EP2423599A2 - Procédé de fonctionnement d'un agencement de brûleur ainsi qu'agencement de brûleur destiné à l'exécution du procédé - Google Patents

Procédé de fonctionnement d'un agencement de brûleur ainsi qu'agencement de brûleur destiné à l'exécution du procédé Download PDF

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Publication number
EP2423599A2
EP2423599A2 EP11177535A EP11177535A EP2423599A2 EP 2423599 A2 EP2423599 A2 EP 2423599A2 EP 11177535 A EP11177535 A EP 11177535A EP 11177535 A EP11177535 A EP 11177535A EP 2423599 A2 EP2423599 A2 EP 2423599A2
Authority
EP
European Patent Office
Prior art keywords
burner
burner wall
cooling air
effusion holes
wall
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
EP11177535A
Other languages
German (de)
English (en)
Other versions
EP2423599B1 (fr
EP2423599A3 (fr
Inventor
Madhavan Poyyapakkam
Adnan Ergolu
Andrea Ciani
Diane Lauffer
Uwe Ruedel
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
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
Publication of EP2423599A2 publication Critical patent/EP2423599A2/fr
Publication of EP2423599A3 publication Critical patent/EP2423599A3/fr
Application granted granted Critical
Publication of EP2423599B1 publication Critical patent/EP2423599B1/fr
Active 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • 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

