EP1856442A1 - Vormischbrenner zum erzeugen eines zündfähigen brennstoff-luftgemisches - Google Patents
Vormischbrenner zum erzeugen eines zündfähigen brennstoff-luftgemischesInfo
- Publication number
- EP1856442A1 EP1856442A1 EP06724902A EP06724902A EP1856442A1 EP 1856442 A1 EP1856442 A1 EP 1856442A1 EP 06724902 A EP06724902 A EP 06724902A EP 06724902 A EP06724902 A EP 06724902A EP 1856442 A1 EP1856442 A1 EP 1856442A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- fuel
- fuel line
- shell
- burner shell
- 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
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
- 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
- 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
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2211/00—Thermal dilatation prevention or compensation
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, which together enclose an axially conically widening swirl space and limit each other in the axial longitudinal extent of the cone mutually tangential air inlet slots through the Combustion air enters the swirl space, in which an axially spreading swirl flow is formed, and with means for injecting fuel, which are provided at least in sections along the tangentially extending 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 create a consisting of a fuel-air mixture swirl flow, which within a downstream of the premix burner combustion chamber under training a spatially stable preheating flame is ignited.
- the partial cone shells which overlap with each other, enclose tangential air inlet slots along the burner axis the radially in the bounded by the partial cone shells swirl space air under impression of a longitudinally to the burner axis propagating swirl flow occurs.
- the mostly double-walled partial cone shells provide for fuel supply in the region along the air inlet slots at least one inner fuel supply channel, is supplied through each gaseous fuel, which exits through fuel nozzle openings in the region of the air inlet slots.
- the fuel openings are distributed in the region of the burner shell wall facing the air inlet slot, in order to ensure an effective and as uniform as possible mixing between the gaseous fuel and the inflowing supply air already in the region of the air inlet slot.
- the supply of gaseous fuel for further feeding along the fuel openings in the region of the air inlet slots usually takes place at gas temperatures in the range between 20 and 30 ° C.
- gas temperatures temperatures between 300 to 350 ° C.
- all those partial cone shell surfaces delimiting the air inlet areas have body temperatures in the range of the above radiation temperatures.
- the partial cone cup portions are cooled immediately around the fuel holes by the cool gas flow. Due to these temperature differences occur in the Area of fuel openings on high thermal gradients, which lead to cracks within the material surrounding the fuel openings.
- a premix burner according to the features of the preamble of claim 1 is developed in such a way that the means for injecting fuel is formed as a fuel line separate from the burner shell, which is longitudinally movably fixed to the burner shell along the burner shell and perpendicular to the surface of the burner shell.
- the means for injecting fuel is formed as a fuel line separate from the burner shell, which is longitudinally movably fixed to the burner shell along the burner shell and perpendicular to the surface of the burner shell.
- Holes provided, open into the fuel injectors, which are provided along the fuel line, which project beyond the peripheral edge of the fuel line.
- the invention is based on the idea to carry out the necessary means for injecting gaseous fuel along the air inlet slot means as separate components, preferably as a separate component, and so spatially relative to the burner shell, so that thermal gradients can be avoided within the material.
- those components in which the comparatively cool burner gas is guided have to be formed and fastened separately from the burner shells, which are heated to correspondingly high temperatures due to the direct radiation exposure in the area of the swirl space.
- Component separation eliminates thermal stresses within the burner shells, thereby eliminating material cracks and the associated problems and hazards.
- the fuel line provided for supplying fuel to each individual burner shell is designed for this purpose in the form of a conduit tube sealed off on both sides and has a tube length which is adapted to the axial extension of the respective burner shell and does not protrude beyond it.
- the fuel line associated with each individual burner shell is connected by at least one retaining means on the burner shell surface remote from the swirl space, such that the fuel line is largely fixed to the burner shell surface by clamping force, but is preferably mounted away from the burner shell surface by a separating gap and largely freely movable in the axial direction to the burner shell is stored.
- fuel injectors that protrude at least partially provided by openings provided within the burner shell or holes.
- the fuel injectors are formed in a preferred embodiment as each having a hollow channel sleeve members having a maximum the peripheral edge of the fuel line towering elevation, with which they connect flush to the fuel line facing away from the surface of the burner shell.
- each individual fuel line is provided with a connecting web, via which the fuel line is firmly connected to a component of the premix burner, which is not part of the burner shell.
