EP2796788A1 - Wirbelerzeuger - Google Patents

Wirbelerzeuger Download PDF

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Publication number
EP2796788A1
EP2796788A1 EP13165102.8A EP13165102A EP2796788A1 EP 2796788 A1 EP2796788 A1 EP 2796788A1 EP 13165102 A EP13165102 A EP 13165102A EP 2796788 A1 EP2796788 A1 EP 2796788A1
Authority
EP
European Patent Office
Prior art keywords
type
radially
swirler
channel wall
swirler vanes
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.)
Withdrawn
Application number
EP13165102.8A
Other languages
English (en)
French (fr)
Inventor
Fernando Biagioli
Khawar Syed
Madhavan Narasimhan Poyyapakkam
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
Priority to EP13165102.8A priority Critical patent/EP2796788A1/de
Publication of EP2796788A1 publication Critical patent/EP2796788A1/de
Withdrawn legal-status Critical Current

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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
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using 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
    • F23R3/02—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 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors

Definitions

  • the invention relates to a swirl generator for creation a swirling premixed fuel-air mixture for combustion in a gas turbine combustor comprising an annular flow channel bordered by a radially inner and outer channel wall between which a plurality of swirler vanes of a first type are uniformly distributed in a circumferential direction of the annular flow channel each of which is connected radially with the inner and outer channel wall and provides a leading and a trailing edge which are interconnected by a streamlined suction and pressure side wall.
  • Swirl generators are well known components of gas turbine combustion systems for mixing fuel and air in a burner for premixed combustion in a subsequent combustion chamber. In modern gas turbines good mixing of fuel and combustion air is a prerequisite for complete combustion with low emissions.
  • a general type of a premix burner is disclosed in EP 321 809 B1 in which the swirl generator consists of hollow part-cone bodies making up a complete body, having tangential air inlet slots and fuel channels for gaseous and liquid fuels.
  • the liquid fuel enters the interior of the burner in shape of a conical column widening in direction of flow which is surrounded by rotating stream of combustion air which flows tangentially into the burner by creating a swirling premixed fuel-air mixture for combustion in a combustor. Ignition of the premixed fuel-air mixture starts at the burner outlet at which the flame is stabilized in the region of the burner outlet by means of a back flow zone.
  • EP 2 522 911 A1 discloses also an axial swirl generator comprising a multitude of vanes being arranged in an annular housing with limiting radially inner and outer channel walls. Each vane is connected at both sides with the inner and outer channel wall providing a radial length which extends through the whole radially extension of the annular flow channel.
  • the leading edge area of each vane has a profile which is oriented parallel to a main flow direction prevailing at the leading edge position wherein the profiles of the vanes turn from the main flow direction prevailing at the leading edge position to impose a swirl on the flow.
  • the trailing edges of each vane provide lobes which contribute to an overall homogeneous mixing of the fuel-air mixture.
  • a swirl generator Regardless of the specific configuration of a generic swirl generator the primary function of a swirl generator is the creation of a swirling flow which after expansion in the combustor brakes down and creates reverse flow of hot gases, which ignite the incoming fresh mixture and stabilize the combustion. So the swirl generator contributes significantly to the quality of combustion concerning combustion efficiency, production of low emissions, pressure drop, just to name a few aspects. To comply with all these requirements a fine balance design of all components of the swirl generator is required. It has been recognized that a swirl generator design which is aero dynamical optimized in one special embodiment may loos its efficiency and reliability just by enlarging the design for example by one factor.
  • FIG 2a illustrates a schematically axial front view into an annular flow channel 2 of a swirl generator 1.
  • the annular flow channel 2 is bordered by a radially inner channel wall 3 and a radial outer channel wall 4 between which a plurality of swirler vanes 5 are uniformly distributed in circumferential direction 6 of the annular flow channel 2.
  • Each vane 5 is connected radially with the inner and outer channel wall 3, 4 and provides a radial length l 1 which is the radial distance between the inner and outer channel walls 3, 4.
  • Figure 2b additionally shows a schematically profile cross-section 7 of an aero dynamical shaped profile of the swirler vanes 5 arranged within the annular flow channel 2.
  • Each swirler vane 5 provides a leading edge 8 and a trailing edge 9 which are interconnected by a streamlined suction side wall 10 and a pressure side wall 11.
