EP2402652A1 - Brenner - Google Patents

Brenner Download PDF

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Publication number
EP2402652A1
EP2402652A1 EP10168107A EP10168107A EP2402652A1 EP 2402652 A1 EP2402652 A1 EP 2402652A1 EP 10168107 A EP10168107 A EP 10168107A EP 10168107 A EP10168107 A EP 10168107A EP 2402652 A1 EP2402652 A1 EP 2402652A1
Authority
EP
European Patent Office
Prior art keywords
attachment
burner
full
jet nozzle
fuel
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Withdrawn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
EP10168107A
Other languages
German (de)
English (en)
French (fr)
Inventor
Siegfried Bode
Matthias Hase
Jürgen MEISL
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
Priority to EP10168107A priority Critical patent/EP2402652A1/de
Priority to JP2013517313A priority patent/JP6005040B2/ja
Priority to EP11728849.8A priority patent/EP2588805B1/de
Priority to PCT/EP2011/061101 priority patent/WO2012001141A1/de
Priority to US13/806,895 priority patent/US20130104554A1/en
Publication of EP2402652A1 publication Critical patent/EP2402652A1/de
Withdrawn legal-status Critical Current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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances

Definitions

  • the present invention relates to a burner according to the preamble of claim 1.
  • the combustion chamber is supplied with compressed air from the compressor.
  • the compressed air is mixed with a fuel, such as oil or gas, and the mixture burned in the combustion chamber.
  • the hot combustion exhaust gases are finally supplied as a working medium via a combustion chamber outlet of the turbine, where they transmit momentum to the blades under relaxation and cooling and thus do work.
  • the vanes serve to optimize the momentum transfer.
  • an injection of the fuel oil via swirl generator in which the oil is mixed with air.
  • the oil within the nozzles used for the injection into a swirling motion is added.
  • This oil nozzle is also referred to as a pressure-swirl nozzle.
  • the oil nozzles can not be arranged so that the mixing of the fuel with the air leads to an optimal result in terms of pressure pulsations.
  • the object of the present invention is therefore to provide a burner which solves the above problem.
  • full jet nozzles produce a full jet without disturbing turbulence.
  • the full jet nozzle has the advantage that a higher fuel pressure is converted into a greater penetration depth.
  • pressure-swirl nozzles smaller drops are formed by a higher pre-pressure, which in turn penetrate less effectively. It follows that a much higher pressure is required for an increased penetration depth for pressure-swirl nozzles than for full-jet nozzles.
  • the jet nozzle e.g. expensive pumps that can deliver more fuel pressure, or avoid piping systems with high pressure ratings.
  • Fig. 1 shows a burner 107 according to the invention.
  • swirl blades 17 are arranged around the lance.
  • the swirl blades 17 are arranged along the circumference of the lance in the housing 12.
  • a compressor air flow 15 is passed into the leading to a combustion chamber part of the burner 107.
  • the air is displaced by the swirl blades 17 in a swirling motion.
  • the lance also comprises a fuel channel 16.
  • the burner 107 further comprises an attachment 13 on the side leading to a combustion chamber.
  • the attachment 13 can be welded to the lance, for example or screwed.
  • the fuel nozzles are arranged in the attachment 13 preferably downstream of the swirl vanes 17 and are fluidically connected to the fuel channel 16, here represented as an oil channel.
  • the fuel channel 16 here represented as an oil channel.
  • eight such burners 107 are arranged in a circle (not shown).
  • the burners 107 are arranged around a pilot burner (not shown) with pilot cone.
  • the plurality of fuel nozzles according to the invention are designed as full jet nozzles 1.
  • the design of the nozzle as a full jet nozzle 1, the full jet nozzle size and also arrangement make it possible to adjust the penetration depth of the fuel so that an advantageous fuel profile is formed.
  • the parameters are the diameter of the full jet nozzles 1 and the number of full jet nozzles 1 available.
  • the fuel distribution is adjusted so that the ignition of the fuel-air mixture is done with a beneficial time delay.
  • the time delay between the injection and the combustion of the fuel is decisive for the formation of thermoacoustic feedback loops, from which combustion chamber pulsations can arise.
