EP2233836B1 - Drallerzeuger, Verfahren zum Vermeiden von Flammenrückschlag in einem Brenner mit wenigstens einem Drallerzeuger und Brenner - Google Patents

Drallerzeuger, Verfahren zum Vermeiden von Flammenrückschlag in einem Brenner mit wenigstens einem Drallerzeuger und Brenner Download PDF

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Publication number
EP2233836B1
EP2233836B1 EP09155904.7A EP09155904A EP2233836B1 EP 2233836 B1 EP2233836 B1 EP 2233836B1 EP 09155904 A EP09155904 A EP 09155904A EP 2233836 B1 EP2233836 B1 EP 2233836B1
Authority
EP
European Patent Office
Prior art keywords
fuel
swirl
combustion air
flow
swirl generator
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
EP09155904.7A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2233836A1 (de
Inventor
Michael Huth
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP09155904.7A priority Critical patent/EP2233836B1/de
Priority to JP2010059450A priority patent/JP5615008B2/ja
Priority to CA2697200A priority patent/CA2697200A1/en
Priority to US12/728,518 priority patent/US8789373B2/en
Priority to RU2010110965/06A priority patent/RU2535901C2/ru
Priority to CN201010151559.6A priority patent/CN101846320B/zh
Publication of EP2233836A1 publication Critical patent/EP2233836A1/de
Priority to US14/263,509 priority patent/US20140230448A1/en
Application granted granted Critical
Publication of EP2233836B1 publication Critical patent/EP2233836B1/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
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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 
    • 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
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes

