WO1999019670A2 - DISTRIBUTEUR DE COMBUSTIBLE POUR DISPOSITIF COMBUSTOR A FAIBLE TENEUR EN NOx - Google Patents

DISTRIBUTEUR DE COMBUSTIBLE POUR DISPOSITIF COMBUSTOR A FAIBLE TENEUR EN NOx Download PDF

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Publication number
WO1999019670A2
WO1999019670A2 PCT/US1998/021338 US9821338W WO9919670A2 WO 1999019670 A2 WO1999019670 A2 WO 1999019670A2 US 9821338 W US9821338 W US 9821338W WO 9919670 A2 WO9919670 A2 WO 9919670A2
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
fuel nozzle
assembly according
nozzle assembly
tips
Prior art date
Application number
PCT/US1998/021338
Other languages
English (en)
Other versions
WO1999019670A3 (fr
Inventor
David Marchant Parker
Stephen Eugene Mumford
Original Assignee
Siemens Westinghouse Power Corporation
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 Westinghouse Power Corporation filed Critical Siemens Westinghouse Power Corporation
Priority to AU19951/99A priority Critical patent/AU1995199A/en
Publication of WO1999019670A2 publication Critical patent/WO1999019670A2/fr
Publication of WO1999019670A3 publication Critical patent/WO1999019670A3/fr

Links

Classifications

    • 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, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • 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
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11002—Liquid fuel burners with more than one nozzle