  • the full jet nozzles 1 have a length, wherein the length to diameter ratio is at least 1.5, in order to achieve a good mixing. As a result, the divergence of the full jet is small enough, so that it does not come to an unwanted ejection of drops.
  • the full-jet nozzle 1 has the advantage that a higher fuel pressure, especially in one greater penetration depth is implemented.
  • a higher fuel pressure especially in one greater penetration depth is implemented.
  • smaller drops are formed by a higher pre-pressure, which in turn are less effective to penetrate. It follows that a much higher pressure is required for an increased penetration depth for pressure-swirl nozzles than for full-jet nozzles. This can be with the full jet nozzle 1, for example, expensive pumps that can provide more fuel supply pressure, or avoid piping systems with high pressure levels.
  • the Fig. 2 schematically shows a section through the attachment 13 in a perspective view.
  • the center attachment axis of the attachment 13 is identified by the reference numeral 18.
  • the attachment 13 is conical towards the combustion chamber, tapered designed. It comprises several, in the present embodiment four, full jet nozzles 1.
  • the full jet nozzles 1 are arranged on the outer circumference of the attachment 13.
  • the center axes of the full-jet nozzles 1 are identified by the reference numeral 19.
  • the central axes 19 of the full-jet nozzles 1 have an angle 20 to the central attachment axis 18 of the attachment 13.
  • the fuel enters the attachment 13 along the direction of flow indicated by the reference numeral 26 through the fuel channel 16.
  • the fuel is then injected through the full jet nozzles 1 in the direction 25 in the coming of the swirl blades 17 air flow.
  • the central axis 19 of the full-jet nozzles 1 is arranged substantially perpendicularly (90 degrees) to the middle attachment axis 18 of the full-jet nozzles 1.
  • the central axis 19 of the nozzle 1 may be perpendicular to the attachment surface.
  • the steel is introduced vertically into the air stream; a very good mix is the result.
  • an arrangement of 90 ° +/- 30 ° degrees, in particular 90 ° +/- 10 ° degree, from the central axis 19 of the full-jet nozzles 1 to the axis 18 or the top surface results in a very advantageous arrangement.
  • the attachment 13 comprises a cylindrical portion 130 and a tapered portion 140 to a combustion chamber.
  • the conical portion 140 may have a cone angle of 10-20 ° degrees exhibit. Due to this configuration, there is no demolition of the flow at the attachment tip.
  • the full-jet nozzles 1 can be arranged on the conical tapering part 140 of the attachment 13.
  • the position of the full jet nozzles 1 may vary depending on the autoignition time of the mixture. In order to achieve a good fuel distribution, eight to twelve full-jet nozzles per attachment 13 are preferably used (not shown). Also advantageous are six to sixteen full jet nozzles 1 (not shown). These are evenly distributed on the circumference of the article 13. Good fuel distribution is necessary to meet emission limits and avoid soot formation.
  • the full-jet nozzles 1 may be formed as bores in the attachment 13. In terms of mixing, in particular, a length to diameter ratio of six to fourteen is advantageous. Preferred diameter of the full-jet nozzles 1 are 0.55-0.8 mm, also 0.5 -1 mm are advantageous (not shown).
  • solid jet nozzles 1 can easily be adapted to other thermodynamic conditions, which are e.g. in an altered air cross-flow speed, air density or fuel mass flow, perform by the diameter of the full jet nozzles 1 is adjusted accordingly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP10168107A 2010-07-01 2010-07-01 Brenner Withdrawn EP2402652A1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP10168107A EP2402652A1 (de) 2010-07-01 2010-07-01 Brenner
JP2013517313A JP6005040B2 (ja) 2010-07-01 2011-07-01 バーナー装置
EP11728849.8A EP2588805B1 (de) 2010-07-01 2011-07-01 Brenneranordnung
PCT/EP2011/061101 WO2012001141A1 (de) 2010-07-01 2011-07-01 Brenneranordnung
US13/806,895 US20130104554A1 (en) 2010-07-01 2011-07-01 Burner assembly

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10168107A EP2402652A1 (de) 2010-07-01 2010-07-01 Brenner

Publications (1)

Publication Number Publication Date
EP2402652A1 true EP2402652A1 (de) 2012-01-04

Family

ID=43531833

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10168107A Withdrawn EP2402652A1 (de) 2010-07-01 2010-07-01 Brenner
EP11728849.8A Active EP2588805B1 (de) 2010-07-01 2011-07-01 Brenneranordnung

