EP2211109A1 - Brûleur de turbine à gaz et procédé pour mélanger un carburant avec un flux gazeux - Google Patents

Brûleur de turbine à gaz et procédé pour mélanger un carburant avec un flux gazeux Download PDF

Info

Publication number
EP2211109A1
EP2211109A1 EP09151189A EP09151189A EP2211109A1 EP 2211109 A1 EP2211109 A1 EP 2211109A1 EP 09151189 A EP09151189 A EP 09151189A EP 09151189 A EP09151189 A EP 09151189A EP 2211109 A1 EP2211109 A1 EP 2211109A1
Authority
EP
European Patent Office
Prior art keywords
duct
burner
fuel
nozzles
airfoil
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Withdrawn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
EP09151189A
Other languages
German (de)
English (en)
Inventor
Andrea Ciani
Adnan Eroglu
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 EP09151189A priority Critical patent/EP2211109A1/fr
Publication of EP2211109A1 publication Critical patent/EP2211109A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F23R3/28—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
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing

Definitions

  • the present invention relates to a burner of a gas turbine and a method for mixing the fuel with a gaseous flow.
  • the present invention refers to a burner wherein the fuel is injected in a hot gases flow and spontaneously auto ignites after a delay time from injection.
  • Burners wherein auto ignition of fuel occurs are typically the second burners of sequential combustion gas turbines.
  • a compressor compresses a main air flow and feeds it to a first burner where a fuel is injected to generate a mixture. Afterwards the mixture is combusted and then expanded in a high pressure turbine. The hot gases flow coming from the high pressure turbine (that are still rich in oxygen) pass through a second burner where further fuel is injected to form a mixture. This mixture is combusted and then expanded in a low pressure turbine.
  • the second burner of the sequential combustion gas turbine has a duct (often square, quadrangular or trapezoidal in shape) enclosing four static vortex generators made of tetraedrical elements connected to the walls of the duct.
  • the burner Downstream of the vortex generators the burner has a lance made of a straight tubular element placed perpendicularly to the direction of the hot gases flow and provided with a terminal portion that is parallel to the direction of the hot gases flow.
  • the terminal portion has usually four nozzles that inject the fuel.
  • the hot gases flow passes trough the vortex generators increasing its vorticity; afterwards the fuel is injected such that it mixes with the hot gases flow.
  • US2008/0148736 discloses a burner that has a duct containing a rotating hub.
  • the rotating hub has airfoils that are provided, in a zone close to their leading edges, with nozzles for injecting the fuel.
  • the hub generates a wake that causes pressure drop, bad mixing (with high NOx emissions) and high flashback risks.
  • the technical aim of the present invention is therefore to provide a burner and a method by which the said problems of the known art are eliminated.
  • an object of the invention is to provide a burner and a method with which mixing quality is improved and the NOx emissions are reduced.
  • Another object of the invention is to provide a burner and a method by which the pressure drop is reduced.
  • a further object of the present invention is to provide a burner and a method which let the risk of auto ignition of the fuel within the burner (flashback) be greatly reduced.
  • the burner 1 is the second burner of a sequential gas turbine and has a duct 2 that has a circular cross section and comprises a vortex generator 3 and, downstream of it, a plurality of nozzles 5 for injecting a fuel within the duct 2.
  • the nozzles 5 are of hybrid type and in this respect they are arranged to inject oil (from a central aperture), gas (from an intermediate annular aperture encircling the central aperture) and shielding air (from an outer annular aperture encircling the central and the intermediate annular aperture).
  • the nozzles 5 are arranged along the wall of the duct 2 and, in addition, are arranged for injecting fuel toward the inner of the duct 2.
  • the nozzles 5 have their axes 6 toward a longitudinal axis 7 the duct 2.
  • the nozzles 5 are located on a lance 9 that is annular (i.e. toroidal) in shape and is housed in the duct 2 with a portion lying on the wall of the same duct 2, and with its central aperture facing the vortex generator 3 such that the hot gases flow may pass through it.
  • a lance 9 that is annular (i.e. toroidal) in shape and is housed in the duct 2 with a portion lying on the wall of the same duct 2, and with its central aperture facing the vortex generator 3 such that the hot gases flow may pass through it.
  • the duct 2 is provided with a longitudinal aperture 11 such that the lance 9 can be introduced within the duct 2 via this longitudinal aperture 11 and subsequently (once it is inside the duct 2) rotated to be transversal housed within the duct 2 (i.e. to be placed in its operating conditions as shown in figure 3 ).
  • the duct is provided with a transversal aperture for letting the lance 9 be inserted within the duct 2.
