EP2430362A1 - Injecteurs de carburant à plusieurs prémélangeurs - Google Patents

Injecteurs de carburant à plusieurs prémélangeurs

Info

Publication number
EP2430362A1
EP2430362A1 EP09760348A EP09760348A EP2430362A1 EP 2430362 A1 EP2430362 A1 EP 2430362A1 EP 09760348 A EP09760348 A EP 09760348A EP 09760348 A EP09760348 A EP 09760348A EP 2430362 A1 EP2430362 A1 EP 2430362A1
Authority
EP
European Patent Office
Prior art keywords
fuel
premixers
fuel nozzle
swirler
nozzle
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Withdrawn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
EP09760348A
Other languages
German (de)
English (en)
Inventor
Kevin W. Mcmahan
Krishna Kumar Venkataraman
Jonathan D. Berry
Sergey Aleksandrovich Stryapunin
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2430362A1 publication Critical patent/EP2430362A1/fr
Withdrawn legal-status Critical Current

Links

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
    • F23R3/286—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 
    • 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
    • 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
    • F23D14/62—Mixing devices; Mixing tubes
    • F23D14/64—Mixing devices; Mixing tubes with injectors
    • 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
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air

Definitions

  • the present application relates generally to gas turbine engines and more particularly relates to the use of fuel nozzles with one fuel supply and mounting column and multiple premixers for premixing prior to combustion.
  • Current fuel nozzle designs for gas turbine combustion systems generally include one central mounting and fuel supply center body per fuel nozzle or a separate fuel supply. Several fuel and air circuits may be contained within the center body. When the fuel nozzle counts is in the range of about four to six nozzles, current combustion chambers with the center bodies generally present no problem from the standpoint of distributing airflow to the more central nozzles.
  • the present application thus provides a fuel nozzle for use in a gas turbine.
  • the fuel nozzle may include a mounting flange, a number of premixers attached to each other, and a number of gas pathways extending from the mounting flange to the number of premixers.
  • the present application further provides a combustion chamber.
  • the combustion chamber may include a center nozzle with a fuel passage and a premixer and a number of outer nozzles.
  • Each of the outer nozzles may include a number of fuel passages, and a number of premixers.
  • the present application further provides a fuel nozzle for use in a gas turbine.
  • the fuel nozzle may include a mounting flange, a number of premixers attached to each other, a number of gas tubes extending from the mounting flange to the premixers, and an outer shell surrounding the fuel tubes.
  • FIG. 1 is a schematic view of a gas turbine engine.
  • Fig. 2 is a perspective view of a known standard single center body fuel nozzle.
  • Fig. 3 is a perspective view of a known combustion chamber with a number of nozzles having a single premixer per center body.
  • Fig. 4 is a perspective view of a multiple premixer fuel nozzle as is described herein.
  • Fig. 5 is a perspective view of a combustion chamber with a number of nozzles having multiple premixers per center body as is shown in Fig. 4.
  • Fig. 6 is side cross-section view of an alternative embodiment of a multiple premixer fuel nozzle as is described herein.
  • Fig. 1 shows a schematic view of a gas turbine engine 10.
  • the gas turbine engine 10 may include a compressor 20 to compress an incoming flow of air.
  • the compressor 20 delivers the compressed flow of air to a combustor 30.
  • the combustor 30 mixes the compressed flow of air with a compressed flow of fuel and ignites the mixture.
  • the gas turbine engine 10 may include any number of combustors 30.
  • the hot combustion gases are in turn delivered to a turbine 40.
  • the hot combustion gases drive the turbine 40 so as to produce mechanical work.
  • the mechanical work produced in the turbine 40 drives the compressor 20 and an external load 50 such as an electrical generator and the like.
  • the gas turbine engine may use natural gas, various types of syngas, and other types of fuels. _ _ . _ Other types of gas turbine engines 10 may be used herein.
  • the gas turbine engine 10 may have other configurations and may use other types of components. Multiple gas turbine engines 10, other types of turbines, and other types of power generation equipment may be used herein together.
  • Fig. 2 shows a known fuel nozzle 100.
  • the fuel nozzle 100 may include a flange 110 on one end that leads to a premixer 115.
  • the nozzle 100 may include a center body tube 120 that extends from the flange 110 and through the premixer 115. Positioned within the center body tube 120 may be a purge air pathway 130 extending therethrough.
  • a number of fuel pathways 140 may encircle the purge air pathway 130 and may extend from the flange 110 through the center body tube 120.