- a connecting web via which the fuel line is firmly connected to a component of the premix burner, which is not part of the burner shell.
- Fig. 2 three-dimensional coronal arrangement of a variety of
- FIG. 3 perspective view of a fuel line, as well Fig. 4 detail of a introduced in a burner cup
- FIG. 1 shows a three-dimensional representation of a single burner shell 1, the upper side facing away from the swirl space facing the viewer visibly.
- the eight individual burner shells 1 provides, which are arranged in a ring around a mold element 2 and each internally in each case a conically widening Include swirl space.
- a retaining ring to be provided for the stability of the burner shells 1, which centrally supports the upper ends of the burner shells in the illustration, is not shown, especially as it does not depend on this to explain the measure according to the solution.
- each two immediately adjacent arranged burner shells 1 together include an air inlet slot 3, flows through the radial flow direction in each case a supply air flow L in the limited by the burner shells 1 inside swirl space.
- the swirl flow forming within the swirl space emerges downwards from the swirl generator shown in FIG. 2 (see arrow illustration).
- gaseous fuel in the region of the air inlet slot 3 of the inflowing combustion air L is added in a manner known per se. This is done by located within the burner shells 1 openings 4, which are arranged in each axial extent of each burner shell, preferably along a straight line.
- the fuel supply takes place in each individual burner shell via a fuel supply line 5 (see Figures 1 and 2), which is connected to a tube-like fuel line 6.
- the tube-like fuel line 6 is formed in each case closed at its two pipe ends and arranged as a separate component relative to the burner shell 1.
- the pipeline 6 provides sleeve-like fuel injectors 7 which, facing the burner shell 1, open at least partially into or through the openings 4 provided in the burner shell 1.
- a holding means 8 which supports the fuel line 6 radially, i. is fixed in a tension-loaded manner perpendicular to the surface of the burner shell 1 and ensures that the fuel injectors 7 projecting into the openings 4 within the burner shell 1 remain securely in the openings and can not "slip out.”
- the retaining means 8 designed as a retaining clip offers the possibility that the Fuel line 6 along its longitudinal axis, ie axially to the burner shell, at least slightly relative movements to perform to prevent in this way any distortion phenomena and clamping between the fuel line 6 and the burner shell 1 due to different thermal expansion behavior.
- the holding means 8 designed as a retaining clip has a shape adapted to the outer contour of the pipeline 6, in the case of a cylinder-shaped fuel line 6 the retaining means is U-shaped and connected to both U-legs at the top of the burner shell 1.
- the connection between the holding means 8 and the burner shell 1 is carried out either in the context of a fixed connection, for example solder or welded connection or by means of a releasably fixed connection, through which a simplified assembly and disassembly of the burner components is possible.
- the fuel line 6 is connected via a connecting web 9 fixed to the inlet geometry of the mold element 2 (see Figure 2).
- the connecting web 9 leads to a fixedly connected to the fuel line 6 connecting flange 10 which establishes a gas-tight connection between the fuel line 6 and supply line 5.
- FIG. 3 shows a schematic perspective view of the fuel line 6 as a separate component.
- the sleeve-like fuel injectors 7 each project beyond the peripheral edge of the tubular fuel line 6, so that they open at least partially into the openings, not shown in FIG. 3, inside the burner shell 1.
- two separate fuel supply lines 5, 5 ' is provided, is supplied via the gaseous fuel from two different fuel supply circuits of the fuel line 6.
- the connecting web 9 is attached, the ungsfuss a fastening 14 provides on which the separate unit is firmly attached to the inlet geometry of the mold element 2, preferably by way of a soldered or welded connection.
- Figure 4 shows a partial cross-sectional view through the fuel line 6 in the region of a fuel injector 7, which opens into the opening 4 of a burner shell 1.
- the fuel injector 7 is sleeve-like and has an inner hollow channel 15, injected by the gaseous fuel from the interior of the fuel line 6 in the bounded by two adjacent burner shells air inlet gap 3.
- the Peripheral edge of the fuel line 6 from the fuel line 6 facing top of the burner shell 1 spaced can be done by providing an air gap between the two components, which is ensured by means not shown spacers between the fuel line 6 and the burner shell 1, or by means of a suitably provided thermally or poorly conductive intermediate layer.
- the openings provided within the burner shell 1 are formed with a slight excess over the diameter of the fuel injectors, so that between the outer peripheral edge of the respective fuel injector 7 and the Opening 4 sets a clear air gap.