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11728849.8A Active EP2588805B1 (de) 2010-07-01 2011-07-01 Brenneranordnung

Country Status (4)

Country Link
US (1) US20130104554A1 (enExample)
EP (2) EP2402652A1 (enExample)
JP (1) JP6005040B2 (enExample)
WO (1) WO2012001141A1 (enExample)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017116266A1 (en) * 2015-12-30 2017-07-06 General Electric Company Liquid fuel nozzles for dual fuel combustors
CN107023834A (zh) * 2017-04-19 2017-08-08 中国科学院工程热物理研究所 一种多尺度值班火焰的喷嘴及燃烧器
CN111520750A (zh) * 2020-03-25 2020-08-11 西北工业大学 新型燃烧室头部喷油结构

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US9765973B2 (en) 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
US9650959B2 (en) 2013-03-12 2017-05-16 General Electric Company Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9759425B2 (en) * 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
JP5984770B2 (ja) * 2013-09-27 2016-09-06 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器およびこれを備えたガスタービン機関
CN106715870B (zh) 2014-07-02 2018-11-09 诺沃皮尼奥内股份有限公司 燃料分配装置、燃气涡轮发动机和安装方法
CN104315540B (zh) * 2014-09-26 2018-05-25 北京华清燃气轮机与煤气化联合循环工程技术有限公司 燃气轮机燃烧室预混燃料喷嘴
WO2016064391A1 (en) 2014-10-23 2016-04-28 Siemens Energy, Inc. Flexible fuel combustion system for turbine engines
EP3224544A1 (en) * 2014-11-26 2017-10-04 Siemens Aktiengesellschaft Fuel lance with means for interacting with a flow of air and improve breakage of an ejected liquid jet of fuel
US10738704B2 (en) * 2016-10-03 2020-08-11 Raytheon Technologies Corporation Pilot/main fuel shifting in an axial staged combustor for a gas turbine engine
US10508811B2 (en) * 2016-10-03 2019-12-17 United Technologies Corporation Circumferential fuel shifting and biasing in an axial staged combustor for a gas turbine engine
US10393030B2 (en) * 2016-10-03 2019-08-27 United Technologies Corporation Pilot injector fuel shifting in an axial staged combustor for a gas turbine engine
US10739003B2 (en) 2016-10-03 2020-08-11 United Technologies Corporation Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine
US10584877B2 (en) 2017-04-28 2020-03-10 DOOSAN Heavy Industries Construction Co., LTD Device to correct flow non-uniformity within a combustion system
DE102020203422B4 (de) * 2020-03-17 2024-02-01 Dometic Sweden Ab Heizvorrichtung, Freizeitfahrzeug mit Heizvorrichtung und Verfahren zum Heizen von Fluiden in einem Freizeitfahrzeug
US11421883B2 (en) * 2020-09-11 2022-08-23 Raytheon Technologies Corporation Fuel injector assembly with a helical swirler passage for a turbine engine
US20220205637A1 (en) * 2020-12-30 2022-06-30 General Electric Company Mitigating combustion dynamics using varying liquid fuel cartridges
KR102460672B1 (ko) * 2021-01-06 2022-10-27 두산에너빌리티 주식회사 연료 노즐, 연료 노즐 모듈 및 이를 포함하는 연소기
US12025311B2 (en) * 2021-08-24 2024-07-02 Solar Turbines Incorporated Micromix fuel injection air nozzles
US11617981B1 (en) 2022-01-03 2023-04-04 Saudi Arabian Oil Company Method for capturing CO2 with assisted vapor compression
KR102583223B1 (ko) * 2022-01-28 2023-09-25 두산에너빌리티 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스터빈
GB2629434A (en) * 2023-04-28 2024-10-30 Siemens Energy Global Gmbh & Co Kg Fuel lance for burner of gas turbine engine