Definitions

  • the present invention relates to the field of burner technology, in particular gas turbines. It relates to methods for operating a burner assembly according to the preamble of claim 1. It further relates to a burner assembly for carrying out the method.
  • SEV burners are used in the applicant, which are described, for example, in the article " Field experience with the sequential combustion system of the GT24 / GT26 gas turbine family ", ABB Review 5, 1998, pp. 12-20 , or in the publication EP 2 169 314 A2 (see the local there Fig. 1 ) to be discribed.
  • the SEV burner 10 of Fig. 1 includes a mixing space 12 extending in a flow direction (see the elongated arrows). Upstream of the mixing chamber 12 is an inlet 11, can enter through the combustion gases 18 from the first (not shown) combustion chamber to relax in the first (not shown) turbine in the mixing chamber 12. Downstream of the mixing chamber 12 is followed by a combustion chamber 13, in which a burner flame with a corresponding flame boundary 17 is formed during operation.
  • the mixing space 12 is bounded outwardly by a burner wall 15 having a plurality of effusion holes 16.
  • Into the mixing chamber 12 projects an angled fuel lance 14, from which a fuel 19 is injected into the mixing chamber 12.
  • Achieved combustion temperatures or highly reactive fuels can be used, and to provide a burner assembly for performing the method.
  • the deflection allow in their area a more concentrated effusion cooling of the burner.
  • the deflecting elements are mounted directly on the outer surface of the burner wall.
  • they have the shape of a halved ball half shell and resemble an orchestra shell.
  • the height and width of the semicircular opening of the deflecting elements can be varied as a function of the diameter and spacing of the effusion holes covered therewith.
  • the number and placement of the deflectors depend on the shape of the burner.
  • the orientation of the baffles that is, the orientation of their openings
  • the deflecting elements can either be manufactured and fastened individually or together in the form of a correspondingly punched and / or embossed sheet metal.
  • the deflecting elements may be welded or cast on the burner wall.
  • the number and diameter of the effusion holes can also be adapted to the positions of the deflection elements.
  • An embodiment of the method according to the invention is characterized in that the cooling air on the outside of the burner wall has a velocity component parallel to the burner wall, and that the cooling air is deflected in the direction of the burner wall.
  • Another embodiment of the method according to the invention is characterized in that the cooling air is deflected by a deflection in each case in one of the effusion holes.
  • Another embodiment of the method according to the invention is characterized in that the cooling air is deflected by a deflecting element in each case in several effusion holes.
  • Another embodiment of the method according to the invention is characterized in that the effusion holes are inclined with their axes relative to the burner wall, and that the cooling air is deflected by the deflecting elements such that it flows on entry into the effusion holes substantially parallel to the axes of the effusion holes.
  • a further embodiment of the method according to the invention is characterized in that the effusion holes are inclined with their axes relative to the burner wall, and that the cooling air is deflected by the deflecting elements such that it flows substantially perpendicular to the burner wall when entering the effusion holes.
  • Another embodiment of the method according to the invention is characterized in that a perforated plate with holes is arranged on the outside of the burner wall and at a distance from the burner wall, and that the cooling air is introduced on the side facing away from the burner wall of the perforated plate and by the deflection into the holes of the perforated plate is deflected and flows to the burner wall.
  • Yet another embodiment of the method according to the invention is characterized in that spoon-like shells are used as deflecting elements which shield the associated effusion holes from one side and are open in the direction of the approaching cooling air.
  • the burner assembly comprises a mixing chamber extending in a flow direction, which is bounded on the outside by a burner wall and has an inlet for combustion air containing hot combustion gas upstream, and to the downstream of a combustion chamber connects, wherein in the mixing chamber a fuel lance for injecting a fuel protrudes and the burner wall is provided with effusion holes through which brought on the outside of the burner wall cooling air can flow into the mixing chamber, wherein deflecting elements are arranged on the outside of the burner wall, which deflect the introduced cooling air in the direction of the burner wall.
  • An embodiment of the burner assembly according to the invention is characterized in that the deflection elements are designed such that the cooling air is deflected in the direction of the burner wall.
  • Another embodiment of the burner assembly according to the invention is characterized in that in each case a deflecting element is associated with one of the effusion holes.
  • Another embodiment of the burner assembly according to the invention is characterized in that a deflecting element is assigned in each case to a plurality of effusion holes.
  • Another embodiment of the burner assembly according to the invention is characterized in that the effusion holes are inclined with their axes relative to the burner wall, and that the deflecting elements are designed such that the cooling air flows in the entry into the effusion holes substantially parallel to the axes of the effusion holes.
  • Another embodiment of the burner assembly according to the invention is characterized in that the effusion holes are inclined with their axes relative to the burner wall, and that the deflection elements are formed such that the cooling air flows when entering the effusion holes substantially perpendicular to the burner wall.
  • a further embodiment of the burner arrangement according to the invention is characterized in that a perforated plate with holes is arranged on the outside of the burner wall and at a distance from the burner wall, and that the deflecting elements are arranged on the side facing away from the burner wall of the perforated plate such that cooling air through the deflecting elements in the holes of the perforated plate is deflected and flows to the burner wall.
  • Yet another embodiment of the burner assembly according to the invention is characterized in that the deflecting elements are designed as spoon-like shells which shield the associated effusion holes from one side and are open in the direction of the approaching cooling air.
  • Yet another embodiment of the burner assembly according to the invention is characterized in that the deflecting elements are applied to the outer surface of the burner wall or the perforated plate.
  • the invention gives the possibility of the effusion cooling of the burner Fig. 1 "tailor" or optimize in order to increase their impact in the most critical areas of the burner (the particularly hot areas). This happens because aerodynamically shaped deflecting elements (21 in FIG. 3 and FIG. 4 ) are arranged on the cold or outer side of the burner wall 15. The presence of this spoon-like, designed in the manner of a half-spherical half-deflection elements 21 makes it possible to adjust the direction of the injected effusion cooling air according to the particular needs.
  • the diverting elements 21 allow the flow to accumulate and convert at least part of the dynamic pressure into static pressure.
  • the deflecting elements 21 thus allow the feed pressure for the effusion cooling to be raised and adjusted.
  • Fig. 3 shows a small section of the burner wall 15 with a plurality of distributed therein effusion holes 16, by the according Fig. 1 Cooling air flows into the mixing chamber 12.
  • Fig. 3 further shows a single deflecting element 21, which, representative of other deflecting elements, not shown, several of the effusion holes 16 so covered that in the direction of the arrow on the burner wall 15 along the cooling air flow 20 captured and deflected in the direction of the effusion holes 16. Over the entire burner wall 15, many such deflecting elements 21 may be arranged in different density and orientation, in order to deflect the cooling air 20 in an optimum manner.
  • Fig. 4 shows a single arrangement of a deflecting element 21, which is associated with only a single effusion hole 16.
  • the function can be set as a deflecting element or as a stowage element for recovering the dynamic pressure.
  • the effusion holes 16 can be oriented with their hole axes perpendicular to the plane of the burner wall 10. In most cases, however, as in Fig. 2 shows the axes of the effusion holes 16 with respect to the plane of the Burner wall 15 inclined so that the inflowing through the effusion holes 16 cooling air has a velocity component parallel to the main flow in the mixing chamber 12 and increases the axial length and thus the cooling effect.
  • the angle ⁇ which includes the axis with the wall plane, may be in a range between 10 ° and 80 °, in particular between 20 ° and 50 °, preferably between 30 ° and 40 °. A particularly suitable value has been found to be an angle of 35 °.
  • the deflecting elements 21, as in Fig. 5 shown be shaped so that the deflected cooling air largely perpendicular to the burner wall 15 and thus meets the hole entrances.
  • it can be more favorable in terms of flow technology according to Fig. 6 adjust the curvature of the deflection elements 22 so that the deflected cooling air enters the effusion holes 16 practically in the direction of the hole axes.
  • the effusion cooling described is not limited to the mixing chamber 12, but may also extend to the liner of the combustion chamber 13.
  • the effusion cooling in the liner has the task of avoiding the self-ignition of the air-fuel mixture.
  • the effusion cooling in the mixing chamber 12 or premixer has the task of avoiding the stagnation of combustion gases on the burner wall 15 by forming a boundary layer.
  • the function of the vortex formation of the cooling air by the deflecting elements 21, 22 can be reinforced by the fact that the deflecting elements 21, 20 are mounted in a specific overall arrangement (staggering) in order to influence each other in terms of flow.
  • staggering the convective cooling on the outside of the burner wall 15 is increased.
  • rows of deflection elements 21, 22 are arranged at right angles to the flow direction of the cooling air 22, wherein the deflection elements 21, 22 of two successive rows are each arranged offset from one another.
  • the deflection elements 21, 22 locally enhance the effusion cooling of the burner. If according to Fig. 7 a perforated plate 23 is used as an impingement cooling plate with deflecting elements, the heat transfer coefficient increases on the cold side of the burner wall 15.
  • the deflecting elements 21, 22 are preferably arranged in the areas where the cooling air has a particularly high speed to more cooling air in the effusion holes 16th redirect.
  • Some areas of the effusion cooling are disadvantaged in that the speed of the cooling air is high there and only a low static pressure prevails.
  • Some areas of effusion cooling need to be reinforced because the heat load on the hot gas side (because of a high heat transfer coefficient or a high flame temperature) is particularly high there.
  • the deflection elements according to the invention catch cooling air through a combination of damming and diverting, which otherwise would have flowed past the effusion holes. In this way, the cooling can be local be reinforced without increasing the number of effusion holes or the diameter of the effusion holes increases the risk of cracking.

