EP3036482B1 - Zweistoffdüsensystem sowie vorrichtung - Google Patents

Zweistoffdüsensystem sowie vorrichtung Download PDF

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Publication number
EP3036482B1
EP3036482B1 EP14838205.4A EP14838205A EP3036482B1 EP 3036482 B1 EP3036482 B1 EP 3036482B1 EP 14838205 A EP14838205 A EP 14838205A EP 3036482 B1 EP3036482 B1 EP 3036482B1
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EP
European Patent Office
Prior art keywords
gas
fuel
fuel nozzle
liquid
transition zone
Prior art date
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EP14838205.4A
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English (en)
French (fr)
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EP3036482A4 (de
EP3036482A1 (de
Inventor
Timothy S. Snyder
Zhongtao Dai
Randolph J. Smith
Kristin KOPP-VAUGHAN
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RTX Corp
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United Technologies Corp
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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 
    • F23C1/00—Combustion apparatus specially adapted for combustion of two or more kinds of fuel simultaneously or alternately, at least one kind of fuel being either a fluid fuel or a solid fuel suspended in a carrier gas or air
    • F23C1/08—Combustion apparatus specially adapted for combustion of two or more kinds of fuel simultaneously or alternately, at least one kind of fuel being either a fluid fuel or a solid fuel suspended in a carrier gas or air liquid and gaseous fuel
    • 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
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/48—Nozzles
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • the present disclosure relates to radial fuel injection in fuel nozzles, and more specifically, to radial fuel injection in dual fuel nozzle to improve gaseous fuel dispersion and/or penetration.
  • a gas turbine may generally include a fuel nozzle that is configured to supply one or more fuels to the combustor. This fuel may be mixed with air and/or pollution mitigation substances such as, for example, water. Dual fuel nozzles used in propulsion and energy production applications may comprise a radial fuel port. Dispersion and/or penetration of gas fuel may be affected by the location of the radial fuel port. Greater dispersion and/or penetration of gaseous fuel may increase the operating efficiency of a gas turbine.
  • a gas turbine fuel nozzle having the features of the preamble of claim 1 is disclosed in US 2010/308135 A1 .
  • a dual fuel nozzle having the features of the preamble of claim 8 is disclosed in EP 905443 A2 .
  • the invention provides a gas turbine fuel nozzle as set forth in claim 1.
  • the invention also provides a dual fuel gas nozzle as set forth in claim 8.
  • any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step.
  • any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option.
  • any reference to without contact (or similar phrases) may also include reduced contact or minimal contact.
  • phrases such as “make contact with,” “coupled to,” “touch,” “interface with” and “engage” may be used interchangeably. Different surface shading may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.
  • a gas turbine engine may comprise a dual fuel nozzle.
  • the fuel nozzle may define one or more channels.
  • One or more of these channels may be configured to receive a gas and/or a liquid.
  • These channels may be operatively coupled and/or may be in fluid communication with one or more components of a gas turbine engine including, for example, the combustor.
  • the liquid, gas, and/or air supplied through the one or more channels may be conducted or carried from the fuel nozzle to the combustor.
  • the nozzle is configured to provide fuel in the form of a gas or a liquid to the combustor for starting or sustained operation of the gas turbine.
  • the nozzle is configured to provide air, and/or water in either gaseous form or liquid form, or combinations thereof to the combustor for starting or sustained operation of the gas turbine.
  • the gas turbine may be a gas turbine configured to provide power and/or a gas turbine configured to provide propulsion.
  • the gas turbine may be installed or operated in a power plant environment where the gas turbine drives electricity generating devices and supplies power to a structure and/or a utility provider.
  • the gas turbine may be installed on a vehicle such as, for example, an aircraft or other suitable machinery.
  • a gas turbine may comprise a typical dual fuel nozzle comprising a housing 110, a gas supply channel 112 and a liquid supply channel 118.
  • Housing 110 may define a gas distribution channel 114 and a liquid distribution channel 120.
  • Housing 110 may also define a mixing chamber 124.
  • Mixing chamber 124 may be in fluid communication with gas distribution channel 114.
  • Dual fuel nozzle 100 may further comprise a gas port 116 defined in an interior wall 117 of housing 110.
