EP1510755A1 - Brûleur avec lance et alimentation étagée en carburant - Google Patents
Brûleur avec lance et alimentation étagée en carburant Download PDFInfo
- Publication number
- EP1510755A1 EP1510755A1 EP04104099A EP04104099A EP1510755A1 EP 1510755 A1 EP1510755 A1 EP 1510755A1 EP 04104099 A EP04104099 A EP 04104099A EP 04104099 A EP04104099 A EP 04104099A EP 1510755 A1 EP1510755 A1 EP 1510755A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- fuel
- combustion air
- fuel outlet
- swirl
- 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
- 239000000446 fuel Substances 0.000 title claims abstract description 140
- 238000002485 combustion reaction Methods 0.000 claims description 50
- 230000000087 stabilizing effect Effects 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 10
- 239000000203 mixture Substances 0.000 description 10
- 239000007788 liquid Substances 0.000 description 8
- 238000009826 distribution Methods 0.000 description 4
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 239000003344 environmental pollutant Substances 0.000 description 3
- 231100000719 pollutant Toxicity 0.000 description 3
- 206010016754 Flashback Diseases 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000009420 retrofitting Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Images
Classifications
-
- 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
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/40—Mixing tubes or chambers; Burner heads
- F23D11/402—Mixing chambers downstream of the nozzle
-
- 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 burner, consisting essentially of a Swirl generator for a combustion air flow, with a conical swirl space and means for introducing fuel into the combustion air stream, wherein the Swirl generator combustion air inlet openings for the tangential in the conical Swirl chamber entering combustion air flow and the means for Introducing fuel into the combustion air stream a first Fuel supply with a first group of substantially in the direction of Burner axis disposed fuel outlet openings for a first Premix fuel quantity include.
- EP 0 321 809 B1 discloses a cone-shaped burner consisting of several shells, a so-called double-cone burner, according to the preamble of claim 1.
- the conical swirl generator composed of several shells produces a closed swirl flow in the conical head, which becomes unstable due to the increasing swirl along the conically expanding swirl space and merges into an annular swirl flow with backflow in the core.
- the shells of the swirl generator are assembled in such a way that tangential air inlet slots for combustion air are formed along the burner axis.
- Feed streams for the premix gas, ie the gaseous fuel are provided on the inflow edge of the conical shells formed in this way, which have outlet openings for the premix gas distributed in the direction of the burner axis.
- the gas is injected through the outlet openings or bores transversely to the air inlet gap. This injection, in conjunction with the swirl generated in the swirl space of the combustion air-fuel gas flow to a good mixing of the fuel or premixed gas with the combustion air. Good mixing in such premix burners is the prerequisite for low NO x values during the combustion process.
- EP 0 918 191 A1 provides for improving the degree of mixing between Fuel and air in the flow direction through the combustion air inlet openings recalculated injection of fuel before, causing it to partial mixing between fuel and combustion air comes before this in the other Inlet of the swirl generator.
- the training of a to ensure stable flame inside the combustion chamber need extensive and structurally complicated flow-related measures be taken within the burner structure. It also shows that in particular the performance of a burner with regard to flame stability, Emission values and the occurrence of thermoacoustic pulsations in burners for the operation of gas turbine plants of medium and smaller capacities greater instabilities than in the case of burners that are powerful Gas turbine plants are designed.
- the invention is based on the object, a burner of the aforementioned Art, in particular according to the preamble of claim 1, so to design, that the operating behavior of the burner in the largest possible operating range should be stable, i. the burner should be independent of the current load have the most consistent combustion stability. Moreover, the Burner also with different fuel types or qualities and can be operated stably, especially at lower burner power.
- the Measures according to the invention should be simple and inexpensive to implement and, moreover, the possibility of retrofitting existing ones Allow burners. Within the above required large operating range the burner should have a minimized pollutant emission as well as a ensure maximum efficiency while forming a stable flame.
- the inventively constructed burner according to the features of the preamble of claim 1 is characterized by the combination of two measures. So the burner has at least a second fuel supply with at least a second group of substantially in the direction of the burner axis arranged fuel outlet openings for a second Premix fuel quantity, which is independent of the first fuel supply with Fuel is acted upon. In this way it is possible the Fuel supply together with the combustion air supply in the conical swirl space in at least two separate spatial areas along the Adjust burner axis within the swirl space individually and thereby in Dependence of the current burner load on individual fuel-air mixtures within the swirl space.