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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)
EP11177535.9A 2010-08-27 2011-08-15 Procédé de fonctionnement d'un agencement de brûleur ainsi qu'agencement de brûleur destiné à la mise en oeuvre du procédé Active EP2423599B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH01388/10A CH703657A1 (de) 2010-08-27 2010-08-27 Verfahren zum betrieb einer brenneranordnung sowie brenneranordnung zur durchführung des verfahrens.

Publications (3)

Publication Number Publication Date
EP2423599A2 true EP2423599A2 (fr) 2012-02-29
EP2423599A3 EP2423599A3 (fr) 2013-07-31
EP2423599B1 EP2423599B1 (fr) 2017-05-17

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EP11177535.9A Active EP2423599B1 (fr) 2010-08-27 2011-08-15 Procédé de fonctionnement d'un agencement de brûleur ainsi qu'agencement de brûleur destiné à la mise en oeuvre du procédé

Country Status (5)

Country Link
US (1) US9157637B2 (fr)
EP (1) EP2423599B1 (fr)
JP (1) JP5896644B2 (fr)
CH (1) CH703657A1 (fr)
ES (1) ES2632755T3 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2728258A1 (fr) 2012-11-02 2014-05-07 Alstom Technology Ltd Turbine à gaz
EP2759772A1 (fr) * 2013-01-23 2014-07-30 Honeywell International Inc. Chambres de combustion avec trous d'effusion de forme complexe
EP3511625A1 (fr) * 2018-01-12 2019-07-17 United Technologies Corporation Appareil et procédé d'atténuation de séparation d'air autour d'une chambre de combustion d'un moteur
US12060995B1 (en) * 2023-03-22 2024-08-13 General Electric Company Turbine engine combustor with a dilution passage

