- Figure 2 shows an upper part of the burner cup according to the invention.
- 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 adjoins the second burner section 8 at the upper end of the burner shell at an acute angle and substantially expands the curvature of the second burner shell section 8 at the location of the transitional line 11 in a tangential continuation.
- FIG. 2 shows the openings 13 passing through the burner bowl, which are arranged along the point of inflection 5, through which gaseous fuel is injected.
- 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.
- the openings 13 are arranged, protrude through the fuel nozzles, which are connected to a fuel line 14, which is remote from the swirl space attached to the burner shell.
- FIG. 4 A representation showing the burner shell in plan view can be taken from FIG. 4, to which reference is made in the following together with FIG.
- a stylized by the flow arrow shown radially incident on the leading edge 12 of the burner cup air flow L is in the range of the third and The second burner section 9, 8 accelerated in the flow direction and subsequently deflected successively by the partially conically shaped first burner bowl section 1 until the flow L leaves the burner bowl via 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 shows a three-dimensional illustration of a premix burner, which has eight burner shells B which bound radially inwardly an internal swirl space and which are individually shaped 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 along its lower boundary edge connected to a mold element 16, by which the forming within the swirl generator swirl flow is transferred into a not further shown mixing tube or directly into a combustion chamber not shown for further mixing or ignition.
- a mold element 16 By way of the fuel lines 14 arranged concealed on the burner shells in the flow direction through the respective second and third burner shell sections, 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.
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH4092005 | 2005-03-09 | ||
PCT/EP2006/060437 WO2006094939A1 (en) | 2005-03-09 | 2006-03-03 | Burner comprising a premix for combustion chamber |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1856447A1 true EP1856447A1 (en) | 2007-11-21 |
EP1856447B1 EP1856447B1 (en) | 2014-09-24 |
Family
ID=34974801
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06708627.2A Not-in-force EP1856447B1 (en) | 2005-03-09 | 2006-03-03 | Burner comprising a premix for combustion chamber |
Country Status (5)
Country | Link |
---|---|
US (1) | US7632091B2 (en) |
EP (1) | EP1856447B1 (en) |
CN (1) | CN101137869A (en) |
AR (1) | AR052687A1 (en) |
WO (1) | WO2006094939A1 (en) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2006094939A1 (en) | 2005-03-09 | 2006-09-14 | Alstom Technology Ltd | Burner comprising a premix for combustion chamber |
EP1985924A1 (en) * | 2007-04-23 | 2008-10-29 | Siemens Aktiengesellschaft | Swirler |
EP2154428A1 (en) * | 2008-08-11 | 2010-02-17 | Siemens Aktiengesellschaft | Fuel nozzle insert |
EP2685161B1 (en) * | 2012-07-10 | 2018-01-17 | Ansaldo Energia Switzerland AG | Combustor arrangement, especially for a gas turbine |
RU2570989C2 (en) * | 2012-07-10 | 2015-12-20 | Альстом Текнолоджи Лтд | Gas turbine combustion chamber axial swirler |
EP2685160B1 (en) * | 2012-07-10 | 2018-02-21 | Ansaldo Energia Switzerland AG | Premix burner of the multi-cone type for a gas turbine |
RU2633475C2 (en) * | 2012-08-06 | 2017-10-12 | Сименс Акциенгезелльшафт | Local improvement of air and fuel mixing in burners supplied with swirlers with blade ends crossed at outer area |
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)
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 |
DE3662462D1 (en) | 1985-07-30 | 1989-04-20 | Bbc Brown Boveri & Cie | Dual combustor |
CH674561A5 (en) | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
CH680946A5 (en) * | 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 (en) | 1992-05-27 | 1993-12-02 | Asea Brown Boveri | Method for operating a combustion chamber of a gas turbine |
DE4412315B4 (en) | 1994-04-11 | 2005-12-15 | Alstom | Method and device for operating the combustion chamber of a gas turbine |
US5479773A (en) * | 1994-10-13 | 1996-01-02 | United Technologies Corporation | Tangential air entry fuel nozzle |
DE19516798A1 (en) * | 1995-05-08 | 1996-11-14 | Abb Management Ag | Premix burner with axial or radial air flow |
DE19654008B4 (en) * | 1996-12-21 | 2006-08-10 | Alstom | burner |
DE59710380D1 (en) * | 1997-11-21 | 2003-08-07 | Alstom | Burner for operating a heat generator |
DE19859829A1 (en) * | 1998-12-23 | 2000-06-29 | Abb Alstom Power Ch Ag | Burner for operating a heat generator |
WO2005078348A1 (en) * | 2004-02-12 | 2005-08-25 | Alstom Technology Ltd | Premixing burner arrangement for operating a burner chamber and method for operating a burner chamber |
WO2006094939A1 (en) | 2005-03-09 | 2006-09-14 | Alstom Technology Ltd | Burner comprising a premix for combustion chamber |
-
2006
- 2006-03-03 WO PCT/EP2006/060437 patent/WO2006094939A1/en not_active Application Discontinuation
- 2006-03-03 EP EP06708627.2A patent/EP1856447B1/en not_active Not-in-force
- 2006-03-03 CN CNA2006800072624A patent/CN101137869A/en active Pending
- 2006-03-09 AR ARP060100894A patent/AR052687A1/en unknown
-
2007
- 2007-09-06 US US11/850,849 patent/US7632091B2/en active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2006094939A1 * |
Also Published As
Publication number | Publication date |
---|---|
US20080070176A1 (en) | 2008-03-20 |
CN101137869A (en) | 2008-03-05 |
WO2006094939A1 (en) | 2006-09-14 |
AR052687A1 (en) | 2007-03-28 |
EP1856447B1 (en) | 2014-09-24 |
US7632091B2 (en) | 2009-12-15 |
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