Definitions

  • the present invention relates to a swirl generator with a central fuel distributor element and to a burner with at least one swirl generator.
  • the invention relates to a method for avoiding flashback in a burner comprising at least one swirl generator with a central fuel distributor element.
  • Gas turbine burners with a central fuel distributor elements and the swirl generators surrounding the fuel distributor elements are, for example, in DE 10 2007 004 394 A1 , in US 2004/0055306 A1 and in US 6,082,111 described.
  • the swirl generator extends from the central fuel distributor element to a surrounding the central fuel distributor element, an axial flow channel for combustion air limiting wall.
  • the burners each comprise a plurality of such arrangements. In such burners, the profiles of the fuel injected into the flow channel are designed such that only very little fuel is supplied to the zone around the central fuel distributor element, so that only a very lean mixture forms in this zone. The reason for this is that a flashback should be avoided.
  • the US 2008/0280238 A1 discloses a burner having a centrally located pilot burner and an outer wall surrounding the central pilot burner, defining an axial combustion air flow passage, and a partition wall surrounding the central pilot burner and located radially inwardly of the outer wall, forming the flow passage into a radially inner passage section and a radially outer passage section separates.
  • a flow unifying aperture is arranged in the radially inner channel portion, whereas in the outer channel portion swirl blades are arranged, which extend in the radial direction to the outer wall and the flowing combustion air impose a tangential flow component.
  • An annular fuel distributor ring extends around the outside wall and around the outside feeds fuel lines which extend through the outer channel section and protrude into the inner channel section.
  • the DE 10 2008 044448 A1 discloses a gas turbine pre-mixer having a central hub and an outer wall surrounding the hub, wherein the flow channel located between the hub and outer wall is divided by a partition wall into an inner and an outer channel section. In both the inner and in the outer channel portion swirl vanes are arranged, which impart a twist to the flow.
  • a further object of the present invention is to provide an advantageous method for avoiding flashback in a burner with at least one swirl generator.
  • a swirl generator comprises a central fuel distributor element, an outer wall surrounding the central fuel distributor element and defining an axial flow channel for combustion air, swirl vanes extending radially to the outer wall and imparting a tangential flow component to the flowing combustion air, and radially surrounding the central fuel distributor element inside the outer wall partition.
  • the partition separates the flow channel into a radially inner channel section and a radially outer channel section.
  • the partition in the axial direction of the swirl generator at least over the axial Length of the swirl blades, but in particular also extend beyond the axial length.
  • the radially inner channel section passes the combustion air without imparting a tangential flow component, fuel pipelines extending through the radially inner channel section to the swirl vanes in the radially outer channel section.
  • fuel outlet openings in the fuel piping can in particular be arranged so that they the fuel substantially perpendicular to the flow direction of the combustion air in the radially inner channel section into the combustion air.
  • fuel outlet openings may be present, which may be arranged in particular so that they inject the fuel substantially perpendicular to the flow direction of the combustion air in the radially outer channel section into the combustion air.
  • the injection direction does not necessarily have to be perpendicular to the flow direction of the combustion air.
  • the injection direction can basically be chosen freely.
  • the fuel can also be supplied perpendicular to the radial direction and / or opposite to the flow direction of the combustion air flowing through the flow channel and / or parallel to the flow direction of the combustion air flowing through the flow channel.
  • this applies both to the fuel supply in the inner duct section and to the fuel supply in the outer in the outer duct section.
  • the dividing wall may at least partially have a conical shape, wherein the opening cross section of the radially inner channel section decreases in the direction of flow of the combustion air.
  • the dividing wall projects beyond the outflow-side end of the outer wall. This development can be realized both in a conical partition, as well as in a non-conical partition.
  • An inventive burner is equipped with at least one swirl generator according to the invention.
  • the advantages described with respect to the swirl generator can be realized in a burner, which in particular can be a gas turbine burner.
  • the invention also provides a method of preventing flashback in a combustor comprising at least one swirl generator with a central fuel distribution element and an outer wall surrounding the central fuel distribution element defining an axial combustion air flow passage.
  • the combustion air flowing through the flow channel is imparted a tangential flow component in a radially outer channel region.
  • the combustion air flowing through the flow channel does not impart a tangential flow component, fuel being directed through fuel conduits which extend through the radially inner channel section to the swirl vanes in the radially outer channel section.