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US3904119A (en) * 1973-12-05 1975-09-09 Avco Corp Air-fuel spray nozzle
US5680766A (en) * 1996-01-02 1997-10-28 General Electric Company Dual fuel mixer for gas turbine combustor
JPH09303776A (ja) * 1996-05-10 1997-11-28 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器の燃料噴射ノズル
WO1999019670A2 (en) * 1997-10-10 1999-04-22 Siemens Westinghouse Power Corporation FUEL NOZZLE ASSEMBLY FOR A LOW NOx COMBUSTOR
WO2000022347A1 (en) * 1998-10-09 2000-04-20 General Electric Company Fuel injection assembly for gas turbine engine combustor
US6141967A (en) * 1998-01-09 2000-11-07 General Electric Company Air fuel mixer for gas turbine combustor
EP1990580A1 (de) * 2007-05-10 2008-11-12 Siemens Aktiengesellschaft Brennerkomponente für einen Gasturbinenbrenner
WO2010073156A1 (en) * 2008-12-23 2010-07-01 Tck - Societa' A Responsabilita' Limitata A combustion head and a burner comprising the head

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JP2000356344A (ja) * 1999-06-14 2000-12-26 Hitachi Ltd ガスタービン燃焼装置及びその燃焼状態制御方法
JP3860952B2 (ja) * 2000-05-19 2006-12-20 三菱重工業株式会社 ガスタービン燃焼器
JP2002276943A (ja) * 2001-03-14 2002-09-25 Mitsubishi Heavy Ind Ltd ガスタービン用燃料ノズル
US6832481B2 (en) * 2002-09-26 2004-12-21 Siemens Westinghouse Power Corporation Turbine engine fuel nozzle
EP1507119A1 (de) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Brenner und Verfahren zum Betrieb einer Gasturbine
US7316117B2 (en) * 2005-02-04 2008-01-08 Siemens Power Generation, Inc. Can-annular turbine combustors comprising swirler assembly and base plate arrangements, and combinations
RU2300702C1 (ru) * 2006-04-04 2007-06-10 Общество с ограниченной ответственностью "Научно-производственное предприятие "ЭСТ" Способ сжигания топлива и устройство для его осуществления
JP4719059B2 (ja) * 2006-04-14 2011-07-06 三菱重工業株式会社 ガスタービンの予混合燃焼バーナー
EP2085695A1 (de) * 2008-01-29 2009-08-05 Siemens Aktiengesellschaft Brennstoffdüse mit Drallkanal und Verfahren zur Herstellung einer Brennstoffdüse

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3904119A (en) * 1973-12-05 1975-09-09 Avco Corp Air-fuel spray nozzle
US5680766A (en) * 1996-01-02 1997-10-28 General Electric Company Dual fuel mixer for gas turbine combustor
JPH09303776A (ja) * 1996-05-10 1997-11-28 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器の燃料噴射ノズル
WO1999019670A2 (en) * 1997-10-10 1999-04-22 Siemens Westinghouse Power Corporation FUEL NOZZLE ASSEMBLY FOR A LOW NOx COMBUSTOR
US6141967A (en) * 1998-01-09 2000-11-07 General Electric Company Air fuel mixer for gas turbine combustor
WO2000022347A1 (en) * 1998-10-09 2000-04-20 General Electric Company Fuel injection assembly for gas turbine engine combustor
EP1990580A1 (de) * 2007-05-10 2008-11-12 Siemens Aktiengesellschaft Brennerkomponente für einen Gasturbinenbrenner
WO2010073156A1 (en) * 2008-12-23 2010-07-01 Tck - Societa' A Responsabilita' Limitata A combustion head and a burner comprising the head

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017116266A1 (en) * 2015-12-30 2017-07-06 General Electric Company Liquid fuel nozzles for dual fuel combustors
US10830445B2 (en) 2015-12-30 2020-11-10 General Electric Company Liquid fuel nozzles for dual fuel combustors
CN107023834A (zh) * 2017-04-19 2017-08-08 中国科学院工程热物理研究所 一种多尺度值班火焰的喷嘴及燃烧器
CN107023834B (zh) * 2017-04-19 2019-01-08 中国科学院工程热物理研究所 一种多尺度值班火焰的喷嘴及燃烧器
CN111520750A (zh) * 2020-03-25 2020-08-11 西北工业大学 新型燃烧室头部喷油结构
CN111520750B (zh) * 2020-03-25 2022-05-20 西北工业大学 新型燃烧室头部喷油结构

Also Published As

Publication number Publication date
US20130104554A1 (en) 2013-05-02
EP2588805A1 (de) 2013-05-08
EP2588805B1 (de) 2016-04-20
JP6005040B2 (ja) 2016-10-12
JP2013529771A (ja) 2013-07-22
WO2012001141A1 (de) 2012-01-05

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