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EP2735796B1 (fr) 2012-11-23 2020-01-01 Ansaldo Energia IP UK Limited Paroi située sur la trajectoire des gaz chauds d'une turbine à gaz et procédé pour améliorer le comportement de fonctionnment d'une turbine à gaz
US9228747B2 (en) * 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
DE102013221286B4 (de) 2013-10-21 2021-07-29 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennkammer, insbesondere Gasturbinenbrennkammer, z. B. für ein Luftfahrttriebwerk
FR3035481B1 (fr) * 2015-04-23 2017-05-05 Snecma Chambre de combustion de turbomachine comportant un dispositif de guidage de flux d'air de forme specifique
US10260751B2 (en) * 2015-09-28 2019-04-16 Pratt & Whitney Canada Corp. Single skin combustor with heat transfer enhancement
KR101766449B1 (ko) * 2016-06-16 2017-08-08 두산중공업 주식회사 공기유도 캡 및 이를 구비하는 연소 덕트
US20190024895A1 (en) * 2017-07-18 2019-01-24 General Electric Company Combustor dilution structure for gas turbine engine
KR101812225B1 (ko) * 2017-08-02 2017-12-27 두산중공업 주식회사 공기유도 캡 및 이를 구비하는 연소 덕트
KR101986729B1 (ko) 2017-08-22 2019-06-07 두산중공업 주식회사 실 영역 집중냉각을 위한 냉각유로 구조 및 이를 포함하는 가스 터빈용 연소기
US11268438B2 (en) * 2017-09-15 2022-03-08 General Electric Company Combustor liner dilution opening
KR102099300B1 (ko) 2017-10-11 2020-04-09 두산중공업 주식회사 스워즐 유동을 개선하는 슈라우드 구조 및 이를 적용한 연소기 버너
US10995635B2 (en) 2017-11-30 2021-05-04 Raytheon Technologies Corporation Apparatus and method for mitigating particulate accumulation on a component of a gas turbine engine
US11098653B2 (en) * 2018-01-12 2021-08-24 Raytheon Technologies Corporation Apparatus and method for mitigating particulate accumulation on a component of a gas turbine
US11098899B2 (en) * 2018-01-18 2021-08-24 Raytheon Technologies Corporation Panel burn through tolerant shell design
GB2596305A (en) * 2020-06-23 2021-12-29 Ansaldo Energia Switzerland AG Burner of a reheat gas turbine engine
US11603799B2 (en) * 2020-12-22 2023-03-14 General Electric Company Combustor for a gas turbine engine
CN116221774B (zh) 2021-12-06 2025-09-09 通用电气公司 用于燃烧器衬里的变化的稀释孔设计

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2728258A1 (fr) 2012-11-02 2014-05-07 Alstom Technology Ltd Turbine à gaz
EP2759772A1 (fr) * 2013-01-23 2014-07-30 Honeywell International Inc. Chambres de combustion avec trous d'effusion de forme complexe
US9765968B2 (en) 2013-01-23 2017-09-19 Honeywell International Inc. Combustors with complex shaped effusion holes
EP3511625A1 (fr) * 2018-01-12 2019-07-17 United Technologies Corporation Appareil et procédé d'atténuation de séparation d'air autour d'une chambre de combustion d'un moteur
US11988145B2 (en) 2018-01-12 2024-05-21 Rtx Corporation Apparatus and method for mitigating airflow separation around engine combustor
US12060995B1 (en) * 2023-03-22 2024-08-13 General Electric Company Turbine engine combustor with a dilution passage
US12601484B2 (en) 2023-03-22 2026-04-14 General Electric Company Turbine engine combustor with a dilution passage

Also Published As

Publication number Publication date
JP2012047443A (ja) 2012-03-08
EP2423599B1 (fr) 2017-05-17
CH703657A1 (de) 2012-02-29
ES2632755T3 (es) 2017-09-15
EP2423599A3 (fr) 2013-07-31
JP5896644B2 (ja) 2016-03-30
US9157637B2 (en) 2015-10-13
US20120047908A1 (en) 2012-03-01

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