EP1493972A1 - Ensemble de brûleur pour une turbine à gaz et turbine à gaz - Google Patents

Ensemble de brûleur pour une turbine à gaz et turbine à gaz Download PDF

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Publication number
EP1493972A1
EP1493972A1 EP03015214A EP03015214A EP1493972A1 EP 1493972 A1 EP1493972 A1 EP 1493972A1 EP 03015214 A EP03015214 A EP 03015214A EP 03015214 A EP03015214 A EP 03015214A EP 1493972 A1 EP1493972 A1 EP 1493972A1
Authority
EP
European Patent Office
Prior art keywords
burner
gas turbine
stages
combustion chamber
burner unit
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Withdrawn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
EP03015214A
Other languages
German (de)
English (en)
Inventor
Werner Dr. Krebs
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 EP03015214A priority Critical patent/EP1493972A1/fr
Priority to EP04740264.9A priority patent/EP1642065B1/fr
Priority to PCT/EP2004/006851 priority patent/WO2005003634A1/fr
Publication of EP1493972A1 publication Critical patent/EP1493972A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • 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
    • 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

Definitions

  • the invention relates to a burner unit for a Gas turbine with a combustion chamber. It also relates to a Gas turbine with a number of such burner units.
  • the nitrogen oxide emissions of the gas turbine be kept very low even in a compact design modern gas turbines usually in the so-called premix mode operated.
  • the fuel is over a Variety of injection nozzles supplied and then in premixed with compressor air.
  • To provide the required high thermal performances usually more burners, in which fuel mixed and the fuel premixed with air is connected in parallel, in particular in the so-called Ring burner chamber design several burners on one common, annular designed combustion chamber arranged could be.
  • the invention is based on the consideration that the Burner unit in particular to operational stability and safety of the gas turbine can contribute by possible Incident sources are consistently avoided.
  • thermoacoustically induced combustion instabilities occur not sufficiently limited by external damping mechanisms can be.
  • the burner unit comprising the combustion chamber in terms of their acoustic properties are designed to be suitable.
  • the Burner stages of each other in at least one of the features distinguish the respective acoustic response times the burner stages to a pressure fluctuation in the combustion chamber characterize, namely the thermoacoustic properties the fuel supply, characterized by the acoustic Impedance of the fuel supply, the thermoacoustic properties the air supply, characterized by the acoustic Impedance of the air passage, and the delay time of the flame, characterized by the time required for a fluid element from the burner outlet to the flame front, also as “Flame delay time", or by the time, the one fuel enriched fluid element from the injection site needed up to the flame front, also as "injection delay time” designated.
  • the impedance generally expresses the relationship between a force excitation and a resulting movement, So for example in the AC technology between electric field and resulting current density, out.
  • the acoustic impedance is thus the ratio of a pressure fluctuation to the resulting Flow rate of a medium again. Between a pressure fluctuation and a resulting There is a fluctuation in the flow velocity on the one hand an amplitude ratio and on the other hand a phase difference.
  • the phase difference expresses to what extent the Fluctuation of the flow velocity of the causing them Pressure fluctuation ahead or hinterhreilt, so that the acoustic impedance among other things a suitable measure of the Time interval between an acoustic stimulus, so for example an acoustic alternating pressure fluctuation, and the Answer the respective burner stage on this, so one Variation of the exit velocity at the respective Burner exit level, is.
  • the throttling devices can in particular for the targeted generation of Pressure losses in the interior of the burner stages, for example in their premix chambers, be designed as Throttle device, for example perforated plates with suitably dimensioned Bore diameters can be provided.
  • Throttle device for example perforated plates with suitably dimensioned Bore diameters can be provided.
  • resonators can be used be, preferably in flow passages upstream or downstream the fuel gas injection, advantageously such that they are in the air passage and / or in the fuel passage of the respective Burner stage open.
  • the burner stages of these are advantageously designed so that the sum of the so-called acoustic time span of each burner stage, ie the through the given acoustic impedances of the respective burner stage Time span between the acoustic stimulus and the answer the respective burner stage, and the so-called delay time, that is, the period of time that a fluid element for the distance between the exit plane of the respective burner stage and the flame front needed, differ from each other.
