EP3486567A1 - Rohrbrenner für eine gasturbine und gasturbine mit solch einem rohrbrenner - Google Patents

Rohrbrenner für eine gasturbine und gasturbine mit solch einem rohrbrenner Download PDF

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Publication number
EP3486567A1
EP3486567A1 EP18206586.2A EP18206586A EP3486567A1 EP 3486567 A1 EP3486567 A1 EP 3486567A1 EP 18206586 A EP18206586 A EP 18206586A EP 3486567 A1 EP3486567 A1 EP 3486567A1
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EP
European Patent Office
Prior art keywords
combustor
liner
damper
damper body
cooling
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
Application number
EP18206586.2A
Other languages
English (en)
French (fr)
Other versions
EP3486567B1 (de
Inventor
Mirko Ruben Bothien
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Ansaldo Energia Switzerland AG
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Publication date
Application filed by Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Publication of EP3486567A1 publication Critical patent/EP3486567A1/de
Application granted granted Critical
Publication of EP3486567B1 publication Critical patent/EP3486567B1/de
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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
    • F23R3/002—Wall structures
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03342—Arrangement of silo-type combustion chambers

Definitions

  • the present invention relates to a can combustor for a gas turbine for power plants.
  • the present invention relates to a can combustor provided with a damper.
  • the present invention refers to a gas turbine for power plants comprising the above mentioned can combustor.
  • a gas turbine for power plants comprises a rotor provided with an upstream compressor sector, a combustor sector and a downstream turbine sector.
  • the terms downstream and upstream refer to the direction of the main gas flow passing through the gas turbine.
  • the compressor comprises an inlet supplied with air and a plurality of blades compressing the passing air.
  • the compressed air leaving the compressor flows into a plenum, i.e. a closed volume delimited by an outer casing, and from there into the combustor.
  • a plenum i.e. a closed volume delimited by an outer casing
  • the compressed air is mixed with at least one fuel.
  • the mixture of fuel and compressed air flows into a combustion chamber inside the combustor where this mixture are combusted.
  • the resulting hot gas leaves the combustor and is expanded in the turbine performing work on the rotor.
  • a sequential gas turbine comprises two combustors in series wherein each combustor is provided with the relative burner and combustion chamber. Following the main gas flow direction, the upstream combustor is called “premix” combustor and is fed by the compresses air. The downstream combustor is called “sequential” or “reheat” combustor and is fed by the hot gas leaving the first combustion chamber.
  • the two combustors are physically separated by a stage of turbine blades, called high pressure turbine.
  • this first kind of sequential gas turbines comprises a compressor, a first combustor, a high-pressure turbine, a second combustor and a low-pressure turbine.
  • the compressor and the two turbines may be connected to a common rotor rotating around an axis and surrounded by a concentric casing.
  • the sequential liner and the picture frame are realized as a single piece called transition duct configured for guiding the hot gas leaving the combustor toward the turbine, in particular toward the first vane of the turbine.
  • the reheat burner can be realized in form of a plurality of single or dual fuel injector fingers extending across the flow channel.
  • these injector fingers can be realized in form of a streamline body having preferably a lobed trailing edge.
  • pressure oscillations may be generated that could cause mechanical damages and limit the operating regime.
  • gas turbines have to operate in lean mode for compliance to pollution emissions.
  • the burner flame during this mode of operation is extremely sensitive to flow perturbations and can easily couple with dynamics of the combustion chamber to lead to thermo-acoustic instabilities. For this reason, usually combustion chambers are provided with damping devices, in order to damp these pressure oscillations.
  • a traditional damper comprises a damper volume that acts as a resonator volume and a neck fluidly connecting the damper volume to the combustion chamber.
  • US8490744 discloses an annular damper as above described.
  • US8490744 discloses a can combustor for a gas turbine having a single stage of combustion wherein the can combustor comprises a burner, a liner arranged downstream the burner and defining an inner combustion chamber and a damper comprising a damper volume wrapped outside the liner and in fluidly connections with the combustion chamber.
  • the inner wall of the damper volume corresponds to the liner and the damper necks collapse in a plurality of through holes provided in the liner.
  • a primary object of the present invention is to provide a can combustor provided with a new damper wrapped around the liner.
  • the present invention provides a can combustor for a gas turbine comprising:
  • the above mentioned damper can be considered as a resonator device or acoustic damper.
  • the can combustor may be provided with a single stage of combustion or two stages of combustion arranged in series.
  • the can combustor comprises a burner followed downstream by a liner defining the combustion chamber and guiding the hot gas flow toward the turbine.
  • the term downstream refers to the hot gas main flow direction.
  • the cross-section of the liner defining the combustion chamber may be circular or square/rectangular.
  • the damper body is annular and arranged spaced from the liner, i.e. the damper body has an inner surface facing the outer surface of the liner, in order to create a cooling gap or channel between the damper body and the liner.
  • this cooling gap between the liner and the damper body at least a damper neck is present acting as a bridge for fluidly connecting the damping volume with the combustion chamber.
  • the cooling gap between the damper body and the liner is provided with a cooling device, for instance a plurality of trip strips or turbolator elements or other different kinds of cooling device.
  • This cooling device may be placed on the outer surface of the liner and/or on the inner wall of the damper body.
  • the ends of the damper neck may be in flush with the liner and/or the damper body or alternatively may protrude at least in part inside the combustion chamber and/or in the damping volume.