  • the vortex generator 3 comprises an airfoil 13 rotating about the longitudinal axis 7 of the duct 2.
  • the airfoil 13 has a leading edge 15 (with 0 angle of attack) and a trailing edge 16 that are tilted with each other.
  • leading edge 15 of the airfoil 13 lay radially within the duct 2 and the trailing edge 16 of the airfoil 13 is straight but not radial within the duct 2.
  • Figure 6 shows a central cross section of the airfoil 13; this central cross section is symmetrical with respect to the rotation axis of the airfoil that overlaps the longitudinal axis 7 of the duct 2; moreover also the cord 18 of the airfoil (i.e. the line between the leading edge 15 and the trailing edge 16) overlaps the longitudinal axis 7 of the duct 2.
  • the other sections are not symmetric but, as the leading edge 15 and the trailing edge 16 are both straight but tilted with each other, they have the cord 18 that is tilted with respect to the rotation axis of the airfoil (this axis overlaps the axis 7).
  • each longitudinal section of the airfoil i.e. the cross section similar to that of figures 6-7
  • the cross sections in each longitudinal section of the airfoil has the angle between the rotational axis of the airfoil (overlapping the axis 7) and the cord 18 that increases with the distance from the rotation axis.
  • the duct 2 has an inlet portion 19 that is convergent; the inlet portion is preferably made of a trapezoidal cross section at its larger end (this is due to the fact that the flow comes from the high pressure turbine) and a circular cross section at its smaller end.
  • the outlet portion 20 has a diffuser.
  • the hot gases flow coming from the high pressure turbine enters the duct 2 through the convergent inlet portion 19; in this zone of the duct the hot gases flow is straightened and stabilised.
  • the hot gases flow passes around the rotating airfoil that makes it increase its vorticity by generating a vortex that rotates about the longitudinal axis 7 of the duct 2 (see arrows F).
  • the hot gases flow (rotating about the axis 7) passes through the lance 9, and the nozzles 5 inject the gaseous or liquid fuel (i.e. the gas or the oil eventually with the shielding air) according to the operating stage.
  • the gaseous or liquid fuel i.e. the gas or the oil eventually with the shielding air
  • the fuel (both liquid and gaseous fuel) is injected from a plurality of nozzles (in the embodiment shown the nozzles 5 are eight in number, but in different embodiments the nozzles can also be much more than eight, for example sixteen or even more); the great number of nozzles and the fact that they are placed along all the perimeter of the duct and also the fact that the fuel is injected toward the inner of the duct lets the fuel be distributed in the whole cross section of the duct 2.
  • the rotating velocity of the hot gases flow and the velocity of the fuel injected toward the centre of the duct 2 are such that while the hot gases flow rotate of an angle A between two next nozzles 5, the fuel goes from the nozzle 5 to the axis 7 of the duct 2; this further increases fuel distribution over the whole cross section of the duct 2.
  • the zone of the hot gases flow having the lowest velocity i.e. the zone along the axis 7 of the duct
  • this improves flashback margin
  • the hot gases flow flows within the duct 2 up to the exit 2 and the entrance of the combustion chamber where the fuel is combusted; in the zone between the lance and the combustion chamber (mixing zone) the hot gases flow further mixes with the fuel to achieve an optimal mixing quality.
  • the present invention also relates to method for mixing a fuel with a gaseous flow passing through the duct of the burner of the gas turbine.
  • the method comprises generating at least a vortex within the gaseous flow and radially injecting a fuel toward the inner of the duct.
  • the vortices are generated making the gaseous flow rotate around the axis 7 of the duct 2 and, during rotation, while the gas flow sweep an angle A between two next nozzles 5, the fuel sweeps the distance B between the nozzle 5 from which it was injected and the axis 7 of the duct 2.
  • figure 10 shows a different vortex generator that could be used in the burner 1 of the invention.
  • the vortex generator of figure 10 is made of two airfoils 13 each having the features of the airfoil already described.
  • These airfoils 13 have the leading edges at right angle with each other and the trailing edges tilted in the same direction with respect to the leading edges.
  • the burner provided with this vortex generator having two airfoils has the same operation already described for the burner with vortex generator with one single airfoil.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP09151189A 2009-01-23 2009-01-23 Brûleur de turbine à gaz et procédé pour mélanger un carburant avec un flux gazeux Withdrawn EP2211109A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09151189A EP2211109A1 (fr) 2009-01-23 2009-01-23 Brûleur de turbine à gaz et procédé pour mélanger un carburant avec un flux gazeux

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09151189A EP2211109A1 (fr) 2009-01-23 2009-01-23 Brûleur de turbine à gaz et procédé pour mélanger un carburant avec un flux gazeux

Publications (1)