  • a particularly uniform fuel profile can be generated when fuel is supplied to the combustion air flowing through the flow channel.
  • the fuel can in this case in particular perpendicular to the flow direction of the is mixed by the flow channel flowing combustion air and / or perpendicular to the radial direction.
  • An admixing substantially opposite to the flow direction of the combustion air flowing through the flow channel and / or parallel to the flow direction of the combustion air flowing through the flow channel is possible alternatively or in addition to the aforementioned variants.
  • FIG. 1 showing a highly schematic sectional view of a gas turbine, explaining the structure and function of a gas turbine.
  • the gas turbine 1 comprises a compressor section 3, a combustion section 4, which in the present embodiment comprises a plurality of tube combustion chambers 5 with burners 6 arranged thereon, but in principle may also comprise an annular combustion chamber, and a turbine section 7.
  • a rotor 9, also called a runner, extends extending through all sections and carries in the compressor section 3 compressor blade rings 11 and the turbine section 7 turbine blade rings 13.
  • FIG. 2 shows a burner 6 of the combustion section 4 in a perspective view.
  • the burner 6 comprises a fuel distributor 27, eight fuel nozzles 29 extending from the fuel distributor 27 and eight swirl generators 31 arranged in the region of the tips of the fuel nozzles 29.
  • the fuel distributor 27 and the fuel nozzles 29 together form a burner housing through which fuel lines extend Extend injection openings, which are arranged within the swirl generator 31 and therefore in FIG. 2 are not recognizable.
  • the burner can be connected to fuel supply lines.
  • a flange 35 the burner 6 can be attached to a tube combustion chamber so that the fuel nozzles 29 point towards the interior of the combustion chamber.
  • burner 6 has eight fuel nozzles 29, it is also possible to equip it with a different number of fuel nozzles 29.
  • the number of fuel nozzles can be greater than or less than eight, for example, six fuel nozzles or twelve fuel nozzles may be present, each having its own swirl generator.
  • a pilot fuel nozzle is usually arranged in the center of the burner. The pilot fuel nozzle is in for clarity FIG. 2 not shown.
  • air from the compressor is passed through the swirl generators 31 where it is mixed with fuel. Subsequently, the air-fuel mixture is then burned in the combustion zone of the combustion chamber 5 to form the working medium.
  • FIG. 3 a swirl generator of the burner 6 is shown in a perspective view.
  • the swirl generator 31 has a central fuel distributor element 37 which is surrounded by an outer wall 39, which forms an axial flow channel for compressor air.
  • a central fuel distributor element 37 surrounding and located radially within the outer wall 39 dividing wall 42 is present, which separates the flow channel 41 into a radially inner channel portion 43 and a radially outer channel portion 45.
  • swirl vanes 47 extend in the radial direction through the radially outer channel section to the outer wall 39.
  • the swirl vanes 47 mediate the flowing through the radially outer channel section 45 compressor air a tangential flow component, so that the air after passing through the swirl generator 31 forms a vortex.
  • the pipelines 49 may in principle also have a round cross-section.
  • the fuel conduits 49 are arranged to be aligned with the swirl vanes 47 in the radially outer passage portion so that a fuel passage 51 may extend in a straight line from the central fuel distributor 37 through the fuel conduits 49 to the swirl vanes 47.
  • the fuel channels 51 are in particular in FIG. 5 which shows a sectional view through the swirl generator 31 along its longitudinal axis.
  • outlet openings 53 in the swirl vanes 47 and outlet openings 55 in the fuel pipes 49 are supplied with fuel.
  • the outlet openings 53, 55 are arranged so that the fuel is injected substantially perpendicular to the flow direction of the compressor air in the radially outer channel portion 45 and the radially inner channel portion 43.
  • the swirl generator design described causes the compressor air flowing through the radially inner channel section 43 to be imparted with no twist. As a result, the flow velocity of this compressor air in the axial direction is higher than in the compressor air flowing through the radially outer channel section 45, in which part of the axial flow is converted into a tangential flow component. Due to the higher axial flow rate in the radially inner channel portion, ie, in the area adjacent to the central fuel distribution element 37, the emergence of low axial flow rate zones downstream of the central fuel distribution element 37 can be avoided, which in turn results in avoiding flashbacks. This allows more fuel to be injected in the vicinity of the central distributor element 37 compared to the prior art, which reduces the NO x emissions during combustion.
  • the partition 42 extends at least over the entire axial length of the swirl vanes 47 in the radially outer channel section 45, so that the supply of a tangential flow component in the radially inner channel section 43 can be reliably avoided.
  • the partition wall 42 also extends in the axial direction beyond the arrival and trailing edges of the swirl vanes 47 in order to avoid influencing the compressor air flowing through the radially inner channel section 43 by the swirling air flowing in the radially outer channel section 45.