  • the interconnecting line between the leading and trailing edge 8, 9 is called chord 12. It is assumed that each swirler vane 5 is connected both sides along its entire axial extension, i.e. from the leading edge 8 to the trailing edge 9, with the inner and outer channel wall 3, 4.
  • the distance between the leading edges 8 of two neighbouring swirler vanes 5 in circumferential direction of the annular flow channel 2 at the radially inner channel wall 3 is called inner pitch p inner
  • outer pitch p outer is the distance between the leading edges 8 of two neighbouring swirler vanes 5 in circumferential direction of the annular flow channel 2 at the radially inner channel wall 3 .
  • a swirl generator 1 which is optimized under aero dynamical aspects provides a so called optimal pitch/chord-ratio at the inner channel wall which however will increase to the outer channel wall depending on the geometry of the flow channel housing to a value far from an optimum.
  • the diameter ratio of D outer /D i nner will be more than two the influence on the pitch/chord ratio between the inner and outer channel wall is not negligible.
  • annular flow through the swirl generator 1 would redistribute from areas of the flow channel 2 near the inner diameter with an optimal pitch/chord ratio to areas of the flow channel in the region of the outer diameter with large pitch in which the air flow practically remain axially.
  • It is an object of the invention to provide a swirl generator for creation a swirling premixed fuel-air mixture for combustion in a gas turbine combustor comprising an annular flow channel bordered by a radially inner and outer channel wall between which a plurality of swirler vanes of a first type are uniformly distributed in a circumferential direction of the annular flow channel each of which is connected radially with the inner and outer channel wall and provides a leading and a trailing edge which are interconnected by a streamlined suction and pressure side wall, such that negative effects on the flow dynamics and the hereto connected mixing ability may not suffer any disadvantages by enlarging the swirl generator and especially by enlarging the diameter ratio D outer / D inner more than 2, preferably more than 3.
  • the inventive swirl generator for creation a swirling premixed fuel-air mixture for combustion in a gas turbine combustor comprising the feature of the generic part of claim 1 is characterized in said between each of two adjacent swirler vanes of the first type in the circumferential direction of the annular flow channel one swirler vane of a second type is arranged. All the swirler vanes of the second type are mounted radially one sided at the outer channel wall and extents radially into the annular flow channel in form of a cantilever beam having a leading and a trailing edge which are interconnected by a stream lined suction and pressure side wall which encircle a swirler vane tip being disposed with a radially distance to the radially inner channel wall.
  • the swirler vanes of the first type provide a radially length l 1 which corresponds to the radial distance between the radially inner and outer channel wall and the swirler vanes of the second type provide a radially length l 2 which is basically less than l 1 but preferably half of the size of l 1 or less than half of l 1 .
  • each swirler vane of the second type provides a plan surface with corresponds to the profile cross-section oriented orthogonal to the radial extension of the swirler vane of the second type.
  • All the surfaces of the vane tips of the swirler vanes of the second type lies in a common virtually separation plane in form of a cylinder wall which separates the flow channel into two co-axial flow zones virtually.
  • the radially inner flow zone ranging radially from the inner channel wall to the virtually separation plane on which the vane tips of the swirler vanes of the second type lie, and a radially outer flow zone ranging radially from the virtually separation plane to the radially outer channel wall.
  • each of the swirler vanes of the first and second type a multitude of fuel nozzles on the suction and/or pressure side wall is arranged to inject fuel into the flow area of the annular flow channel.
  • the number and arrangement of the fuel nozzles along the suction and/or pressure side walls of the swirler vanes of the first and second type are chosen with the provision of an optimized fuel-air mixing quality after passing the swirled premixed fuel-air mixture the swirl generator.
  • the fuel injection can be inventively optimized for creation of a defined radial profile of fuel equivalence ratio in a mixing tube following the swirl generator as well at the flame front inside the combustor which follows the swirl generator directly or follows the mixing tube. Due to the different length of the swirler vanes of the first and second type a possibility is given for radial staging which means a controlled variation of equivalence ratio between the inner and outer flow zone of the two coaxial flow zones. Especially it is possible to reach flow behaviour through the swirler generator after steps of aero dynamical optimization such that the radial flow velocity at the virtually border between the two radial flow zones especially at the swirler exit is zero, so that no mixing between the two zones occurs.