- a burner lance projects along a burner axis from the side of the burner Swirl space with the smallest swirl space cross section into the swirl space and has at least one fuel outlet opening within the burner lance, through the fuel, preferably liquid fuel, along the burner axis can be carried out.
- the burner lance preferably over at least 50% of the axial extent of the swirl space protrudes into this, on the one hand due to their preferably round outer contour which is fluid dynamics forming swirl flow within the swirl space stabilize, which ultimately also the flame front within the combustion chamber is stabilized, on the other hand, which allows preferably in the burner longitudinal axis oriented fuel outlet within the burner lance an additional Discharge of fuel into the swirl space, which coincides with the over the tangential Combustion air inlet openings along the swirl generator introduced Combustion air mixed and for the stable formation of a downstream in the Combustion chamber forming flame front contributes.
- the advantage of the inventively designed burner is in the multi-stage Fuel feed into the swirl chamber to see what the burner behavior in Depending on the burner load can be set very finely dosed.
- the burner lance within the swirl space which is a kind Flow body or Umströmungsisson for the longitudinal to the burner axis represents within the swirl space forming fuel-air mixture, the Extent of combustion usually occurring thermoacoustic pulsations significantly reduced.
- the inventive integration of the burner lance in at least one Double stepped premix burner is a burner operation for each type of Fuel possible. So allows the provided within the swirl space Burner lance the discharge of liquid fuel, preferably axially in Direction of the burner axis.
- the burner lance looks at her Brennerlanzen dictate the fuel outlet opening in front of an annular Opening is surrounded by the combustion air along the burner axis is dischargeable, so that the fuel discharge through the fuel outlet opening of the combustion air is cone-shaped, creating a centered Introduction of a liquid fuel-air mixture along the swirl space is created, in addition to the spiral along the burner axis spreading gaseous fuel-air mixture.
- the cone-shaped swirl generator provides at least two groups of fuel outlet openings along its combustion air inlet openings, through which individually selectable premix fuel quantities can each be fed into the swirl space.
- This makes it possible to achieve individual mixture distributions and mixing qualities, taking into account different combustion boundary conditions.
- a balance of different Wobbelwar be achieved by, for example, discharged via the first fuel supply a certain volume flow of fuel and the rest of the volume flow required for a certain power range is applied via the second fuel feeds.
- the burner according to the invention is not limited to just two fuel feeds with correspondingly arranged in the direction of the burner axis fuel outlet openings.
- the burner concept according to the invention also comprises three-, four- and multi-stage fuel feeds with corresponding fuel outlet openings, which can be acted upon separately and with gaseous fuel for a fuel exit into the swirl space to form a fuel-air mixture spreading along the burner axis are.
- the groups of the fuel outlet openings arranged essentially in the direction of the burner axis, which are each supplied individually with fuel via fuel feeds, are arranged in series in burner axles in corresponding exemplary embodiments or are designed to be partially overlapping at least in the burner axis.
- the special group-trained arrangements of fuel outlet openings along the burner axis in the combustion air inlet openings are basically no design-related limits set.
- the burner is preferably in the context of a heat generator operated, such as in a gas turbine, so may in a start phase of Gas turbine supplied the entire fuel via the first fuel supply become.
- the fuel for example divided into a first and one or more second fuel feeds become.
- the second fuel outlet openings of the second fuel supply in comparison to the first fuel outlets other mutual distances or Have flow cross sections.
- the respective fuel outlet openings also have the same mutual distances, however be offset from each other. This leads to a more uniform injection of the premix fuel into the swirl space.
- the first fuel outlet openings over the entire axial extent of the Combustion air inlet openings the second fuel outlet openings only in be arranged a certain axial portion. In the same way it is possible, the first fuel outlet openings only in a first axial Part area and the second fuel outlet openings only in one at the provide first partial area subsequent second axial portion - or vice versa.
- each other means independent regulation or control of the premix fuel supply to the provided first and the second fuel feeds.
- the different ones Supply can be controlled for example by a suitable control valve.
- a longitudinal section is shown by a highly schematic Premix burner with burner lance 6 shown.
- the premix burner has a starting from the burner head 1 conically expanding swirl space 2, the is surrounded radially by a conical swirl generator 2, each consisting of at least two premix burner bowls, the at least two combustion air inlet openings (not shown) for a tangential in the cone-shaped Include swirl space 2 incoming combustion air flow.