  • the flame delay time is advantageously on the specification of a suitably selected exit velocity at the respective burner outlet and / or via integrated Spin generating agent adjusted, in particular the ratio of the size of the peripheral speed component to the meridional velocity component of the used the respective burner stage effluent flow medium is.
  • the stated object is achieved by the burner unit as a burner unit of the aforementioned Art is designed.
  • the advantages achieved by the invention are in particular in that by the multi-stage configuration of the burner unit with burner stages that are in terms of their distinguish thermoacoustic properties from each other, a consistent acoustic decoupling of the individual Burner stages is reachable from each other. This can the possible excitation of thermoacoustically induced combustion instabilities especially in the combustion system of the gas turbine be kept low. Such a design Burner unit is thus particularly stable against pressure fluctuations in the combustion chamber, leaving a gas turbine with Such a burner unit a particularly high operational Stability.
  • the combustion chamber 4 is provided with a number of burners 10 for Combustion of a liquid or gaseous fuel equipped. She is still on her inner wall with no closer provided heat shield elements provided.
  • Each vane 14 has one also referred to as blade root 19 Platform 18 on which is to fix the respective Guide vane 14 on the inner housing 16 of the turbine 6 as a wall element is arranged.
  • the platform 18 is a thermal comparatively heavily loaded component, which is the outer boundary a Bankgaskanals for the turbine 6 flowing through Working medium M forms.
  • Each blade 12 is in analog Way about one also referred to as platform 18 Blade 19 attached to the turbine shaft 8, wherein the Blade foot 19 each one along a blade axis extended profiled airfoil 20 carries.
  • each guide ring 21 on the inner housing 16 of Turbine 6 is arranged between the spaced apart platforms 18 of the vanes 14 of two adjacent rows of vanes.
  • the outer surface of each guide ring 21 is also the hot, the turbine 6 flowing through Working medium M exposed and in the radial direction from the outer end 22 of the blade opposite it 12 spaced by a gap.
  • the between adjacent Guide blade rows arranged guide rings 21st serve in particular as cover elements that the inner wall 16 or other housing-mounted components before a thermal Overuse by the turbine 6 flowing through hot Working medium M protects.
  • each Burner stage 30 is in each case to a schematically indicated Air supply or air passage 32 and to a no closer shown, each in a number of inflow openings Connected 34 fuel supply line.
  • outgoing from the burner exit plane 36 of each burner stage 30 forms during operation of the gas turbine 1 in the interior of the combustion chamber 4 shows a flame front assigned to the respective burner stage 30 38.
  • FIG 2 are three Burner stages 30 shown; but it can also only two or four or more burner stages 30 are provided be.
  • thermoacoustic decoupling or Distortion of the burner stages 30 the avoidance the excitation of thermoacoustically induced combustion instabilities is to ensure the burner stages 30 with regard to the acoustic impedance of their fuel supply, the acoustic impedance of their air passage 32 and / or their flame delay time designed differently from each other. From the acoustic impedances of the fuel supply line and the air passage 32 can each time constants derive the time span between an im Interior of the combustion chamber 4 occurring pressure fluctuation and the subsequent reaction of the respective burner stage 30, So a fluctuation of the exit velocity at the exit the flow medium from the respective exit plane 36, play.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP03015214A 2003-07-04 2003-07-04 Ensemble de brûleur pour une turbine à gaz et turbine à gaz Withdrawn EP1493972A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP03015214A EP1493972A1 (fr) 2003-07-04 2003-07-04 Ensemble de brûleur pour une turbine à gaz et turbine à gaz
EP04740264.9A EP1642065B1 (fr) 2003-07-04 2004-06-24 Ensemble de brûleur pour une turbine à gaz et turbine à gaz
PCT/EP2004/006851 WO2005003634A1 (fr) 2003-07-04 2004-06-24 Unite de combustion pour turbine a gaz et turbine a gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03015214A EP1493972A1 (fr) 2003-07-04 2003-07-04 Ensemble de brûleur pour une turbine à gaz et turbine à gaz

Publications (1)

Publication Number Publication Date
EP1493972A1 true EP1493972A1 (fr) 2005-01-05

Family

ID=33427129

Family Applications (2)

Application Number Title Priority Date Filing Date
EP03015214A Withdrawn EP1493972A1 (fr) 2003-07-04 2003-07-04 Ensemble de brûleur pour une turbine à gaz et turbine à gaz
EP04740264.9A Expired - Lifetime EP1642065B1 (fr) 2003-07-04 2004-06-24 Ensemble de brûleur pour une turbine à gaz et turbine à gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP04740264.9A Expired - Lifetime EP1642065B1 (fr) 2003-07-04 2004-06-24 Ensemble de brûleur pour une turbine à gaz et turbine à gaz