  • Figure 1 shows a schematically axial view of an inventive swirl generator 1 providing an annular flow channel 2 bordered by a radially inner channel wall 3 and a radially outer channel wall 4.
  • a plurality of swirler vanes 5 of a first type is uniformly distributed in the circumferential direction 6 of the annular flow channel 2 each of which is connected radially with the inner and outer channel wall 3, 4 and provides a leading and trailing edge 8, 9 which are interconnected by a streamlined suction and pressure side wall 10, 11 which is shown in the before described figure 2b .
  • one swirler vane 13 of the second type is arranged providing a radially length l 2 which is shorter than the radially length l 1 of the swirler vane 5 of the first type.
  • the swirler vane 13 of the second type is mounted radially one sided at the outer channel wall 4 and extends radially into the annular flow channel 2 in form of a cantilever beam having a swirler vane tip 14 ending freely and facing the radially inner channel wall with a radially distance.
  • all the swirler vanes 13 of the second type do have the same aero dynamical shaped profile and chord length like the swirler vanes of the first type but differ in radial length from the swirler vanes 5 of the first type.
  • the aero dynamical profile of the swirler vanes of the first and second type are constant along their radial extension but may differ in other embodiments for purposes of aero dynamical optimization.
  • the outer pitch p outer which is the azimuthally distance between two neighbouring vanes 5, 13 of the first and second type is significantly smaller than the outer pitch p* outer corresponding to the distance between two neighbouring swirler vanes of the fist type, see the dotted arrow. Due to the introduction of the swirler vanes of the second type 13 with reduced radially length l 2 between the long vanes 5 only in the radially outer part of the flow channel 2, where the pitch starts to be unacceptably large, the pitch/chord-ratio is reduced significantly and more or less adapted to the pitch/chord-ratio at the inner channel wall.
  • the dotted circular line relates to a virtually separation plane 15 along which the axially flow channel 2 is separated into two coaxial flow zones 2.1 and 2.2.
  • the radially inner flow zone 2.1 ranges radially from the inner channel wall 3 to the virtually separation plane 15 along which the swirler vane tips 14 of the swirler vanes of the second type 13 lie.
  • the radially outer flow zone 2.2 ranges radially from the virtually separation plane 15 to the radially outer channel wall 4.
  • Figure 3a show the perspective view to the swirler inlet and figure 3b shows the perspective view to the swirler exit.
  • Swirler components which are already explained are labelled with the known reference numbers without repeating explanation.
  • the swirler vanes 13 of the second type provide a free ending swirler vane tip 14 which is a plane surface having the contour of the profile cross section of the vane.
  • the radially length l 2 of the swirler vane of the second type 13 is more or less half of the length l 1 of the swirler vanes 5 of the first type but can vary according to shape and size of a swirler embodiment.
  • Figures 4a shows an axially front view into the swirl generator 1.
  • Figure 4b shows a side view on the swirler vane 1.
  • the inventive implementation of additional swirler vanes with a shorter length l 2 between a multitude of swirler vanes 5 with long length l 1 becomes relevant for swirl generators having a geometrical size in which the diameter ratio D outer /D inner is significantly larger than 2, preferably larger than 3.
  • FIG. 4a shows the inner pitch p inner and the outer pitch p* outer in case of the swirler vanes of the first type with full length l 1 .
  • the outer pitch p outer is reduced clearly and nearly adapted to the inner pitch p inner .
  • the pitch/chord-ratio between the inner and outer flow region is nearly similar because the length of the chord 12 of the swirler vanes of the first and second type is the same.
  • Figure 5 shows a perspective view on two adjacent swirler vanes 5 and 13.
  • a multitude of fuel nozzles 16 is arranged linearly along a radial direction with equal distance between two neighbouring fuel nozzles 16.
  • the linearly arrangement of the fuel nozzles 16 of each vane provides a distance d to the leading edge 8 of at least a quarter of the length of the chord 12. Due to the fact that the fuel nozzles 16 are also placed at the swirler vanes 13 of the second type with the reduced length l 2 an increased number of fuel nozzles 16 in the outer part of the annular flow channel is present so that the requirement on the fuel jet penetration depth decreases.
  • the swirl generator is part of a premix burner comprising a fuel lance providing a diameter which is adapted to the inner diameter D inner of the radially inner channel wall 3.
  • the radially outer channel wall 4 comprises a diameter D outer which corresponds to a diameter of a mixing tube following downstream to that swirl generator which may merge into a combustor of a gas turbine.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13165102.8A 2013-04-24 2013-04-24 Wirbelerzeuger Withdrawn EP2796788A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13165102.8A EP2796788A1 (de) 2013-04-24 2013-04-24 Wirbelerzeuger