  • Gas port 116 may be located downstream of a shoulder 119 in interior wall 117 substantially near a transition zone 124' of a mixing chamber 124.
  • gas e.g., a gaseous fuel
  • the gas may be discharged through gas port 116 into mixing chamber 124 adjacent to transition zone 124'.
  • liquid may be supplied through liquid supply channel 118 and conducted into liquid distribution channel 120.
  • the liquid may be disbursed through a lip 122.
  • Dual fuel nozzle 100 may further comprise an impeller 126.
  • Housing 110 may define an air supply channel 128 along a centerline A-A' of dual fuel nozzle 100.
  • the impeller may be configured to conduct air through air supply channel 128 into a discharge zone 130.
  • the liquid, fuel and air may be mixed in discharge zone 130.
  • the liquid may be a liquid fuel and/or water. Where the dual fuel nozzle is installed in a power generation application, the liquid may be water that is used to mitigate or minimize carbon monoxide and/or mono-nitrogen oxide emissions (i.e., NO x ).
  • Fuel mixing is shown as letter G.
  • Fuel may be discharged through gas port 116 from fuel distribution channel 114 into mixing chamber 124.
  • Fuel distribution G generally shows that the fuel does not mix well into mixing chamber 124, but rather, remains clustered (e.g., close to) near interior wall 117 as the fuel propagates from mixing chamber 124 to transition zone 124'. This clustering or lack of fuel dispersion and/or penetration may result in inefficient combustion of fuel G.
  • the fluid velocity in mixing chamber 124 generally increases at transition zone 124'. This increase in fluid velocity may minimize fuel distribution G as the fuel propagates from mixing chamber 124 to transition zone 124' causing the fuel to cluster along a portion of interior wall 117 adjacent to transition zone 124'.
  • adjusting the position of fuel port 216 may increase fuel penetration (e.g., the distance the fuel travels into the mixing chamber 224) and dispersion (e.g., the spreading of a mass of fuel across a volume) . More specifically, moving fuel port 216 forward (e.g., in the direction associated with reference A of the A-A' centerline) further away from transition zone 224' may allow fuel discharged through fuel port 216 to further propagate into mixing chamber 224. In this regard, the fluid velocity in mixing chamber 224 may be lower upstream of transition zone 224', allowing for greater fuel penetration in mixing chamber 224.
  • the fuel port 216 is defined by interior wall 217 at shoulder 219.
  • fuel may be distributed or injected into mixing chamber 224 where the fluid velocity in the chamber is relatively low (e.g., the fluid velocity in an upstream portion of mixing chamber 224 may be lower than the fluid velocity in mixing chamber 224 near transition zone 224').
  • the fuel distribution G' demonstrates greater fuel penetration as compared to fuel distribution G, as shown in FIG. 1B .
  • fuel distribution G' illustrates that the fuel propagates across the entire volume of mixing chamber 224. This greater penetration provides for lower fuel density, a more suitable fuel-air mixture, and better ignition efficiency.
  • the fuel distribution G' illustrates that the fuel may propagate into the volume of mixing chamber 224 as opposed to clustering near interior wall 217.
  • the fuel may be conducted through the transition zone 224', and mixed with air supplied through channel 228, and a liquid supplied through channel 220 and lip 222.
  • This air,fuel, and water mixture may be further supplied to the combustor for ignition.
  • the mixture gas (e.g., fuel), liquid (e.g., fuel and/or water), and/or air) may be conducted to the combustor.
  • interior wall 217 may comprise a plurality of gas ports 216.
  • interior wall 217 may define 8-14 gas ports 216 around its diameter.
  • interior wall 217 may define 12 gas ports 216 around its diameter.
  • Gas ports 216 may be substantially aligned with one another around along a diameter of interior wall 217.
  • gas ports 216 may be equally spaced circumferentially around interior wall 217.
  • the holes may be of any suitable diameter (e.g., 0.090 inches - .110 inches/0.2286cm to 0.29784cm) and/or pitch.
  • the pitch may be a function of the shape and/or slope of shoulder 219.
  • the geometry of one or more gas ports 216 and/or number of gas ports may provide a Holdeman Parameter that is greater than the ratio of pitch to diameter.
  • a liquid B may be supplied through liquid supply 218 and conducted to channel 220 and discharged through lip 222 as B'.
  • a gas A may be supplied to gas distribution channel 212 through gas distribution channel 214 and out of gas port 216 into mixing chamber 224 as A'.
  • Air C may be supplied along channel 228 as C'.
  • gas A' and liquid B' may be mixed and supplied into channel 228 and mixed with air C'. The mixture is then conducted to a combustor for gas turbine operation, ignition and/or burning.
  • references to "one embodiment”, “an embodiment”, “various embodiments”, etc. indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Claims (15)