Publication Number Publication Date
EP2211109A1 true EP2211109A1 (fr) 2010-07-28

Family

ID=40790686

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09151189A Withdrawn EP2211109A1 (fr) 2009-01-23 2009-01-23 Brûleur de turbine à gaz et procédé pour mélanger un carburant avec un flux gazeux

Country Status (1)

Country Link
EP (1) EP2211109A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2420731A1 (fr) * 2010-08-16 2012-02-22 Alstom Technology Ltd Brûleur post-combustion
EP2644997A1 (fr) 2012-03-26 2013-10-02 Alstom Technology Ltd Agencement de mélange pour mélanger un combustible avec un flux de gaz contenant de l'oxygène
US9046265B2 (en) 2010-08-16 2015-06-02 Alstom Technology Ltd Reheat burner
EP2933559A1 (fr) 2014-04-16 2015-10-21 Alstom Technology Ltd Agencement de mélange de carburant et chambre de combustion avec un tel agencement
EP2957835A1 (fr) 2014-06-18 2015-12-23 Alstom Technology Ltd Procédé de recirculation des gaz d'échappement provenant d'une chambre de combustion d'un brûleur d'une turbine à gaz et turbine à gaz pour l'exécution de ce procédé
CN105627369A (zh) * 2014-11-26 2016-06-01 通用电器技术有限公司 燃气涡轮的焚烧器
US10094570B2 (en) 2014-12-11 2018-10-09 General Electric Company Injector apparatus and reheat combustor
US10094571B2 (en) 2014-12-11 2018-10-09 General Electric Company Injector apparatus with reheat combustor and turbomachine
US10094569B2 (en) 2014-12-11 2018-10-09 General Electric Company Injecting apparatus with reheat combustor and turbomachine
US10107498B2 (en) 2014-12-11 2018-10-23 General Electric Company Injection systems for fuel and gas

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3002634A1 (de) * 1980-01-25 1981-07-30 Albert 2400 Lübeck Diesenberger Vorrichtung zum oeffnen und schliessen des abgaskanales eines heizkessels
US5647200A (en) * 1993-04-08 1997-07-15 Asea Brown Boveri Ag Heat generator
EP0935095A2 (fr) * 1998-02-09 1999-08-11 Mitsubishi Heavy Industries, Ltd. Chambre de combustion pour turbine à gaz
DE19948673A1 (de) * 1999-10-08 2001-04-12 Asea Brown Boveri Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens
GB2398375A (en) * 2003-02-14 2004-08-18 Alstom A mixer for two fluids having a venturi shape
EP1462716A1 (fr) * 2003-03-24 2004-09-29 Riello S.p.a. Mélangeur air/gas combustible pour un brûleur à prémélange, et système de combustion avec un tel mélangeur
US20050178104A1 (en) * 2002-09-13 2005-08-18 Schmotolocha Stephen N. Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance
EP1716918A1 (fr) * 2005-04-28 2006-11-02 Hitachi, Ltd. Dispositif mélangeur pour fluides
US20080148736A1 (en) 2005-06-06 2008-06-26 Mitsubishi Heavy Industries, Ltd. Premixed Combustion Burner of Gas Turbine Technical Field

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3002634A1 (de) * 1980-01-25 1981-07-30 Albert 2400 Lübeck Diesenberger Vorrichtung zum oeffnen und schliessen des abgaskanales eines heizkessels
US5647200A (en) * 1993-04-08 1997-07-15 Asea Brown Boveri Ag Heat generator
EP0935095A2 (fr) * 1998-02-09 1999-08-11 Mitsubishi Heavy Industries, Ltd. Chambre de combustion pour turbine à gaz
DE19948673A1 (de) * 1999-10-08 2001-04-12 Asea Brown Boveri Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens
US20050178104A1 (en) * 2002-09-13 2005-08-18 Schmotolocha Stephen N. Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance
GB2398375A (en) * 2003-02-14 2004-08-18 Alstom A mixer for two fluids having a venturi shape
EP1462716A1 (fr) * 2003-03-24 2004-09-29 Riello S.p.a. Mélangeur air/gas combustible pour un brûleur à prémélange, et système de combustion avec un tel mélangeur
EP1716918A1 (fr) * 2005-04-28 2006-11-02 Hitachi, Ltd. Dispositif mélangeur pour fluides
US20080148736A1 (en) 2005-06-06 2008-06-26 Mitsubishi Heavy Industries, Ltd. Premixed Combustion Burner of Gas Turbine Technical Field