Definitions

  • the present invention relates to a fuel nozzle assembly for a combustor. More specifically, the present invention relates to a fuel nozzle assembly for a low NOx combustor such as that used in a gas turbine.
  • fuel is burned in compressed air, produced by a compressor, in one or more combustors.
  • combustors had a primary combustion zone in which an approximately stoichiometric mixture of fuel and air was formed and burned in a diffusion type combustion process. Additional air was introduced into the combustor downstream of the primary combustion zone.
  • Such fuel nozzle assemblies typically comprised a support flange from which a single tubular member extended. A liquid fuel nozzle was threaded onto the end of the tubular member. Passages in the support flange and tubular member supplied liquid fuel to the nozzle.
  • a fuel nozzle assembly of this type in shown in U.S. Patent No. 4,891,935 (McLaurin et al.).
  • One such fuel nozzle assembly features a nozzle block attached to the front end of the combustor.
  • Fuel supply tubes in which filters are disposed, are connected to each nozzle block.
  • a number of long tubular fuel pegs project axially from each nozzle block into the combustor.
  • Each fuel peg has a nozzle tip that is welded to its distal end and in which a number of fuel injectors are disposed.
  • the fuel pegs extend through a device that swirls the incoming combustion air so that the nozzle tips are disposed downstream of the swirler.
  • fuel is introduced into a swirling flow of air by a plurality of dispersed fuel nozzles.
  • a fuel nozzle assembly of this type is shown in U.S. Patent No.
  • Such fuel nozzle assemblies have also featured thermal shields that reduce the thermal stresses within the nozzle tip.
  • thermal shields are created by internal sleeves that form annular gaps that retard the conduction of heat from the hot distal end of the fuel peg to the liquid fuel flowing through its central passage.
  • the fuel injectors in such nozzle tips employ relatively small fuel passages that have a tendency to become clogged, for example, by carbon deposits formed by burnt fuel, or by foreign matter that originates in the fuel passages downstream of the supply piping filter and that is carried along by the fuel flow to the injectors. Since the nozzle tips are welded to the fuel pegs, servicing and cleaning of the injectors, which is a time consuming operation, requires removal of the entire nozzle assembly. This can result in costly downtime of the gas turbine or, at the very least, require that the user undertake the cost of purchasing an entire set of replacement nozzles.
  • a fuel nozzle assembly comprising a nozzle block having a plurality of first fuel passages formed therein, and a plurality of elongate members extending from the nozzle block.
  • a second fuel passage is formed in each of the elongate members, with each of the second fuel passages being in flow communication with one of the first fuel passages in the nozzle block.
  • a fuel nozzle tip is provided for each of the elongate members.
  • Each of the fuel nozzle tips has at least one fuel discharge port formed therein that is in flow communication with the second fuel passage of its elongate member.
  • Means are provided for rotatably attaching and detaching each of the fuel nozzle tips from its elongate member, and for preventing rotation of each of the fuel nozzle tips with respect to its elongate member.
  • the rotatable attaching and detaching means comprises a threaded joint formed between each of the fuel nozzle tips and its respective elongate member.
  • a conical filter is disposed in the second fuel passage of each of the elongate members adjacent its outlet.
  • the invention also encompasses a method of assembling a fuel nozzle assembly having a fuel nozzle tip and a member forming a passage that supplies fuel to the nozzle tip, comprising the steps of (i) threading the fuel nozzle tip onto the member so that a deformable portion of the nozzle tip is disposed adjacent a notch formed in the member, and (ii) deforming the deformable portion of the nozzle tip so that the deformable portion protrudes into the notch, thereby preventing further rotation of the nozzle tip about the member.
  • Figure 1 is longitudinal cross section through a portion of a gas turbine, partially schematic, incorporating the fuel nozzle assembly of the current invention, in the vicinity of the combustion section.
  • Figure 2 is an isometric view of the fuel nozzle assembly shown in
  • Figure 3 is partial longitudinal cross section through one of the fuel pegs shown in Figure 2.
  • Figure 4 is a detailed view of a portion of the longitudinal cross section through the fuel peg shown in Figure 3 in the vicinity of the nozzle tip.
  • Figure 5 is a transverse cross section taken through line V-V shown in Figure 4.
  • FIG. 1 the combustion section 2 of a gas turbine.
  • the gas turbine is comprised of a compressor 1 that is driven by a turbine 3 via a rotor shaft 4.
  • ambient air is drawn into the compressor 1 and compressed.
  • the compressed air 6 produced by the compressor 1 is directed to the combustion section 2, which includes one or more combustors 8 disposed within a chamber 10 formed by a cylindrical shell 12.
  • a fuel nozzle assembly 18 located at the front end of the combustor 8, serves to inject liquid fuel 20 and/or gaseous fuel 21 into the combustor downstream of air swirlers 19.
  • the fuel is burned in the compressed air 6 within the combustor 8, thereby producing a hot compressed gas 16.
  • the hot compressed gas 16 produced by the combustor 8 is directed to the turbine 3 by a duct 14 where it is expanded, thereby producing shaft horsepower for driving the compressor 1, as well as a load, such as an electric generator.
  • the expanded gas produced by the turbine 3 is exhausted, either to the atmosphere directly or, in a combined cycle plant, to a heat recovery steam generator and then to atmosphere.
  • each fuel nozzle assembly 18 is comprised of a nozzle block 28 from which a number of elongate fuel pegs 32 axially extend in the downstream direction.
  • a pilot fuel nozzle 31 also extends from the nozzle block 28.
  • Supply pipes 25, 26, 27 and 29 are connected to the nozzle block 28.
  • Liquid fuel 20 is supplied to the nozzle block via supply tubes 25.
  • Liquid pilot fuel 23 is supplied to the nozzle block 28 via supply tube 35.
  • Gaseous fuel 21 is supplied to the nozzle block 28 via supply pipes 26.
  • Gaseous pilot fuel 22 is supplied to the nozzle block 28 via supply pipe 27.
  • Supplemental gaseous fuel 24 is supplied to the nozzle block via supply pipe 29. From the nozzle block 28, the supplemental gas 24, which premixes with the air to reduce NOx formation, is directed to an injection ring 30 that surrounds the pilot nozzle 31.
  • each fuel peg 32 is substantially hollow and is comprised of inner and outer tubular members 48 and 49, respectively, that are joined at the distal end 33 of the fuel peg. Upstream of the distal end 33, the members 48 and 49 form an annular passage 41.
  • the annular passage 41 receives the flow of gaseous fuel 21 from a passage 40 formed within nozzle block 28 that is supplied with gaseous fuel from one of the supply pipes 26.
  • the annular passage 41 directs the gaseous fuel 21 to four gaseous fuel discharge ports 54 spaced around the distal end of the outer tubular member 49.
  • the discharge ports 54 direct streams of gaseous fuel 21' into the combustor 8.
  • the inner tubular member 48 of the fuel peg 32 forms a central passage 43.
  • the inlet of the central passage 43 receives liquid fuel 20 from a passage formed in the nozzle block 28 that is supplied with liquid fuel by one of the supply tubes 25.
  • the central passage 43 directs the liquid fuel 20 to a conical filter 62 disposed adjacent the outlet of passage 43.
  • the filter 62 is formed from a 117 micron mesh screen.
  • the liquid fuel 20 is directed by a passage 44, formed in a thermal shield 60, to a central passage 46 form in the nozzle tip 34.
  • the nozzle tip central passage 46 distributes the liquid fuel 20 to four radially extending passages 45.
  • Each of the radial passages 45 direct the fuel to a fuel injector 56, which discharges a spray 20' of liquid fuel into the air at an angle of slightly less than 90° with respect to the .axial center line of the combustor 8.
  • the fuel nozzle tip 34 is comprised of a body portion 50 and a shroud portion 52 that extends axially from the body portion in the upstream direction and that encircles the distal end 33 of the fuel peg 32.
  • female threads 58 are formed in the inside surface of the shroud 52 that mate with male threads 59 formed on the distal end 33 of the fuel peg 32.
  • the threads 58 and 59 allow the nozzle tip 34 to be threaded onto the fuel peg distal end 33 so that it can be readily removed from the fuel peg 32 and replaced with a new nozzle tip whenever servicing or cleaning of the nozzle tip is required.
  • liquid fuel injectors 56 are evenly spaced around the circumference of the nozzle tip 34.
  • threading the nozzle tips 34 onto the fuel pegs 32 results in essentially random circumferential orientation of the fuel injectors 56, the inventors have found that the spray pattern from each injector is sufficiently broad to eliminate the need for precise control of injector orientation.
  • the fuel injectors 56 are installed, preferably by brazing, into recesses 64 formed in the nozzle tip body 50 and are supplied with liquid fuel 20 by the radial passages 45, as previously discussed.
  • Each fuel injector 56 contains a liquid fuel discharge port 57.
  • the fuel injectors employ micro lamination technology, in which a number of thin plates, each of which contains a fuel passage, are bonded together to form a single unit.
  • Such fuel injectors are disclosed in U.S. Patent No. 5,435,884, incorporated by reference herein in its entirety, .and are commercially available from Parker-Hannifin of Andover, Ohio.
  • the thermal shield 60 is disposed in the distal end 33 of the fuel peg 32.
  • the thermal shield 60 is comprised of a sleeve in which the central passage 44 is formed and which forms an annular gap 36 inside the distal end 33 of the fuel peg 32.
  • the annular gap 36 serves to retard the conduction of heat from the hot distal end 33 of the fuel peg 32 to the liquid fuel 20 flowing through the central passage 43, thereby reducing thermal stresses in the fuel nozzle tip 34 and preventing the formation of coke deposits within the passages of the fuel injectors 56.
  • a seal 72 is formed between the fuel peg 32 and the nozzle tip 34.
  • an annular groove 70 is formed in the front face 66 of the distal end 33 of the fuel peg 32.
  • An elastically deformable C-shaped metallic seal ring 72 is disposed in the groove 70. Initially, the ring 72 is relatively wide in cross section.
  • the rear face 68 of the nozzle tip 32 contacts the ring 72 and elastically compresses its sides so as to flatten the C-shape, thereby forming a tight seal between the mating faces 66 and 68 of the fuel peg and the nozzle tip.
  • the present invention has been discussed with reference to a fuel nozzle assembly for a particular low NOx combustor, the invention is also applicable to other types of fuel nozzle assemblies in which it is important that the nozzle tips be removable and/or in which it is desirable to filter out foreign matter as close as possible to the fuel discharge ports. Consequently, the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof .and, accordingly, reference should be made to the appended claims, rather than to the foregoing specification, as indicating the scope of the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Abstract