- a conical swirl generator 2 each consisting of at least two premix burner bowls, the at least two combustion air inlet openings (not shown) for a tangential in the cone-shaped Include swirl space 2 incoming combustion air flow.
- Such a burner is described in detail in EP 0 321 809 B1 and this document is integrated Component of this description.
- Combustion air inlets is a first group 4 of substantially in the direction the burner axis A arranged fuel outlet openings provided, the via a not shown first fuel supply with preferably supplied gaseous fuel.
- burner assembly is a so-called two-stage Premix burner, wherein the order of the steps of the number of separate Groups of separately supplied with gaseous fuel fuel outlet openings depends.
- embodiments are conceivable in which three and more groups of fuel outlet openings along the combustion air inlet openings are arranged.
- Such premixed burners allow depending on the respective Operating condition, i. be it start, part load or full load conditions, one Optimized fuel supply into the swirl chamber 2, resulting in an optimized Incineration is taken care of.
- one Optimized fuel supply into the swirl chamber 2 resulting in an optimized Incineration is taken care of.
- the fuel supply over the first stage of the fuel outlet openings 4 by a Regardless regulated second fuel feed through the second stage of Fuel outlet openings 5 supplements.
- In full load operation is suitable exclusive fuel feed via the second stage of the fuel outlets 5. The centrally from the side of the burner head 1 in the swirl space.
- burner lance 6 protruding burner lance 6 is due to its aerodynamically shaped round outer contour to stabilize within the swirl space 2 forming fuel-air vortex flow, axially in accordance with Longitudinal view to the right in the subsequent, not shown Combustion chamber, spreads. Due to the aerodynamically stabilizing effect of Burner lance 6 on the forming fuel-air vortex flow is a supports spatially stable flame front within the combustion chamber. Also will be through the burner lance the commonly occurring thermoacoustic Vibrations significantly reduced.
- At the burner tip 7 of the burner lance 6 at least one more Fuel outlet 8 provided axially through the liquid fuel to Burner axis A is discharged.
- a preferably annular Air outlet 9 provided by the liquid fuel discharge in the Burner space of a preferably conically spreading Air vortex flow is surrounded.
- the central by the burner lance 6 Liquid fuel discharge into the swirl space 2 leads to a central fuel enrichment within the vortex-shaped fuel-air mixture, causing the inside of the combustion chamber (not shown) forming flame front is additionally stabilized and the firing temperature is increased.
- the fuel input be it through the Fuel outlet openings 4, 5 or 8 individually matched to each other be made.
- the burner concept according to the invention opens up by the multiplicity of different separately controllable fuel feeds in the presence of an aerodynamic stabilizing acting burner lance a high variability in control measures, the fuel type, fuel quantity as well as the spatial distribution relates to the fuel supply within the swirl generator.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH14932003 | 2003-09-01 | ||
CH14932003 | 2003-09-01 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1510755A1 true EP1510755A1 (fr) | 2005-03-02 |
EP1510755B1 EP1510755B1 (fr) | 2016-09-28 |
Family
ID=34085317
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04104099.9A Not-in-force EP1510755B1 (fr) | 2003-09-01 | 2004-08-26 | Brûleur avec lance et alimentation étagée en carburant |
Country Status (2)
Country | Link |
---|---|
US (1) | US7445445B2 (fr) |
EP (1) | EP1510755B1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2068076A2 (fr) | 2007-12-03 | 2009-06-10 | Siemens Aktiengesellschaft | Améliorations portant sur ou en relation avec des brûleurs pour un moteur à turbine à gaz |
US8313324B2 (en) | 2006-01-19 | 2012-11-20 | Siemens Aktiengesellschaft | Fuel ratio control in a combustion apparatus with multiple fuel supply lines |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1828684A1 (fr) * | 2004-12-23 | 2007-09-05 | Alstom Technology Ltd | Bruleur de premelange dote d'un parcours de melange |