  • inner refers to the combustor axis.
  • this cooling air is the compressed air delivered in the plenum by the compressor
  • the purge air passing through the damper body may be independently adjusted without impacting the liner cooling.
  • a dumper purge air reduction for instance applied for optimizing the damping effect, does not involve any detrimental effect on the liner cooling.
  • the damper body may wrap the liner completely or only in part.
  • the damper body wraps the liner completely and the damping volume can be divided in a plurality of sub-volumes.
  • the damper may comprises a plurality of damper necks connecting the combustion chamber with the damping volume.
  • the damper comprises at least a purge air inlet configured for entering purge air in the damping volume.
  • the purge air inlet may be located on the outer wall of the damper body or on the inner wall of the damper body facing the liner.
  • the purge air inlet may be located between the damper neck and the damper body. In this case, part of the cooling air passing through the cooling gap enters into the damping volume acting as purge air.
  • the can combustor is a sequential can combustor and comprises in series a first burner, a first liner defining a first combustion chamber, a subsequent burner and a subsequent liner defining a subsequent combustion chamber.
  • the damper is associated at least to the subsequent liner.
  • the present invention refers also to a gas turbine for power plants comprising such a can combustor wherein preferably this can combustor is a sequential can combustor.
  • FIG. 1 is a schematic view of a gas turbine for power plants that can be provided with a can combustor according to the present invention.
  • a gas turbine 1 having an axis 9 and comprising a compressor 2, a combustor sector 4 and a turbine 3.
  • ambient air 10 enters the compressor 2 and compressed air leaves the compressor 2 and enters in a plenum 16, i.e. a volume defined by an outer casing 17.
  • the compressed air 37 enters in the combustor that comprises a plurality of can combustors 4 annularly arranged as ring around the axis 9.
  • each can combustor 4 involves a single stage of combustion and comprises a burner 5 where the compressed air 37 is mixed with at least a fuel. This mixture is then combusted in a combustion chamber 6 and the resulting hot gas flows toward a downstream turbine 3.
  • the combustion chamber 6 is limited by a liner 7.
  • the turbine 3 comprises a plurality of vanes 12, i.e. stator blades, supported by a vane carrier 14, and a plurality of blades 13, i.e. rotor blades, supported by a rotor 8.
  • the hot gas expands performing work on the rotor 8 and leaves the turbine 3 in form of exhaust gas 11.
  • figure 2 is schematic view of a different kind of can combustor that can be improved according the present invention.
  • a can combustor 4 having two stages of combustion in series and housed in a relative portal hole of an outer casing 17 defining the plenum 16 where the compresses air are delivered by the compressor 2.
  • the can combustor 4 has an axis 24 and comprises in series along the gas flow M a first combustor, or premix combustor 18, and a second combustor, or sequential combustor 19.
  • the first combustor 18 comprises a first or premix burner 20 and a first combustion chamber 21.
  • the sequential combustor 19 comprises a sequential burner 22 and a second combustion chamber 23.
  • the burner axis 24 is parallel to the gas flow direction M and the sequential burner 22 may comprise a plurality of fuel injectors, in particular dual fuel and carrying air injectors.
  • the fuel is fed to the sequential burner 22 by a fuel lance 25 axially extending outside the first combustion chamber 21 up to the sequential burner 22.
  • the combustion chambers 21 23 are delimited by a liner 7.
  • the premix combustion chamber 21 is limited by an upstream portion of the liner 7 and the sequential combustion chambers 21 by a sequential liner 26 that is part of a transition duct 27 for guiding the hot gas toward the turbine.
  • FIGS. 3-7 are schematic views of two alternative embodiments of the present invention.
  • the reference number 7 refers to a liner in general and therefore may correspond to the single liner 7 of the can combustor 4 of figure 1 but also to the sequential liner 26 of figure 2 .
  • the reference number 6 refers to a combustion chamber in general and therefore may correspond to the combustion chamber 6 of the can combustor 4 of figure 1 but also to the sequential combustion chamber 23 of figure 2 .
  • Figures 3-7 disclose an annular damper 28 comprising a damper body 29 defining a damping volume 30 that is wrapped outside around the liner 7.
  • the damper body 28 is spaced from the liner 7 in order to form a cooling gap 31 between the damper body 29 and the liner 7.
  • the reference C in figures 3-7 refers to a cooling air, i.e. the compressed air delivered by the compressor in the plenum, passing in the cooling gap 31.
  • a damper neck 32 connects the damping volume 30 with the combustion chamber 6 and acts as a bridge in the cooling gap 31 between the liner 7 and the damper body 29.
  • the damper neck 32 may be welded to the liner 7 and the damper body 29 is connected or integral with the damper neck 32.
  • the damper purge air P enters the damping volume 30 passing through a purge air inlet 33 realized on the outer wall of the damper body 29. Therefore, in this embodiment the purge air flow P is decoupled from the cooling air C passing through the cooling gap 31.
  • the purge air inlet is realized in form of a gap 34 realized between the damper neck 32 and the damper body 29.
  • part of the cooling air C passing through the cooling gap 31 enters the damping volume 30 becomes the purge air P. Therefore, in this embodiment part of cooling air C passing through the cooling gap 31 enters the damping volume 30 acting as purge air flow P.
  • the figure 7 discloses an embodiment that can be considered as a hybrid of the foregoing embodiments of figures 4 and 6 .
  • the embodiment of figure 7 is provided with two purge air inlets 33, 34 wherein the first purge air inlet 34 is located between the damper neck 32 and the damper body 29 and the second purge air inlet 33 is located on the outer wall of the damper body 29.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP18206586.2A 2017-11-15 2018-11-15 Rohrbrenner für eine gasturbine und gasturbine mit solch einem rohrbrenner Active EP3486567B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17201899 2017-11-15