L'invention porte sur un distributeur de combustible pour dispositif combustor à faible teneur en NOx, ce distributeur comportant une pluralité de tubes (32) à combustible s'étendant axialement à partir d'un bloc d'ajutages pourvu de voies d'alimentation en combustible. Un embout d'ajutage (34) pourvu d'une pluralité d'injecteurs (56) de combustible liquide est couplé à chaque tube au moyen d'un joint (58, 59) fileté, ce qui permet de retirer facilement les embouts des tubes pour les nettoyer et les entretenir. Au niveau du distributeur, une partie de chaque ajutage peut se déformer de façon à faire saillie dans une encoche (74) formée dans le tube à combustible, ce qui empêche les embouts des ajutages de se desserrer en rotation. Un joint (72) en C métallique est placé entre chaque embout d'ajutage et son tube correspondant de façon à se déformer élastiquement lorsque l'embout est vissé sur le tube. Un filtre (62) est placé à côté de l'orifice d'évacuation d'un passage central formé dans le tube, et retire les matières étrangères des passages amont qui ont été transportées par le combustible.
PCT/US1998/021338 1997-10-10 1998-10-09 DISTRIBUTEUR DE COMBUSTIBLE POUR DISPOSITIF COMBUSTOR A FAIBLE TENEUR EN NOx WO1999019670A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU19951/99A AU1995199A (en) 1997-10-10 1998-10-09 Fuel nozzle assembly for a low nox combustor