  • FIG. 6 An alternative embodiment of the swirl generator 31 is shown in FIG. 6 shown. Elements corresponding to the swirl generator of the first embodiment are shown in FIG FIG. 6 are denoted by the same reference numerals as in the first embodiment and will not be explained again to avoid repetition.
  • the swirl generator 131 of the second embodiment differs from the swirl generator 31 of the first embodiment only by its partition wall 142.
  • the partition wall 142 of the second embodiment has a conical portion 144 which causes the opening cross section of the radially inner channel portion 43 reduced toward the output of the swirl generator 131 out.
  • the conical portion 144 By the conical portion 144, the flow velocity of the compressor air flowing through the radially inner passage portion 43 increases in comparison with the swirl generator 31 of the first embodiment.
  • the central fuel distributor element 37 can thus be surrounded by an air jacket, which has a particularly high axial flow velocity and thus particularly reliably avoids the formation of regions with low flow velocity, and consequently the formation of flashbacks.
  • the partition 142 in the present embodiment only has a conical portion 144 downstream, it may also be conical over its entire axial length.
  • FIG. 7 A third embodiment of the swirl generator according to the invention is in FIG. 7 shown in a partially sectioned view. As with the swirl generator of the second embodiment, even in the swirl generator of the third embodiment, all those elements which do not differ from the first embodiment are denoted by the same reference numerals as in the first embodiment and will not be described again.
  • the swirl generator 231 of the third exemplary embodiment differs from the swirl generator of the first exemplary embodiment in that swirl blades 149 are also present in the radially inner channel section 43.
  • swirl blades 47 in the radially outer channel section 45 suction side and pressure side of the blades are reversed, so that the compressor air in the radially inner channel section through the compressor blades 159 a tangential component is taught, which has a reverse orientation with respect to the axial flow direction than the tangential component, which is imparted to the compressor air in the radially outer channel section 45 by the swirl blades 47 located there. Also by this measure can be avoided flashbacks.
  • the swirl vanes 149 in the radially inner passage section 43 have fuel channels 51 and fuel outlets 155 arranged to inject the fuel substantially perpendicular to the flow direction of the air flowing through the radially inner passage section 43.
  • FIG. 7 Although the swirler 231 of the third embodiment is shown in FIG. 7 is shown with a cylindrical partition wall 42, the swirl generator according to the third embodiment also be equipped with an at least partially conical partition, as has been described with reference to the second embodiment.
  • the partitions do not protrude beyond the downstream end of the respective outer wall.
  • the dividing walls can also be extended downstream, as shown in the figures, so that they protrude beyond the downstream end of the outer wall. This applies regardless of whether a partition is conical or not.
  • the relatively complex geometric shape of the swirl generator according to the described embodiments can be realized in an advantageous manner when the swirl generators are produced as castings.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
EP09155904.7A 2009-03-23 2009-03-23 Drallerzeuger, Verfahren zum Vermeiden von Flammenrückschlag in einem Brenner mit wenigstens einem Drallerzeuger und Brenner Not-in-force EP2233836B1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP09155904.7A EP2233836B1 (de) 2009-03-23 2009-03-23 Drallerzeuger, Verfahren zum Vermeiden von Flammenrückschlag in einem Brenner mit wenigstens einem Drallerzeuger und Brenner
JP2010059450A JP5615008B2 (ja) 2009-03-23 2010-03-16 スワーラおよび少なくとも１つのスワーラを備えたバーナ
CA2697200A CA2697200A1 (en) 2009-03-23 2010-03-19 Swirl generator, method for preventing flashback in a burner having at least one swirl generator and burner
RU2010110965/06A RU2535901C2 (ru) 2009-03-23 2010-03-22 Завихритель, способ предотвращения обратного удара пламени в горелке, по меньшей мере, с одним завихрителем и горелка
US12/728,518 US8789373B2 (en) 2009-03-23 2010-03-22 Swirl generator, method for preventing flashback in a burner having at least one swirl generator and burner
CN201010151559.6A CN101846320B (zh) 2009-03-23 2010-03-23 涡流发生器，在燃烧器内避免火焰反冲的方法和燃烧器
US14/263,509 US20140230448A1 (en) 2009-03-23 2014-04-28 Method for preventing flashback in a burner having at least one swirl generator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09155904.7A EP2233836B1 (de) 2009-03-23 2009-03-23 Drallerzeuger, Verfahren zum Vermeiden von Flammenrückschlag in einem Brenner mit wenigstens einem Drallerzeuger und Brenner

Publications (2)

Publication Number Publication Date
EP2233836A1 EP2233836A1 (de) 2010-09-29
EP2233836B1 true EP2233836B1 (de) 2015-07-29

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EP09155904.7A Not-in-force EP2233836B1 (de) 2009-03-23 2009-03-23 Drallerzeuger, Verfahren zum Vermeiden von Flammenrückschlag in einem Brenner mit wenigstens einem Drallerzeuger und Brenner

Country Status (6)

Country Link
US (2) US8789373B2 (zh)
EP (1) EP2233836B1 (zh)
JP (1) JP5615008B2 (zh)
CN (1) CN101846320B (zh)
CA (1) CA2697200A1 (zh)
RU (1) RU2535901C2 (zh)

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JP5615008B2 (ja) 2014-10-29
US20100236252A1 (en) 2010-09-23
RU2010110965A (ru) 2011-09-27
RU2535901C2 (ru) 2014-12-20
US20140230448A1 (en) 2014-08-21
JP2010223577A (ja) 2010-10-07
CN101846320B (zh) 2014-12-17
US8789373B2 (en) 2014-07-29

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