  • the fuel nozzle 100 also may include a swirler 150 positioned with the center body tube 120 of the premixer 115.
  • the swirler 150 may extend from the center body tube 120 to a burner tube 160.
  • the swirler 150 may include a number of vanes 170.
  • the fuel pathways 140 may extend from the flange 110 through the center body tube 120 in-part and may exit via the vanes 170 of the swirler 150.
  • the premixer 115 of the fuel nozzle 100 also may include an inlet section 190 for the admission of air through the swirler 150.
  • Other configurations of the fuel nozzle 100 and the components thereof may be used herein.
  • gas may enter the flange 110, pass into the premixer 115, and exit from the vanes 170 of the swirler 150.
  • the gas flow may mix with an incoming airflow from the inlet section 190.
  • the gas and air flows thus may mix within the premixer 115 and then may be ignited downstream of the fuel nozzle 100.
  • multiple fuel nozzles 100 may be mounted within an end cover assembly 200 of a combustion chamber 205. As is shown, each of the nozzles has a single fuel supply tube 210.
  • the use of the multiple nozzles 100 may create a circuitous path 220 for the airflow, at least with respect to one or more center nozzles 230. This restricted airflow between the center nozzles 230 and a number of outer fuel nozzles 240, however, may cause unacceptable variations in the airflow. These variations may cause uneven temperatures within the combustion chamber 205 as a whole. As described above, these uneven temperatures may lead to increase emissions and durability concerns.
  • Fig. 4 shows a multiple premixer fuel nozzle 250 as is described herein.
  • the multiple premixer fuel nozzle 250 also may include a flange 260 leading to a center body tube 270.
  • a purge pathway 280 may extend from the flange 260 and through the center body tube 270.
  • a number of fuel pathways 290 may extend from the flange 260 and through the center body tube 270.
  • Other configurations may be used herein.
  • the multiple premixer fuel nozzle 250 may include a number of premixers 300. Although three (3) premixers 300 are shown, any number of premixers 300 may be used. Each premixer 300 may include a s wirier 310 positioned therein. As described above, each swirler 310 may include a number of vanes 320. The fuel pathways 290 may pass through the flange 260, through the center body tube 270 in part, into each premixer 300, and exit about the vanes 320 of the swirler 310. Each premixer 300 also may include a burner tube 335 positioned about the swirler 310 and an air inlet section 340 in a manner similar to that described above
  • gas flows through the fuel pathways 290 and then into the vanes 320 of the swirler 310 of each premixer 300. Likewise, air passes through the inlet sections 340 and the swirlers 310 so as to mix with the gas within the burner tube 335. The mixed pathways are then ignited downstream of the multiple premixer fuel nozzle 250.
  • Fig. 5 shows the use of the multiple premixer fuel nozzles 250 within a combustion chamber 350.
  • a single fuel nozzle 100 is used as a center nozzle 360 while a number of the multiple premixer fuel nozzles 250 are used as a number of outer fuel nozzles 370.
  • the combustor chamber 350 has a simplified airflow path 380 to the center nozzle 360 in particular.
  • the airflow path 380 may have fewer restrictions as compared to the design of Fig. 3. Further, less restricted air access also is available to the air inlet sections 340 of each premixer 300 of the outer fuel nozzles 370.
  • the use of the multiple premixer fuel nozzles 250 thus not only provides an even airflow distribution among the nozzles 100, 250 so as to increase the overall efficiency of the gas turbine engine 10, but use of the multiple premixer fuel nozzles 250 also should provide a cost reduction relative to the single center body designs of the fuel nozzles 100. Moreover, the overall design of the combustion chamber 350 also may be simplified.
  • Fig. 6 shows a cross-sectional view of an alternative embodiment of a multiple premixer fuel nozzle 400.
  • the multiple premixer fuel nozzle 400 may include a number of fuel tubes 410 that extend from a flange 420 to a number of premixers 430.
  • the space between the flange 420 and the premixers 430 may be encased in an outer shell 440.
  • the outer shell 440 provides structure in the absence of the center body tube 270.
  • the fuel tubes 410 thus may be made out of flexible tubing as opposed to a structural member.
  • Each fuel tube 410 may be in communication with one of the premixers 430.
  • the flange 420 may include a number of apertures therein including a number of fuel apertures 450 and air apertures 460.
  • the fuel apertures 450 may be in communication with the fuel tubes 410 while the air apertures 460 may direct a flow of air towards each of the premixers 430.
  • Other configurations may be used herein.
  • the use of the multiple fuel tubes 410 thus allows a variable flow of fuel to each of the premixers 430. Depending upon the nature of the load, steady state conditions, and transient conditions, varying the flow of fuel may be desired to each of the premixers 430.