- the openings 4 introduced within the burner shell 1 are designed as elongated holes oriented in the axial extension of the burner shell, in order in particular to allow the greatest possible possibility of relative longitudinal expansion for the area of the fuel line 6 located furthest away from the connecting web 9.
- the fuel injector 7 embodied as a sleeve element is connected to the pipeline wall via at least one intermediate element 16 in order to minimize the heating that may possibly occur on the fuel line 6 via the sleeve element of the fuel injector 14.
- the burner shell 1 Due to the separate design of the fuel line 6 and its storage described above the burner shell 1 can be largely excluded any thermal stresses between the two components and in particular the associated risk of possible cracking in the material of the burner shell in the fuel holes are avoided. LIST OF REFERENCE NUMBERS
- Burner shell Form element Air inlet gap Opening inside the burner shell, 5 'Supply line Fuel line Fuel injector Holding means Connecting bridge 0 Connecting flange 1, 12 End sections of the fuel line 6 3 Opening inside the fuel line 4 Fastening 5 Hollow channel 6 Adapter
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH4072005 | 2005-03-09 | ||
PCT/EP2006/060355 WO2006094922A1 (de) | 2005-03-09 | 2006-03-01 | Vormischbrenner zum erzeugen eines zündfähigen brennstoff-luftgemisches |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1856442A1 true EP1856442A1 (de) | 2007-11-21 |
EP1856442B1 EP1856442B1 (de) | 2010-08-25 |
Family
ID=34974799
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06724902A Active EP1856442B1 (de) | 2005-03-09 | 2006-03-01 | Vormischbrenner zum erzeugen eines zündfähigen brennstoff-luftgemisches |
Country Status (9)
Country | Link |
---|---|
US (1) | US8007273B2 (de) |
EP (1) | EP1856442B1 (de) |
CN (1) | CN101137868A (de) |
AR (1) | AR052686A1 (de) |
AT (1) | ATE479054T1 (de) |
DE (1) | DE502006007733D1 (de) |
DK (1) | DK1856442T3 (de) |
MY (1) | MY146315A (de) |
WO (1) | WO2006094922A1 (de) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ATE479054T1 (de) | 2005-03-09 | 2010-09-15 | Alstom Technology Ltd | Vormischbrenner zum erzeugen eines zündfähigen brennstoff-luftgemisches |
EP2796789B1 (de) * | 2013-04-26 | 2017-03-01 | General Electric Technology GmbH | Rohrbrennkammer für eine Rohr-Ring Anordnung in einer Gasturbine |
ITMI20131931A1 (it) * | 2013-11-20 | 2015-05-21 | Tenova Spa | Bruciatore industriale autorigenerativo e forno industriale per la conduzione di processi di combustione autorigenerativa |
CN104406163A (zh) * | 2014-11-12 | 2015-03-11 | 宁夏嘉翔自控技术有限公司 | 一种金属镁还原炉的煤粉燃烧器的壳体 |
USD842979S1 (en) * | 2017-05-24 | 2019-03-12 | Hamworthy Combustion Engineering Limited | Atomizer |
CN107252640B (zh) * | 2017-06-23 | 2023-06-27 | 东风商用车有限公司 | 一种管道流体混合器总成 |
CN107261873B (zh) * | 2017-06-23 | 2023-06-02 | 东风商用车有限公司 | 一种管道流体混合器结构 |
US10837643B2 (en) | 2018-08-06 | 2020-11-17 | General Electric Company | Mixer assembly for a combustor |
Family Cites Families (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2056531A (en) * | 1933-05-22 | 1936-10-06 | Amco Inc | Process for luminous flame heating |
US2181108A (en) * | 1936-12-02 | 1939-11-21 | Fedders Mfg Company | Apparatus for making cross-fin coils |
US2390947A (en) * | 1940-04-01 | 1945-12-11 | Chicago Flexible Shaft Co | Compensating thermostat |
US2532569A (en) * | 1948-01-29 | 1950-12-05 | William L Gilbert Clock Corp | Automatic electric toaster and the like |
US2996598A (en) * | 1960-06-29 | 1961-08-15 | Gen Electric | Support structure for surface heating units |
