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US20130263605A1 - Diffusion Combustor Fuel Nozzle - Google Patents

Diffusion Combustor Fuel Nozzle Download PDF

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Publication number
US20130263605A1
US20130263605A1 US13/438,851 US201213438851A US2013263605A1 US 20130263605 A1 US20130263605 A1 US 20130263605A1 US 201213438851 A US201213438851 A US 201213438851A US 2013263605 A1 US2013263605 A1 US 2013263605A1
Authority
US
United States
Prior art keywords
fuel
flow
fuel nozzle
swirler
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.)
Abandoned
Application number
US13/438,851
Other languages
English (en)
Inventor
Abinash Baruah
Gilbert Otto Kraemer
Predrag Popovic
Arvind Venugopal Menon
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
Priority to US13/438,851 priority Critical patent/US20130263605A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: POPOVIC, PREDRAG, BARUAH, ABINASH, KRAEMER, GILBERT OTTO, Menon, Arvind Venugopal
Priority to JP2013067726A priority patent/JP2013217635A/ja
Priority to EP13161763.1A priority patent/EP2647910A2/en
Priority to RU2013114768/06A priority patent/RU2013114768A/ru
Priority to CN2013101195727A priority patent/CN103363524A/zh
Publication of US20130263605A1 publication Critical patent/US20130263605A1/en
Abandoned 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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

