EP1064498A1 - Bruleur et procede pour reduire les vibrations en cours de combustion - Google Patents

Bruleur et procede pour reduire les vibrations en cours de combustion

Info

Publication number
EP1064498A1
EP1064498A1 EP99917770A EP99917770A EP1064498A1 EP 1064498 A1 EP1064498 A1 EP 1064498A1 EP 99917770 A EP99917770 A EP 99917770A EP 99917770 A EP99917770 A EP 99917770A EP 1064498 A1 EP1064498 A1 EP 1064498A1
Authority
EP
European Patent Office
Prior art keywords
swirl
burner
combustion
flow
combustion air
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
EP99917770A
Other languages
German (de)
English (en)
Other versions
EP1064498B1 (fr
Inventor
Manfred Ziegner
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of EP1064498A1 publication Critical patent/EP1064498A1/fr
Application granted granted Critical
Publication of EP1064498B1 publication Critical patent/EP1064498B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F23D—BURNERS
    • F23D23/00—Assemblies of two or more burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement

Definitions

  • the invention relates to a burner with a flow channel for supplying a flow from combustion air or from a combustion air / fuel mixture, a swirl device being provided in the flow channel for imparting a swirl to the flow.
  • the invention further relates to the use of a burner and a method for reducing combustion vibrations.
  • combustion vibrations When operating a burner in a combustion system, combustion vibrations can form. This is also known under the terms “combustion chamber hum”, “combustion chamber vibrations”, “combustion-induced pressure pulsations”, “vibrating combustion”. The combustion vibrations are based on an interaction of the pro
  • a hybrid burner for a gas turbine is known from the EP-0 580 683 B1.
  • a hybrid burner has both a diffusion burner and a premix burner.
  • the premix burner of the hybrid burner has an annular channel for supplying combustion air or a combustion air / fuel mixture.
  • a swirl device for applying a swirl to a flow, which forms the supplied combustion air / fuel mixture or the combustion air in the ring channel.
  • This swirl device is also referred to as a swirl grid.
  • the diffusion burner of the hybrid burner is arranged coaxially in the ring channel of the premix burner.
  • the diffusion burner has a combustion air supply duct designed as an annular duct, in which a fuel supply duct is arranged coaxially.
  • the channels of the diffusion burner open into a nozzle.
  • the diffusion burner has a pilot burner in its combustion air supply duct, which is only required for the operation of the premix burner.
  • a combustion air / fuel mixture is supplied via the ring channel of the premix burner, which mixture forms a flow in the ring channel, and a swirl is applied to the flow with the help of the swirl grille.
  • the swirling flow exits the premix burner for combustion.
  • the combustion is stabilized with the pilot burner flame.
  • combustion air or fuel is fed to a mixture in the region of the nozzles of the diffusion burner via the combustion air and the fuel supply channel of the diffusion burner.
  • the combustion air / fuel mixture formed in the mixture emerges from the diffusion burner for combustion.
  • the object of the invention is to provide a burner with a lower tendency to form combustion vibrations to indicate use in a combustion system. Another object is to provide a method for reducing combustion vibrations.
  • the object directed to a burner is achieved by a burner according to the preamble of claim 1, which has a swirl device with an outflow end, which swirl device is designed such that the swirl is impressed unevenly in the circumferential direction.
  • the invention is based on the knowledge that when a burner is operating in the flow channel, a flow of combustion air is formed which is mixed with fuel to form a combustion air / fuel mixture via fuel inlets.
  • the fuel is preferably fed into a flow of combustion air that is uniform over the cross section of the flow channel. This has the advantage that the local mixing ratio between combustion air and fuel is essentially uniform over the cross section. With a uniform mixture, the NO x content of the exhaust gas, which arises during the combustion of the combustion air / fuel mixture formed in the mixture, can be influenced.
  • a swirl is preferably applied to the flow in the flow channel in order to stabilize the combustion.
  • This swirl is usually uniform over the circumference of the flow channel so as not to impair the uniformity of the flow.
  • Studies have shown that the more uniform the flow of a combustion air / fuel mixture supplied for combustion with a burner, the greater the likelihood that combustion vibrations can form when the burner is operated in a combustion system.
  • the invention is therefore based on the idea of designing a burner in such a way that a flow of a combustion air / fuel mixture formed before the supply to a combustion is so uneven by applying an uneven swirl that the excitation of combustion vibrations during operation of the burner in a combustion system is at least significantly reduced.
  • a swirl device arranged in the flow channel, a swirl which is uneven in the circumferential direction is impressed on the flow of the combustion air / fuel mixture.
  • the swirl device preferably has a plurality of swirl elements, each swirl element having a deflection surface. Due to the geometry of the flow channel, a main flow direction of the flow of the combustion air / fuel mixture is defined, which can change depending on the burner geometry.