EP2058590B1 (fr) * | 2007-11-09 | 2016-03-23 | Alstom Technology Ltd | Procédé de fonctionnement d'un brûleur |
EP2220433B1 (fr) * | 2007-11-27 | 2013-09-04 | Alstom Technology Ltd | Procédé et dispositif pour la combustion d'hydrogène dans un brûleur à prémélange |
US8479720B1 (en) | 2008-10-16 | 2013-07-09 | Oscar Enrique Figueroa | Heating device and method |
JP5462502B2 (ja) * | 2009-03-06 | 2014-04-02 | 大阪瓦斯株式会社 | 管状火炎バーナ |
US8616002B2 (en) * | 2009-07-23 | 2013-12-31 | General Electric Company | Gas turbine premixing systems |
US20120052451A1 (en) * | 2010-08-31 | 2012-03-01 | General Electric Company | Fuel nozzle and method for swirl control |
KR102002042B1 (ko) * | 2012-05-29 | 2019-07-19 | 주성엔지니어링(주) | 기판 처리 장치 및 기판 처리 방법 |
US9991023B2 (en) * | 2013-01-29 | 2018-06-05 | Creganna Unlimited Company | Interconnect cable having insulated wires with a conductive coating |
US20140209347A1 (en) | 2013-01-29 | 2014-07-31 | Tyco Electronics Corporation | Cable Having a Sparse Shield |
US11774093B2 (en) | 2020-04-08 | 2023-10-03 | General Electric Company | Burner cooling structures |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5127821A (en) * | 1989-04-24 | 1992-07-07 | Asea Brown Boveri Ltd. | Premixing burner for producing hot gas |
US5482457A (en) * | 1992-10-16 | 1996-01-09 | Asea Brown Boveri Ltd. | Gas-operated premixing burner |
US5833451A (en) * | 1995-12-05 | 1998-11-10 | Asea Brown Boveri Ag | Premix burner |
WO2001096785A1 (fr) * | 2000-06-15 | 2001-12-20 | Alstom (Switzerland) Ltd | Procede pour l'exploitation d'un bruleur et bruleur a injection etagee de gaz premelange |
WO2002029318A1 (fr) * | 2000-10-05 | 2002-04-11 | Alstom (Switzerland) Ltd | Procede et dispositif pour alimenter un bruleur a melange prealable en combustible |
WO2002052201A1 (fr) * | 2000-12-23 | 2002-07-04 | Alstom (Switzerland) Ltd | Bruleur a injection de combustible etagee |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2109003B (en) | 1981-11-02 | 1985-05-30 | British Gas Corp | Sulphide-resistant iron-base alloy for coal gasifier |
CH674561A5 (fr) | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
CH680816A5 (fr) * | 1989-04-27 | 1992-11-13 | Asea Brown Boveri | |
ATE244380T1 (de) | 1997-11-21 | 2003-07-15 | Alstom | Brenner für den betrieb eines wärmeerzeugers |
DE10051221A1 (de) * | 2000-10-16 | 2002-07-11 | Alstom Switzerland Ltd | Brenner mit gestufter Brennstoff-Eindüsung |
DE10205839B4 (de) * | 2002-02-13 | 2011-08-11 | Alstom Technology Ltd. | Vormischbrenner zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen |
-
2004
- 2004-08-26 EP EP04104099.9A patent/EP1510755B1/fr not_active Not-in-force
- 2004-09-01 US US10/931,052 patent/US7445445B2/en not_active Expired - Fee Related
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5127821A (en) * | 1989-04-24 | 1992-07-07 | Asea Brown Boveri Ltd. | Premixing burner for producing hot gas |
US5482457A (en) * | 1992-10-16 | 1996-01-09 | Asea Brown Boveri Ltd. | Gas-operated premixing burner |
US5833451A (en) * | 1995-12-05 | 1998-11-10 | Asea Brown Boveri Ag | Premix burner |
WO2001096785A1 (fr) * | 2000-06-15 | 2001-12-20 | Alstom (Switzerland) Ltd | Procede pour l'exploitation d'un bruleur et bruleur a injection etagee de gaz premelange |
WO2002029318A1 (fr) * | 2000-10-05 | 2002-04-11 | Alstom (Switzerland) Ltd | Procede et dispositif pour alimenter un bruleur a melange prealable en combustible |
WO2002052201A1 (fr) * | 2000-12-23 | 2002-07-04 | Alstom (Switzerland) Ltd | Bruleur a injection de combustible etagee |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8313324B2 (en) | 2006-01-19 | 2012-11-20 | Siemens Aktiengesellschaft | Fuel ratio control in a combustion apparatus with multiple fuel supply lines |
EP2068076A2 (fr) | 2007-12-03 | 2009-06-10 | Siemens Aktiengesellschaft | Améliorations portant sur ou en relation avec des brûleurs pour un moteur à turbine à gaz |
Also Published As
Publication number | Publication date |
---|---|
US20050106522A1 (en) | 2005-05-19 |
EP1510755B1 (fr) | 2016-09-28 |
US7445445B2 (en) | 2008-11-04 |
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