Landscapes

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

Abstract

L'invention concerne un injecteur de carburant (250) destiné à être utilisé dans une turbine à gaz. L'injecteur de carburant peut comprendre un flasque de montage (260), plusieurs prémélangeurs (300) fixés les uns aux autres, et plusieurs passages de gaz (290) s'étendant depuis le flasque de montage jusqu'aux prémélangeurs.
EP09760348A 2009-05-07 2009-05-07 Injecteurs de carburant à plusieurs prémélangeurs Withdrawn EP2430362A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2009/000221 WO2010128882A1 (fr) 2009-05-07 2009-05-07 Injecteurs de carburant à plusieurs prémélangeurs

Publications (1)

Publication Number Publication Date
EP2430362A1 true EP2430362A1 (fr) 2012-03-21

Family

ID=41534849

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09760348A Withdrawn EP2430362A1 (fr) 2009-05-07 2009-05-07 Injecteurs de carburant à plusieurs prémélangeurs

Country Status (4)

Country Link
US (1) US20120031097A1 (fr)
EP (1) EP2430362A1 (fr)
JP (1) JP5476462B2 (fr)
WO (1) WO2010128882A1 (fr)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8522555B2 (en) 2009-05-20 2013-09-03 General Electric Company Multi-premixer fuel nozzle support system
WO2013150340A1 (fr) 2012-04-05 2013-10-10 Nokia Corporation Filtrage de signal audio adaptatif
US9360220B2 (en) 2012-11-06 2016-06-07 General Electric Company Micro-mixer nozzle
US9291103B2 (en) * 2012-12-05 2016-03-22 General Electric Company Fuel nozzle for a combustor of a gas turbine engine
US10408454B2 (en) 2013-06-18 2019-09-10 Woodward, Inc. Gas turbine engine flow regulating
US9482433B2 (en) * 2013-11-11 2016-11-01 Woodward, Inc. Multi-swirler fuel/air mixer with centralized fuel injection
US9587833B2 (en) 2014-01-29 2017-03-07 Woodward, Inc. Combustor with staged, axially offset combustion
CN105318320B (zh) * 2015-10-30 2018-06-08 神雾科技集团股份有限公司 一种兰炭粉与贫煤气混合燃烧装置、系统及方法
US10520194B2 (en) * 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

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EP2216600A2 (fr) * 2009-02-04 2010-08-11 Gas Turbine Efficiency Sweden AB Buse de brûleur

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DE2950535A1 (de) * 1979-11-23 1981-06-11 BBC AG Brown, Boveri & Cie., Baden, Aargau Brennkammer einer gasturbine mit vormisch/vorverdampf-elementen
DE3361535D1 (en) * 1982-05-28 1986-01-30 Bbc Brown Boveri & Cie Gas turbine combustion chamber and method of operating it
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See also references of WO2010128882A1 *

Also Published As

Publication number Publication date
JP2012526261A (ja) 2012-10-25
JP5476462B2 (ja) 2014-04-23
WO2010128882A1 (fr) 2010-11-11
US20120031097A1 (en) 2012-02-09

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