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US94843697A 1997-10-10 1997-10-10
US08/948,436 1997-10-10

Publications (2)

Publication Number Publication Date
WO1999019670A2 true WO1999019670A2 (fr) 1999-04-22
WO1999019670A3 WO1999019670A3 (fr) 1999-06-24

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PCT/US1998/021338 WO1999019670A2 (fr) 1997-10-10 1998-10-09 DISTRIBUTEUR DE COMBUSTIBLE POUR DISPOSITIF COMBUSTOR A FAIBLE TENEUR EN NOx

Country Status (2)

Country Link
AU (1) AU1995199A (fr)
WO (1) WO1999019670A2 (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1013990A2 (fr) * 1998-12-24 2000-06-28 Mitsubishi Heavy Industries, Ltd. Buse à deux combustibles
JP2003106528A (ja) * 2001-08-23 2003-04-09 Delavan Inc 複式噴射器
EP2107304A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Buse de pulvérisation tourbillonnant destinée à la pulvérisation de carburant liquide et son procédé de fabrication, porte-glicleur pour un brûleur doté de la buse de pulvérisation rotative
JP2010513838A (ja) * 2006-12-22 2010-04-30 シーメンス アクチエンゲゼルシヤフト ガスタービンにおけるバーナ
EP2400216A1 (fr) * 2010-06-23 2011-12-28 Alstom Technology Ltd Lance de brûleur post-combustion
EP2402652A1 (fr) * 2010-07-01 2012-01-04 Siemens Aktiengesellschaft Brûleur
WO2015052078A1 (fr) * 2013-10-11 2015-04-16 Siemens Aktiengesellschaft Insert de protection contre la chaleur pour conduite de carburant
WO2015187785A1 (fr) * 2014-06-03 2015-12-10 Siemens Aktiengesellschaft Ensemble injecteur de carburant avec composants amovibles
DE102014220689A1 (de) * 2014-10-13 2016-04-14 Siemens Aktiengesellschaft Brennstoffdüsenkörper
WO2018132185A1 (fr) * 2017-01-11 2018-07-19 Siemens Energy, Inc. Accessoire de fixation mécanique d'une fusée à combustible sur une base de boîtier de support
KR20190047521A (ko) * 2017-10-27 2019-05-08 두산중공업 주식회사 연료 노즐, 이를 포함하는 연소기 및 가스 터빈
CN113803744A (zh) * 2021-09-27 2021-12-17 中国联合重型燃气轮机技术有限公司 燃烧室入料装置及入料系统
US11230976B2 (en) 2017-07-14 2022-01-25 General Electric Company Integrated fuel nozzle connection

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4891935A (en) 1987-10-23 1990-01-09 Westinghouse Electric Corp. Fuel nozzle assembly for a gas turbine engine
US5415000A (en) 1994-06-13 1995-05-16 Westinghouse Electric Corporation Low NOx combustor retro-fit system for gas turbines

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3441223A (en) * 1967-03-08 1969-04-29 Parker Hannifin Corp Nozzle
US4595143A (en) * 1983-07-20 1986-06-17 Parker-Hannifin Corporation Air swirl nozzle
US5247790A (en) * 1992-09-18 1993-09-28 Westinghouse Electric Corp. Gas turbine fuel nozzle with replaceable cap
US5328101A (en) * 1993-08-27 1994-07-12 General Electric Company Gas turbine fuel nozzle seal
DK32196A (da) * 1996-03-19 1997-07-04 Danfoss As Dyseenhed til en oliebrænder