US3324625A (en) * | 1963-10-11 | 1967-06-13 | Dow Chemical Co | Equipment and method of controlled peripheral shrink |
US4216652A (en) * | 1978-06-08 | 1980-08-12 | General Motors Corporation | Integrated, replaceable combustor swirler and fuel injector |
EP0210462B1 (de) | 1985-07-30 | 1989-03-15 | BBC Brown Boveri AG | Dualbrenner |
CH674561A5 (de) | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
CH682952A5 (de) * | 1991-03-12 | 1993-12-15 | Asea Brown Boveri | Brenner für eine Vormischverbrennung eines flüssigen und/oder gasförmigen Brennstoffes. |
US5307634A (en) * | 1992-02-26 | 1994-05-03 | United Technologies Corporation | Premix gas nozzle |
EP0592717B1 (de) * | 1992-10-16 | 1998-02-25 | Asea Brown Boveri Ag | Gasbetriebener Vormischbrenner |
US5479773A (en) * | 1994-10-13 | 1996-01-02 | United Technologies Corporation | Tangential air entry fuel nozzle |
US5916142A (en) * | 1996-10-21 | 1999-06-29 | General Electric Company | Self-aligning swirler with ball joint |
DE59710380D1 (de) * | 1997-11-21 | 2003-08-07 | Alstom | Brenner für den Betrieb eines Wärmeerzeugers |
US6176087B1 (en) * | 1997-12-15 | 2001-01-23 | United Technologies Corporation | Bluff body premixing fuel injector and method for premixing fuel and air |
EP0924458B1 (de) * | 1997-12-22 | 2002-08-28 | Alstom | Brenner |
US6094904A (en) * | 1998-07-16 | 2000-08-01 | United Technologies Corporation | Fuel injector with a replaceable sensor |
DE19859829A1 (de) * | 1998-12-23 | 2000-06-29 | Abb Alstom Power Ch Ag | Brenner zum Betrieb eines Wärmeerzeugers |
DE59909531D1 (de) * | 1999-07-22 | 2004-06-24 | Alstom Technology Ltd Baden | Vormischbrenner |
DE10050248A1 (de) * | 2000-10-11 | 2002-04-18 | Alstom Switzerland Ltd | Brenner |
DE10064259B4 (de) * | 2000-12-22 | 2012-02-02 | Alstom Technology Ltd. | Brenner mit hoher Flammenstabilität |
US6539724B2 (en) * | 2001-03-30 | 2003-04-01 | Delavan Inc | Airblast fuel atomization system |
CN1263983C (zh) * | 2001-10-19 | 2006-07-12 | 阿尔斯通技术有限公司 | 用于合成气体的燃烧器 |
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 |
DE102004049491A1 (de) * | 2004-10-11 | 2006-04-20 | Alstom Technology Ltd | Vormischbrenner |
ATE479054T1 (de) | 2005-03-09 | 2010-09-15 | Alstom Technology Ltd | Vormischbrenner zum erzeugen eines zündfähigen brennstoff-luftgemisches |
US7721436B2 (en) * | 2005-12-20 | 2010-05-25 | Pratt & Whitney Canada Corp. | Method of manufacturing a metal injection moulded combustor swirler |
-
2006
- 2006-03-01 AT AT06724902T patent/ATE479054T1/de active
- 2006-03-01 DK DK06724902.9T patent/DK1856442T3/da active
- 2006-03-01 EP EP06724902A patent/EP1856442B1/de active Active
- 2006-03-01 DE DE502006007733T patent/DE502006007733D1/de active Active
- 2006-03-01 WO PCT/EP2006/060355 patent/WO2006094922A1/de not_active Application Discontinuation
- 2006-03-01 CN CNA2006800074297A patent/CN101137868A/zh active Pending
- 2006-03-08 MY MYPI20060988A patent/MY146315A/en unknown
- 2006-03-09 AR ARP060100893A patent/AR052686A1/es active IP Right Grant
-
2007
- 2007-08-15 US US11/838,999 patent/US8007273B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2006094922A1 * |
Also Published As
Publication number | Publication date |
---|---|
WO2006094922A1 (de) | 2006-09-14 |
US8007273B2 (en) | 2011-08-30 |
AR052686A1 (es) | 2007-03-28 |
US20080032246A1 (en) | 2008-02-07 |
DK1856442T3 (da) | 2010-12-20 |
DE502006007733D1 (de) | 2010-10-07 |
MY146315A (en) | 2012-07-31 |
EP1856442B1 (de) | 2010-08-25 |
ATE479054T1 (de) | 2010-09-15 |
CN101137868A (zh) | 2008-03-05 |
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