  1. Gasturbinenbrennstoffdüse, Folgendes umfassend:
    ein Gehäuse (210), das eine Mischkammer (224) definiert, die einen Übergangsbereich (224') beinhaltet, wobei das Gehäuse (210) Folgendes umfasst:
    eine innere Wand (217), die einen ersten, stromaufwärtigen Wandabschnitt mit einem ersten Durchmesser, einen zweiten, stromabwärtigen Wandabschnitt mit einem zweiten Durchmesser, der kleiner ist als der erste Durchmesser, und einen geneigten Ansatz (219) umfasst, der den ersten und den zweiten Wandabschnitt miteinander verbindet;
    wobei die innere Wand (217) einen Brenngasanschluss (216) definiert, der dazu konfiguriert ist, ein Brenngas in eine Mischkammer (224) zu leiten, wobei der Brennstoff sich über ein Volumen der Mischkammer (224) ausbreitet, bevor er den Übergangsbereich (224') erreicht;
    dadurch gekennzeichnet, dass:
    der Brenngasanschluss (216) in dem Ansatz (219) definiert ist.
  2. Gasturbinenbrennstoffdüse nach Anspruch 1, ferner eine Flüssigkeitszufuhr (218) umfassend.
  3. Gasturbinenbrennstoffdüse nach Anspruch 2, wobei die Flüssigkeitszufuhr (218) dazu konfiguriert ist, eine Flüssigkeit zu dem Übergangsbereich (224') zu leiten.
  4. Gasturbinenbrennstoffdüse nach Anspruch 3, wobei die Flüssigkeit mindestens eines von einem flüssigen Brennstoff und Wasser ist.
  5. Gasturbinenbrennstoffdüse nach einem der vorhergehenden Ansprüche, wobei der Ansatz (219) eine Vielzahl von Brenngasanschlüssen (216) definiert.
  6. Gasturbinenbrennstoffdüse nach einem der vorhergehenden Ansprüche, wobei der Brenngasanschluss (216) einen Durchmesser von ungefähr 2,286 mm (0,090 in) bis ungefähr 2,794 mm (0,110 in) aufweist.
  7. Gasturbinenbrennstoffdüse nach einem der vorhergehenden Ansprüche, wobei sich das Brenngas von der inneren Wand (217) weg ausbreitet.
  8. Zweistoffdüse, Folgendes umfassend:
    eine Gaszufuhr;
    eine innere Wand (217), die einen ersten, stromaufwärtigen Wandabschnitt mit einem ersten Durchmesser, einen zweiten, stromabwärtigen Wandabschnitt mit einem zweiten Durchmesser, der kleiner ist als der erste Durchmesser, und einen geneigten Ansatz (219) umfasst, der den ersten und den zweiten Wandabschnitt miteinander verbindet;
    ein Gehäuse (210), das einen Gasaustrittsbereich definiert, der ein Gas von dem Gasanschluss (216) empfängt, wobei der Gasaustrittsbereich einen Übergangsbereich (224') umfasst;
    eine Flüssigkeitszufuhr (218); und
    einen Flüssigkeitszufuhrkanal (220), der dazu konfiguriert ist, eine Flüssigkeit in den Übergangsbereich (224') zu leiten; dadurch gekennzeichnet, dass
    der Ansatz (219) einen Gasanschluss (216) definiert.
  9. Zweistoffdüse nach Anspruch 8, wobei die Flüssigkeit ein flüssiger Brennstoff ist.
  10. Zweistoffdüse nach Anspruch 8, wobei die Flüssigkeit Wasser ist und zugeführt wird, um Emissionen zu reduzieren.
  11. Zweistoffdüse nach Anspruch 8, 9 oder 10, wobei der Ansatz (219) eine Vielzahl von Gasanschlüssen (216) definiert.
  12. Zweistoffdüse nach einem der Ansprüche 8 bis 11, wobei das Gas ein Volumen des Gasaustrittsbereichs (224) durchdringt.
  13. Zweistoffdüse nach einem der Ansprüche 8 bis 12, wobei sich das Gas von der inneren Wand (217) weg ausbreitet.
  14. Zweistoffdüse nach einem der Ansprüche 8 bis 13, wobei sich das Gas und die Flüssigkeit in dem Übergangsbereich (224') mischen.
  15. Zweistoffdüse nach einem der Ansprüche 8 bis 14, ferner einen Luftkanal (228) umfassend, der dazu konfiguriert ist, Luft zu dem Übergangsbereich (224') zu leiten, wobei die Luft mit der Flüssigkeit und dem Gas gemischt wird.
EP14838205.4A 2013-08-20 2014-08-19 Zweistoffdüsensystem sowie vorrichtung Active EP3036482B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201361867869P 2013-08-20 2013-08-20
PCT/US2014/051582 WO2015026760A1 (en) 2013-08-20 2014-08-19 Dual fuel nozzle system and apparatus