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4891935A (en) 1987-10-23 1990-01-09 Westinghouse Electric Corp. Fuel nozzle assembly for a gas turbine engine
US5415000A (en) 1994-06-13 1995-05-16 Westinghouse Electric Corporation Low NOx combustor retro-fit system for gas turbines

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1013990A3 (fr) * 1998-12-24 2001-01-10 Mitsubishi Heavy Industries, Ltd. Buse à deux combustibles
US6434945B1 (en) 1998-12-24 2002-08-20 Mitsubishi Heavy Industries, Ltd. Dual fuel nozzle
EP1013990A2 (fr) * 1998-12-24 2000-06-28 Mitsubishi Heavy Industries, Ltd. Buse à deux combustibles
JP2003106528A (ja) * 2001-08-23 2003-04-09 Delavan Inc 複式噴射器
EP1286111A3 (fr) * 2001-08-23 2004-04-28 Delavan Inc. Injecteur multiplex
US6755024B1 (en) 2001-08-23 2004-06-29 Delavan Inc. Multiplex injector
JP2010513838A (ja) * 2006-12-22 2010-04-30 シーメンス アクチエンゲゼルシヤフト ガスタービンにおけるバーナ
US8869534B2 (en) 2006-12-22 2014-10-28 Siemens Aktiengesellschaft Burner for a gas turbine
EP2107304A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Buse de pulvérisation tourbillonnant destinée à la pulvérisation de carburant liquide et son procédé de fabrication, porte-glicleur pour un brûleur doté de la buse de pulvérisation rotative
WO2009121743A1 (fr) * 2008-04-01 2009-10-08 Siemens Aktiengesellschaft Buse de pulvérisation rotative destinée à pulvériser un combustible liquide et son procédé de fabrication, porte-buse pour brûleur comprenant la buse de pulvérisation rotative
EP2400216A1 (fr) * 2010-06-23 2011-12-28 Alstom Technology Ltd Lance de brûleur post-combustion
US8943831B2 (en) 2010-06-23 2015-02-03 Alstom Technology Ltd Lance of a burner
EP2402652A1 (fr) * 2010-07-01 2012-01-04 Siemens Aktiengesellschaft Brûleur
WO2012001141A1 (fr) * 2010-07-01 2012-01-05 Siemens Aktiengesellschaft Ensemble brûleur
CN105637294A (zh) * 2013-10-11 2016-06-01 西门子公司 用于燃料管道的热防护插入件
WO2015052078A1 (fr) * 2013-10-11 2015-04-16 Siemens Aktiengesellschaft Insert de protection contre la chaleur pour conduite de carburant
RU2626915C1 (ru) * 2013-10-11 2017-08-02 Сименс Акциенгезелльшафт Теплозащитная вставка для трубопровода топливной системы
WO2015187785A1 (fr) * 2014-06-03 2015-12-10 Siemens Aktiengesellschaft Ensemble injecteur de carburant avec composants amovibles
DE102014220689A1 (de) * 2014-10-13 2016-04-14 Siemens Aktiengesellschaft Brennstoffdüsenkörper
US10591165B2 (en) 2014-10-13 2020-03-17 Siemens Aktiengesellschaft Fuel nozzle body
WO2018132185A1 (fr) * 2017-01-11 2018-07-19 Siemens Energy, Inc. Accessoire de fixation mécanique d'une fusée à combustible sur une base de boîtier de support
US11230976B2 (en) 2017-07-14 2022-01-25 General Electric Company Integrated fuel nozzle connection
EP3428537B1 (fr) * 2017-07-14 2022-11-16 General Electric Company Chambre de combustion de turbomachine comprnant une connexion intégrée de buse à combustible
KR20190047521A (ko) * 2017-10-27 2019-05-08 두산중공업 주식회사 연료 노즐, 이를 포함하는 연소기 및 가스 터빈
CN113803744A (zh) * 2021-09-27 2021-12-17 中国联合重型燃气轮机技术有限公司 燃烧室入料装置及入料系统
CN113803744B (zh) * 2021-09-27 2023-03-10 中国联合重型燃气轮机技术有限公司 燃烧室入料装置及入料系统

Also Published As

Publication number Publication date
AU1995199A (en) 1999-05-03
WO1999019670A3 (fr) 1999-06-24

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