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13165102.8A EP2796788A1 (de) 2013-04-24 2013-04-24 Wirbelerzeuger

Publications (1)

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EP2796788A1 true EP2796788A1 (de) 2014-10-29

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EP13165102.8A Withdrawn EP2796788A1 (de) 2013-04-24 2013-04-24 Wirbelerzeuger

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EP (1) EP2796788A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3296462B1 (de) 2016-09-16 2018-09-05 Benninghoven GmbH & Co.KG Mülheim Anlage und verfahren zum herstellen von asphalt
CN110440286A (zh) * 2019-07-26 2019-11-12 中国航发沈阳发动机研究所 一种用于预混气态燃料的旋流装置
CN110440288A (zh) * 2019-07-26 2019-11-12 中国航发沈阳发动机研究所 一种用于预混气态燃料的进气装置

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809B1 (de) 1987-12-21 1991-05-15 BBC Brown Boveri AG Verfahren für die Verbrennung von flüssigem Brennstoff in einem Brenner
EP1096201A1 (de) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Brenner
US20070028624A1 (en) * 2005-07-25 2007-02-08 General Electric Company Mixer assembly for combustor of a gas turbine engine having a plurality of counter-rotating swirlers
US20090183511A1 (en) 2008-01-18 2009-07-23 General Electric Company Swozzle design for gas turbine combustor
US20100095675A1 (en) * 2008-10-17 2010-04-22 General Electric Company Combustor Burner Vanelets
US20110023494A1 (en) * 2009-07-28 2011-02-03 General Electric Company Gas turbine burner
EP2522911A1 (de) 2011-05-11 2012-11-14 Alstom Technology Ltd Gelappter Verwirbeler

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321809B1 (de) 1987-12-21 1991-05-15 BBC Brown Boveri AG Verfahren für die Verbrennung von flüssigem Brennstoff in einem Brenner
EP1096201A1 (de) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Brenner
US20070028624A1 (en) * 2005-07-25 2007-02-08 General Electric Company Mixer assembly for combustor of a gas turbine engine having a plurality of counter-rotating swirlers
US20090183511A1 (en) 2008-01-18 2009-07-23 General Electric Company Swozzle design for gas turbine combustor
US20100095675A1 (en) * 2008-10-17 2010-04-22 General Electric Company Combustor Burner Vanelets
US20110023494A1 (en) * 2009-07-28 2011-02-03 General Electric Company Gas turbine burner
EP2522911A1 (de) 2011-05-11 2012-11-14 Alstom Technology Ltd Gelappter Verwirbeler

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3296462B1 (de) 2016-09-16 2018-09-05 Benninghoven GmbH & Co.KG Mülheim Anlage und verfahren zum herstellen von asphalt
CN110440286A (zh) * 2019-07-26 2019-11-12 中国航发沈阳发动机研究所 一种用于预混气态燃料的旋流装置
CN110440288A (zh) * 2019-07-26 2019-11-12 中国航发沈阳发动机研究所 一种用于预混气态燃料的进气装置

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