Publications (2)

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EP3486567A1 true EP3486567A1 (de) 2019-05-22
EP3486567B1 EP3486567B1 (de) 2022-01-26

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EP18206586.2A Active EP3486567B1 (de) 2017-11-15 2018-11-15 Rohrbrenner für eine gasturbine und gasturbine mit solch einem rohrbrenner

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EP (1) EP3486567B1 (de)
CN (1) CN110030578A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220316709A1 (en) * 2020-12-07 2022-10-06 Rolls-Royce Plc Combustor with improved aerodynamics

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3974723B1 (de) * 2020-09-23 2023-08-30 Ansaldo Energia Switzerland AG Gasturbine für kraftwerk mit einer dämpfungsvorrichtung

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0896193A2 (de) * 1997-08-05 1999-02-10 European Gas Turbines Limited Gasturbinenbrennkammer
EP1669670A1 (de) * 2004-12-11 2006-06-14 ROLLS-ROYCE plc Brennkammer eines Gasturbinentriebwerks
US8490744B2 (en) 2009-02-27 2013-07-23 Mitsubishi Heavy Industries, Ltd. Combustor and gas turbine having the same
US20160003162A1 (en) * 2013-02-28 2016-01-07 Siemens Aktiengesellschaft Damping device for a gas turbine, gas turbine and method for damping thermoacoustic oscillations
EP3029377A1 (de) * 2014-12-03 2016-06-08 Alstom Technology Ltd Dämpfer für Gasturbine
US20160215984A1 (en) * 2015-01-28 2016-07-28 General Electric Technology Gmbh Sequential combustor arrangement with a mixer

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013144070A1 (en) * 2012-03-30 2013-10-03 Alstom Technology Ltd Combustion chamber seal segments equipped with damping devices

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0896193A2 (de) * 1997-08-05 1999-02-10 European Gas Turbines Limited Gasturbinenbrennkammer
EP1669670A1 (de) * 2004-12-11 2006-06-14 ROLLS-ROYCE plc Brennkammer eines Gasturbinentriebwerks
US8490744B2 (en) 2009-02-27 2013-07-23 Mitsubishi Heavy Industries, Ltd. Combustor and gas turbine having the same
US20160003162A1 (en) * 2013-02-28 2016-01-07 Siemens Aktiengesellschaft Damping device for a gas turbine, gas turbine and method for damping thermoacoustic oscillations
EP3029377A1 (de) * 2014-12-03 2016-06-08 Alstom Technology Ltd Dämpfer für Gasturbine
US20160215984A1 (en) * 2015-01-28 2016-07-28 General Electric Technology Gmbh Sequential combustor arrangement with a mixer

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220316709A1 (en) * 2020-12-07 2022-10-06 Rolls-Royce Plc Combustor with improved aerodynamics
US11603993B2 (en) * 2020-12-07 2023-03-14 Rolls-Royce Plc Combustor with improved aerodynamics

Also Published As

Publication number Publication date
EP3486567B1 (de) 2022-01-26
CN110030578A (zh) 2019-07-19

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