  • the deflection surfaces of the swirl elements each have an outflow angle to the main flow direction at the outflow end, which angle is preferably different for at least two directly adjacent swirl elements. It is thereby achieved that the flow exits at least two different angles in the circumferential direction after flowing through the swirl device, so that the imposed swirl is uneven in the circumferential direction.
  • each swirl element is designed as a swirl blade.
  • a plurality of swirl elements with the same outflow angles preferably form a swirl group, and the swirl device has at least one such swirl group.
  • the swirl device is further preferably formed from a plurality of swirl groups, adjacent swirl groups having different outflow angles.
  • the swirl device can for example, be formed from six swirl groups, each swirl group each having four swirl elements.
  • the flow channel of the burner is preferably designed as an annular channel, the swirl device being arranged in the annular channel.
  • the burner can be designed, for example, as a hybrid burner for a gas turbine.
  • the burner preferably has a fuel inlet through which fuel can be fed into the flow channel upstream of the outflow end. As a result, the fuel is fed into a uniform flow of combustion air flowing in the supply duct in front of the swirl device.
  • the object directed to the use is achieved according to the invention by a use according to claim 10, according to which the burner is used in a gas turbine for the combustion of a combustion air / fuel mixture in a combustion chamber.
  • a flow of a combustion air / fuel mixture or of combustion air in a flow channel of the burner is imparted with an uneven swirl in the circumferential direction.
  • the swirl device for imparting the swirl and the method for reducing combustion vibrations are explained in more detail. They show schematically and partly not to scale, showing the constructive and functional features used for the explanation:
  • FIG. 1 shows a burner designed as a hybrid burner for a gas turbine and
  • FIG. 2 shows a view of the swirl elements of the ring channel of the premix burner which are developed in the circumferential direction.
  • the reference numerals feliere figures are each moving ⁇ che importance.
  • the hybrid burner 1 shows a burner 1 designed as a hybrid burner 1 of a gas turbine, which is not shown in greater detail.
  • the hybrid burner 1 has both a diffusion burner 2 and a premix burner 3.
  • the premix burner 3 has an annular channel 4 with an outer wall 16, which is used to supply combustion air 5 or a combustion air / fuel mixture 5.
  • a swirl device 6 Arranged in the ring channel 4 is a swirl device 6 with an outflow end 12, which serves to apply a swirl to a flow 7, which flow 7 forms the supplied combustion air / fuel mixture 5 or the combustion air 5 in the ring channel 4.
  • the swirl device 6 is also referred to below as a swirl grille 6.
  • the swirl grille 6 has a plurality of swirl elements 15, each of which is designed as a swirl blade.
  • Fuel inlets 13 are arranged upstream of the outflow end 12, via which fuel 14 can be fed into the ring channel 4 and thus can be admixed with the combustion air 5.
  • the diffusion burner 2 of the hybrid burner 1 is arranged coaxially in the ring channel 4 of the premix burner 3.
  • the diffusion burner 2 has a combustion air supply duct 8 designed as an annular duct, in which a fuel supply duct 9 is arranged coaxially.
  • the channels 8 and 9 of the diffusion burner 2 open into a nozzle 10.
  • the diffusion burner has ner 2 in its combustion air supply channel 8, a pilot burner 11, which is provided for operating the premix burner 3.
  • combustion air 5 is supplied via the ring channel 4 and mixes with fuel 14 supplied via the fuel inlets 13 to form a combustion air / fuel mixture.
  • the combustion air / fuel mixture 5 forms a flow 7 with a local main flow direction 14
  • An advantage of the described embodiment of the Hyb ⁇ d burner 1 is that, due to the uneven swirl that the flow 7 of the combustion air / fuel mixture 5 supplied to the combustion has, the outflow from the burner itself is uneven, which increases the combustion vibrations is at least reduced.
  • Another advantage is that the flow 7 has a swirl with which the combustion is stabilized.
  • the combustion air 5 upstream of the outflow end 12 forms a uniform flow 7.
  • the uniform flow 7 of the combustion air 5 can be supplied and mixed with fuel 14 upstream, as a result of which a uniform mixture between combustion air 5 and fuel 14 can be achieved. This makes it possible to reduce the amount of NO x compounds formed during the combustion.
  • a swirl grille arranged in the combustion air supply duct 8 can be designed such that a swirl which is uneven in the circumferential direction can be impressed on a flow forming in the combustion air supply duct 8.
  • FIG. 2 shows a view of the swirl elements 15 of the ring channel 4 of the premix burner 3 which are developed in the circumferential direction, the direction 17 shown in FIG. 1 perpendicular to the outer wall 16 of the ring channel 4 being selected as the viewing direction.
  • the swirl elements 15 each have a deflection surface 18.
  • the deflection surfaces 18 each form an outflow angle ⁇ with the local main flow direction 14 (see also FIG. 1).
  • the deflection surfaces 18 of two adjacent swirl elements 20 and 21 have different outflow angles cxi and ⁇ 2 .
  • the flow 7 leaves the swirl grille 6 at the outflow end 12 with a swirl impressed unevenly in the circumferential direction.
  • the swirl elements 20 and the swirl elements 21 are each combined to form a swirl group which have the outflow angle oci or ⁇ 2 .
  • the invention is characterized by a burner in which combustion air or a combustion air / fuel mixture is fed to a combustion in a flow, a swirl which is uneven in the circumferential direction being impressed on the flow.