Country Status (2)

Country Link
EP (2) EP1493972A1 (fr)
WO (1) WO2005003634A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009038625A2 (fr) * 2007-09-14 2009-03-26 Siemens Energy, Inc. Système de combustion axial à étages multiples
EP2587158A1 (fr) * 2011-10-31 2013-05-01 Siemens Aktiengesellschaft Chambre de combustion pour une turbine à gaz et agencement de brûleur
WO2018202407A1 (fr) 2017-05-04 2018-11-08 Siemens Aktiengesellschaft Chambre de combustion

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4122674A (en) * 1976-12-27 1978-10-31 The Boeing Company Apparatus for suppressing combustion noise within gas turbine engines
WO1998012478A1 (fr) * 1996-09-16 1998-03-26 Siemens Aktiengesellschaft Procede et dispositif pour la combustion d'un combustible avec de l'air
US6164055A (en) * 1994-10-03 2000-12-26 General Electric Company Dynamically uncoupled low nox combustor with axial fuel staging in premixers
EP1180646A1 (fr) * 2000-08-10 2002-02-20 ROLLS-ROYCE plc Chambre de combustion
US6430930B1 (en) * 1998-08-11 2002-08-13 Abb Ab Arrangement for reduction of acoustic vibrations in a combustion chamber
US20020121080A1 (en) * 2001-01-16 2002-09-05 Jones Alan R. Fluid flow control valve
US6490864B1 (en) * 1999-10-08 2002-12-10 Alstom (Switzerland) Ltd Burner with damper for attenuating thermo acoustic instabilities
US20030041588A1 (en) * 1999-08-18 2003-03-06 Franz Joos Method for generating hot gases in a combustion device and combustion device for carrying out the method
DE10164099A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeinspritzung
DE10164097A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Vormischbrenner mit hoher Flammenstabilität

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1342953A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Turbine à gaz

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4122674A (en) * 1976-12-27 1978-10-31 The Boeing Company Apparatus for suppressing combustion noise within gas turbine engines
US6164055A (en) * 1994-10-03 2000-12-26 General Electric Company Dynamically uncoupled low nox combustor with axial fuel staging in premixers
WO1998012478A1 (fr) * 1996-09-16 1998-03-26 Siemens Aktiengesellschaft Procede et dispositif pour la combustion d'un combustible avec de l'air
US6430930B1 (en) * 1998-08-11 2002-08-13 Abb Ab Arrangement for reduction of acoustic vibrations in a combustion chamber
US20030041588A1 (en) * 1999-08-18 2003-03-06 Franz Joos Method for generating hot gases in a combustion device and combustion device for carrying out the method
US6490864B1 (en) * 1999-10-08 2002-12-10 Alstom (Switzerland) Ltd Burner with damper for attenuating thermo acoustic instabilities
EP1180646A1 (fr) * 2000-08-10 2002-02-20 ROLLS-ROYCE plc Chambre de combustion
US20020121080A1 (en) * 2001-01-16 2002-09-05 Jones Alan R. Fluid flow control valve
DE10164099A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeinspritzung
DE10164097A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Vormischbrenner mit hoher Flammenstabilität

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009038625A2 (fr) * 2007-09-14 2009-03-26 Siemens Energy, Inc. Système de combustion axial à étages multiples
WO2009038625A3 (fr) * 2007-09-14 2010-05-06 Siemens Energy, Inc. Système de combustion axial à étages multiples
JP2010539436A (ja) * 2007-09-14 2010-12-16 シーメンス エナジー インコーポレイテッド 多段式軸流燃焼システム
US7886539B2 (en) 2007-09-14 2011-02-15 Siemens Energy, Inc. Multi-stage axial combustion system
KR101324142B1 (ko) * 2007-09-14 2013-11-01 지멘스 에너지, 인코포레이티드 다중 스테이지 축방향 연소 시스템
EP2587158A1 (fr) * 2011-10-31 2013-05-01 Siemens Aktiengesellschaft Chambre de combustion pour une turbine à gaz et agencement de brûleur
WO2013064383A1 (fr) * 2011-10-31 2013-05-10 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz et système de brûleurs
WO2018202407A1 (fr) 2017-05-04 2018-11-08 Siemens Aktiengesellschaft Chambre de combustion

Also Published As

Publication number Publication date
WO2005003634A1 (fr) 2005-01-13
EP1642065A1 (fr) 2006-04-05
EP1642065B1 (fr) 2018-04-25

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