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9057518B2 (en) 2010-08-16 2015-06-16 Alstom Technology Ltd. Reheat burner
JP2012042200A (ja) * 2010-08-16 2012-03-01 Alstom Technology Ltd 再加熱バーナー
EP2420731A1 (fr) * 2010-08-16 2012-02-22 Alstom Technology Ltd Brûleur post-combustion
EP2420730A3 (fr) * 2010-08-16 2015-06-24 Alstom Technology Ltd Brûleur de post-combustion
RU2550294C2 (ru) * 2010-08-16 2015-05-10 Альстом Текнолоджи Лтд Горелка промежуточного подогрева
US9046265B2 (en) 2010-08-16 2015-06-02 Alstom Technology Ltd Reheat burner
US9822981B2 (en) 2012-03-26 2017-11-21 Ansaldo Energia Switzerland AG Mixing arrangement for mixing a fuel with a stream of oxygen containing gas
WO2013143983A2 (fr) 2012-03-26 2013-10-03 Alstom Technology Ltd Système mélangeur servant au mélange d'un carburant comprenant un flux de gaz contenant de l'oxygène
EP2644997A1 (fr) 2012-03-26 2013-10-02 Alstom Technology Ltd Agencement de mélange pour mélanger un combustible avec un flux de gaz contenant de l'oxygène
EP2933559A1 (fr) 2014-04-16 2015-10-21 Alstom Technology Ltd Agencement de mélange de carburant et chambre de combustion avec un tel agencement
EP2957835A1 (fr) 2014-06-18 2015-12-23 Alstom Technology Ltd Procédé de recirculation des gaz d'échappement provenant d'une chambre de combustion d'un brûleur d'une turbine à gaz et turbine à gaz pour l'exécution de ce procédé
CN105627369A (zh) * 2014-11-26 2016-06-01 通用电器技术有限公司 燃气涡轮的焚烧器
EP3026344A1 (fr) * 2014-11-26 2016-06-01 Alstom Technology Ltd Brûleur d'une turbine à gaz
US10215416B2 (en) 2014-11-26 2019-02-26 Ansaldo Energia Switzerland AG Burner of a gas turbine with a lobed shape vortex generator
CN105627369B (zh) * 2014-11-26 2020-06-05 安萨尔多能源瑞士股份公司 燃气涡轮的焚烧器
US10094570B2 (en) 2014-12-11 2018-10-09 General Electric Company Injector apparatus and reheat combustor
US10094571B2 (en) 2014-12-11 2018-10-09 General Electric Company Injector apparatus with reheat combustor and turbomachine
US10094569B2 (en) 2014-12-11 2018-10-09 General Electric Company Injecting apparatus with reheat combustor and turbomachine
US10107498B2 (en) 2014-12-11 2018-10-23 General Electric Company Injection systems for fuel and gas

Similar Documents

Publication Publication Date Title
EP2211109A1 (fr) Brûleur de turbine à gaz et procédé pour mélanger un carburant avec un flux gazeux
EP3182013B1 (fr) Brûleur pour une chambre de combustion sequentielle
EP2685164B1 (fr) Dispositif de tourbillonnement axial pour brûleur de turbine à gaz
EP2496884B1 (fr) Système d'injection de brûleur de postcombustion
EP2496880B1 (fr) Système d'injection pour brûleur de réchauffage
US9360221B2 (en) Gas turbine burner
EP2522912A1 (fr) Redresseur de flux et mélangeur
EP2522911A1 (fr) Gérérateur de vortex à lobes
JP2010223577A (ja) スワーラ、少なくとも１つのスワーラを備えたバーナにおける逆火の防止方法およびバーナ
JP2010223577A6 (ja) スワーラ、少なくとも１つのスワーラを備えたバーナにおける逆火の防止方法およびバーナ
EP2722591A1 (fr) Brûleur à multiples cones pour une turbine à gaz
EP3236157A1 (fr) Générateur de tourbillonnement pour mélanger un combustible avec de l'air dans un moteur à combustion
EP3486569B1 (fr) Turbine à gaz pour centrale électrique
EP2420731B1 (fr) Brûleur post-combustion
EP2905535A1 (fr) Chambre à combustion
CN109312924A (zh) 燃气涡轮发动机的燃烧器组件
US10215416B2 (en) Burner of a gas turbine with a lobed shape vortex generator
CN108869041B (zh) 用于燃气轮机的前端转向勺状件
EP2796788A1 (fr) Générateur de tourbillon
EP2420730B1 (fr) Brûleur de post-combustion
EP3564585A1 (fr) Agencement tourbillonnaire d'un brûleur
EP2253888A1 (fr) Brûleur d'une turbine à gaz
KR20220111959A (ko) 분사노즐, 연소기 및 이를 포함하는 가스터빈
CN116412418A (zh) 发动机燃料喷嘴和旋流器

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA RS

AKY No designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: R108

Effective date: 20110309

Ref country code: DE

Ref legal event code: 8566

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20100129