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)
  • Air Supply (AREA)

Abstract

L'invention concerne un brûleur (1), dans lequel de l'air de combustion (5) ou un mélange air de combustion/combustible (5) est acheminé dans un flux (7) en vue d'un processus de combustion. Le flux (7) est soumis à un mouvement tourbillonnant irrégulier dans le sens périphérique. Pour acheminer l'air de combustion (5) ou le mélange air de combustion/combustible (5), il est prévu un canal d'écoulement dans lequel est monté un dispositif produisant ce mouvement tourbillonnant (6), destiné à imprimer ce mouvement à l'écoulement (7). L'invention concerne en outre le mode d'utilisation d'un brûleur, ainsi qu'un procédé permettant de réduire les vibrations en cours de combustion.
EP99917770A 1998-03-20 1999-03-08 Bruleur pour une turbine a gas Expired - Lifetime EP1064498B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19812322 1998-03-20
DE19812322 1998-03-20
PCT/DE1999/000614 WO1999049264A1 (fr) 1998-03-20 1999-03-08 Bruleur et procede pour reduire les vibrations en cours de combustion

Publications (2)

Publication Number Publication Date
EP1064498A1 true EP1064498A1 (fr) 2001-01-03
EP1064498B1 EP1064498B1 (fr) 2002-11-13

Family

ID=7861710

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99917770A Expired - Lifetime EP1064498B1 (fr) 1998-03-20 1999-03-08 Bruleur pour une turbine a gas

Country Status (5)

Country Link
US (1) US6374593B1 (fr)
EP (1) EP1064498B1 (fr)
JP (1) JP2002507717A (fr)
DE (1) DE59903398D1 (fr)
WO (1) WO1999049264A1 (fr)

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EP1096201A1 (fr) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Brûleur
DE10040869A1 (de) * 2000-08-21 2002-03-07 Alstom Power Nv Verfahren und Vorrichtung zur Unterdrückung von Strömungswirbeln innerhalb einer Strömungskraftmaschine
US6539721B2 (en) * 2001-07-10 2003-04-01 Pratt & Whitney Canada Corp. Gas-liquid premixer
EP1342953A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Turbine à gaz
EP1342952A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Brûleur, procédé de fonctionnement d'un brûleur et turbine à gaz
US6898938B2 (en) * 2003-04-24 2005-05-31 General Electric Company Differential pressure induced purging fuel injector with asymmetric cyclone
DE10345440A1 (de) * 2003-09-30 2005-05-12 Siemens Ag Verfahren, Computerprogramm mit Programmcode-Mitteln und Computerprogramm-Produkt zur Analyse von Einflussgrößen auf einen Brennvorgang in einer Brennkammer unter Verwendung eines trainierbaren, statistischen Modells
ITTO20040309A1 (it) * 2004-05-13 2004-08-13 Ansaldo Energia Spa Metodo per controllare un combustore a gas di una turbina a gas
EP1645805A1 (fr) * 2004-10-11 2006-04-12 Siemens Aktiengesellschaft brûleur pour combustible fluide et procédé pour uriliser un tel brûleur
EP1659339A1 (fr) * 2004-11-18 2006-05-24 Siemens Aktiengesellschaft Procédé de démarrage d'un brûleur
US7874138B2 (en) * 2008-09-11 2011-01-25 Siemens Energy, Inc. Segmented annular combustor
US20120103237A1 (en) * 2010-11-03 2012-05-03 Ronny Jones Tiltable multiple-staged coal burner in a horizontal arrangement
US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US10830442B2 (en) 2016-03-25 2020-11-10 General Electric Company Segmented annular combustion system with dual fuel capability
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system
US10605459B2 (en) 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10584880B2 (en) 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US11002190B2 (en) 2016-03-25 2021-05-11 General Electric Company Segmented annular combustion system
US10641491B2 (en) 2016-03-25 2020-05-05 General Electric Company Cooling of integrated combustor nozzle of segmented annular combustion system
US11428413B2 (en) 2016-03-25 2022-08-30 General Electric Company Fuel injection module for segmented annular combustion system
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
US11156362B2 (en) 2016-11-28 2021-10-26 General Electric Company Combustor with axially staged fuel injection
US10690350B2 (en) 2016-11-28 2020-06-23 General Electric Company Combustor with axially staged fuel injection
KR102245798B1 (ko) * 2019-09-17 2021-04-28 두산중공업 주식회사 연료 노즐 어셈블리 및 이를 포함하는 가스 터빈의 연소기
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11598526B2 (en) * 2021-04-16 2023-03-07 General Electric Company Combustor swirl vane apparatus
US11802693B2 (en) * 2021-04-16 2023-10-31 General Electric Company Combustor swirl vane apparatus
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

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Also Published As

Publication number Publication date
EP1064498B1 (fr) 2002-11-13
US6374593B1 (en) 2002-04-23
WO1999049264A1 (fr) 1999-09-30
JP2002507717A (ja) 2002-03-12
DE59903398D1 (de) 2002-12-19

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