Publications (3)

Publication Number Publication Date
EP3036482A1 EP3036482A1 (de) 2016-06-29
EP3036482A4 EP3036482A4 (de) 2017-05-03
EP3036482B1 true EP3036482B1 (de) 2020-10-21

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EP14838205.4A Active EP3036482B1 (de) 2013-08-20 2014-08-19 Zweistoffdüsensystem sowie vorrichtung

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US (1) US20160201897A1 (de)
EP (1) EP3036482B1 (de)
WO (1) WO2015026760A1 (de)

Families Citing this family (7)

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Publication number Priority date Publication date Assignee Title
US10605459B2 (en) * 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10578306B2 (en) * 2017-06-16 2020-03-03 General Electric Company Liquid fuel cartridge unit for gas turbine combustor and method of assembly
DE102022201182A1 (de) 2022-02-04 2023-08-10 Rolls-Royce Deutschland Ltd & Co Kg Düsenbaugruppe mit eine Kraftstoffleitung passierender Verbindungsleitung in einem Düsenhauptkörper für eine Luftströmung
DE102022207492A1 (de) 2022-07-21 2024-02-01 Rolls-Royce Deutschland Ltd & Co Kg Düsenvorrichtung zur Zugabe zumindest eines gasförmigen Kraftstoffes und eines flüssigen Kraftstoffes, Set, Zuleitungssystem und Gasturbinenanordnung
DE102022207493A1 (de) 2022-07-21 2024-02-01 Rolls-Royce Deutschland Ltd & Co Kg Verbindungsvorrichtung zur Strömungsverbindung zwischen einem Kraftstoff- Zuleitungssystem und einer Düsenvorrichtung, Düsenvorrichtung und Gasturbinenanordnung
DE102022208339A1 (de) 2022-08-10 2024-02-15 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung zum Betrieb mit flüssigem und/oder gasförmigem Kraftstoff, Gasturbinenanordnung und Verfahren
DE102022210807A1 (de) 2022-10-13 2024-04-18 Rolls-Royce Deutschland Ltd & Co Kg Antriebssystem für ein Flugzeug, Flugzeug mit einem Antriebssystem und Verfahren zum Betreiben eines Flugzeugs

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JP4683787B2 (ja) * 2001-03-09 2011-05-18 大阪瓦斯株式会社 バーナ装置及びガスタービンエンジン
US20020162333A1 (en) * 2001-05-02 2002-11-07 Honeywell International, Inc., Law Dept. Ab2 Partial premix dual circuit fuel injector
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US6871501B2 (en) * 2002-12-03 2005-03-29 General Electric Company Method and apparatus to decrease gas turbine engine combustor emissions
JP5472863B2 (ja) 2009-06-03 2014-04-16 独立行政法人 宇宙航空研究開発機構 ステージング型燃料ノズル
US8661825B2 (en) * 2010-12-17 2014-03-04 General Electric Company Pegless secondary fuel nozzle including a unitary fuel injection manifold
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JP5772245B2 (ja) * 2011-06-03 2015-09-02 川崎重工業株式会社 燃料噴射装置

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Also Published As

Publication number Publication date
US20160201897A1 (en) 2016-07-14
EP3036482A4 (de) 2017-05-03
WO2015026760A1 (en) 2015-02-26
EP3036482A1 (de) 2016-06-29

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