Definitions

  • the present application and the resultant patent relate generally to gas turbine engines and more particularly relate to a diffusion combustor fuel nozzle using a flow of curtain air to reduce emissions such as nitrogen oxides and the like while maintaining efficient performance.
  • Operational efficiency in a gas turbine engine generally increases as the temperature of the combustion stream increases. Higher combustion stream temperatures, however, may result in the production of high levels of nitrogen oxides (NO x ) and other types of undesirable emissions. Such emissions may be subject to both federal and state regulations in the United States and also may be subject to similar regulations abroad. A balancing act thus exist between operating the gas turbine engine within an efficient temperature range while also ensuring that the output of nitrogen oxides and other types of regulated emissions remain well below mandated levels. Many other types of operational parameters also may be varied in providing such an optimized balance.
  • NO x nitrogen oxides
  • Many other types of operational parameters also may be varied in providing such an optimized balance.
  • a diffusion-type combustor i.e., non-premixed
  • fuel is injected into the air swirler.
  • the air also flows through the swirler so as to mix with the fuel for downstream combustion.
  • the fuel and the resultant hot combustion gases may become entrained in a recirculation zone downstream of the swirler.
  • the liner surrounding the fuel nozzles and the combustion chamber may experience relatively high-head end temperatures.
  • the relatively high head-end temperatures may be increased even further when the combustor burns certain types of liquid fuels. Such high temperatures may have an impact on the integrity and the lifetime of the liner and other components.
  • Such a fuel nozzle for a diffusion combustor may efficiently combust the fuel and the air streams therein with limited emissions while also limiting liner temperatures for increased component lifetime.
  • the present application and the resultant patent thus provide a fuel nozzle for use with one or more flows of fuel and a flow of air in a combustor.
  • the fuel nozzle may include one or more gas fuel passages for the one or more of flows of fuel, a swirler with one or more air chambers therein surrounding the gas fuel passages, and a collar with one or more curtain slots surrounding the swirler. The flow of air is divided between a swirler flow through the air chambers and a curtain flow through the curtain slots.
  • the present application and the resultant patent further provide a method of operating a fuel nozzle in a combustor.
  • the method may include the steps of providing one or more flows of fuel through the fuel nozzle, providing a flow of air about the fuel nozzle, and dividing the flow of air into a swirler flow through a swirler and a curtain flow through a collar such that the curtain flow surrounds a mixed fuel-air flow of the swirler flow and the one or more flows of fuel.
  • the present application and the resultant patent further provide a fuel nozzle for use with one or more flows of fuel and a flow of air in a diffusion combustor.
  • the fuel nozzle may include one or more gas fuel passages for the flows of fuel, a swirler surrounding the gas fuel passages, and a collar surrounding the swirler.
  • the swirler may include a number of swirl vanes that define a number of air chambers therein.
  • the collar may include a number of curtain slots. The flow of air may be divided between a swirler flow through the air chambers and a curtain flow through the curtain slots.
  • FIG. 1 is a schematic diagram of a gas turbine engine showing a compressor, a combustor, and a turbine.
  • FIG. 2 is a side view of an example of the combustor such as that shown in FIG. 1 .
  • FIG. 3 is a side cross-sectional view of a fuel nozzle that may be used in the combustor of FIG. 2 .
  • FIG. 4 is a front plan view of the fuel nozzle of FIG. 3 .
  • FIG. 5 is a partial perspective view of a fuel nozzle as may be described herein.
  • FIG. 6 is a perspective view of a nozzle collar for use with the fuel nozzle of FIG. 5 .
  • FIG. 1 shows a schematic view of gas turbine engine 10 as may be used herein.
  • the gas turbine engine 10 may include a compressor 15 .
  • the compressor 15 compresses an incoming flow of air 20 .
  • the compressor 15 delivers the compressed flow of air 20 to a combustor 25 .
  • the combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35 .
  • the gas turbine engine 10 may include any number of combustors 25 .
  • the flow of combustion gases 35 is in turn delivered to a turbine 40 .
  • the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
  • the mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
  • Other configurations and other components may be used herein.
  • the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
  • the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, N.Y., including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like.
  • the gas turbine engine 10 may have different configurations and may use other types of components.
  • Other types of gas turbine engines also may be used herein.
  • Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
  • FIG. 2 shows an example of the combustor 25 that may be used with the gas turbine engine 10 and the like.
  • the combustor 25 may include a number of fuel nozzles 55 therein. As described above, each of the fuel nozzles 55 may direct the flow of air 20 , the flow of fuel 30 , and optional flows of other fluids for combustion therein. Any number of the fuel nozzles 55 may be used in any configuration.
  • the fuel nozzles 55 may be attached to an end cover 60 near a head-end 65 of the combustor 25 .
  • the flows of the air 20 and the fuel 30 may be directed through the end cover 60 and the head-end 65 into each of the fuel nozzles 55 so as to distribute a fuel-air mixture downstream thereof.
  • the combustor 25 also may include a combustion chamber 70 therein.
  • the combustion chamber 70 may be defined by a combustion casing 75 , a combustion liner 80 , a flow sleeve 85 , and the like.
  • the liner 80 and the flow sleeve 85 may be coaxially positioned with respect to one another so as to define an air pathway 90 for the flow of air 20 therethrough.
  • the combustion chamber 70 may lead to a downstream transition piece 95 .
  • the flows of the air 20 and the fuel 30 may mix downstream of the fuel nozzles 55 for combustion within the combustion chamber 70 .
  • the flow of combustion gases 35 then may be directed via the transition piece 95 towards the turbine 40 so as to produce useful work therein.
  • Other components and other configuration also may be used herein.
  • FIGS. 3 and 4 show an example of the fuel nozzle 55 that may be used with the combustor 25 and the like.
  • the fuel nozzle 55 may be a diffusion fuel nozzle 100 . More specifically, the fuel nozzle 55 may be a dual fuel nozzle 105 .
  • the flow of fuel 30 may include one or more flows of a gas fuel 110 such as natural gas and one or more flows of a liquid fuel 115 such as a syngas and the like. Other types of fuel flows and other types of combinations of fuel flows may be used herein.
  • the fuel nozzle 55 may include an outer tube 120 .
  • the outer tube 120 may lead to a downstream face 125 with a fuel nozzle tip 130 .
  • the outer tube 120 may include a number of fuel, air, and water passages therein.
  • a number of gas fuel passages 135 may extend therethrough and may be axially positioned about the downstream face 125 .
  • the gas fuel passages 135 may be in communication with the flow of gas fuel 110 .
  • a number of tip outlets 140 also may extend therethrough and may be positioned about the fuel nozzle tip 130 .
  • the tip outlets 140 may include a liquid fuel outlet 145 in communication with the flow of liquid fuel 115 .
  • the tip outlets 140 also may include an atomizing air outlet 150 in communication with a flow of atomizing air as well as a water outlet 155 in communication with a flow of water.
  • Other components and other configurations may be used herein.
  • a swirler 160 may be positioned about the downstream face 125 of the fuel nozzle 55 .
  • the swirler 160 may include a number of swirl vanes 165 .
  • the swirl vanes 165 may define a number of air chambers 170 .
  • the air chambers 170 may be in communication with the flow of air 20 from the end cover 60 .
  • a number of swirler passages 175 may extend from the gas fuel passages 135 to the air chambers 170 for at least a portion of the flow of gas fuel 110 .
  • the flow of air 20 and the flow of gas fuel 110 thus may begin to mix about the swirler 160 for combustion within the downstream combustion chamber 70 .
  • all of the flow of air 20 thus passes through the air chambers 170 of the swirler 160 as a swirler flow 180 .
  • a collar 185 may surround the swirler 160 .
  • a cone (not shown) may extend from the fuel nozzle 55 to the liner 80 .
  • Other types of fuel nozzles 55 and other types of combustors 25 may be used herein with differing types of fuel.
  • other components and other configurations may be used herein.
  • FIG. 5 and FIG. 6 show a fuel nozzle 200 as may be described herein.
  • the fuel nozzle 200 may be a diffusion nozzle 210 with little to no upstream fuel-air premixing.
  • the fuel nozzle 200 also may be a dual fuel nozzle 220 for use with both the flow of gas fuel 110 and the flow of the liquid fuel 115 .
  • Other types of flows may be used herein.
  • the fuel nozzle 200 thus includes one or more gas fuel passages 230 extending therethrough.
  • the gas fuel passages 230 may extend towards a downstream face 240 .
  • the fuel nozzle 200 also may include a number of tip outlets 250 .
  • the tip outlets 250 may be positioned about a fuel nozzle tip 260 about the downstream face 240 .
  • the tip outlets 250 may include one or more liquid fuel outlets 270 as well as outlets for atomizing air, water, and the like.
  • Other components and other configurations also may be used herein.
  • the fuel nozzle 200 also may include a swirler 280 positioned about the downstream face 240 thereof.
  • the swirler 280 surrounds fuel nozzle tip 260 .
  • the swirler 280 may include a number of swirl vanes 290 that define a number of air chambers 300 extending therethrough.
  • the swirl vanes 290 and the air chambers 300 may have any size, shape, or configuration. Any number of the swirl vanes 290 and the air chambers 300 may be used herein.
  • a number of swirl vane gas fuel passages 310 may extend from one or more of the gas fuel passages 230 to the air chambers 300 for at least a portion of the flow of gas fuel 110 therethrough.
  • An air inlet 320 may be defined on the upstream end of the swirler 280 in communication with the flow of air 20 from the end cover 60 .
  • the air inlet 320 may have any size, shape, or configuration. Other components and other configurations also may be used herein.
  • the fuel nozzle 200 also may include a collar 330 surrounding the swirler 280 .
  • a cone 340 may extend from the collar 330 towards the liner 80 .
  • the collar 330 may include a number of curtain slots 350 extending therethrough.
  • the curtain slots 350 may include an angled configuration 360 .
  • the curtain slots 350 may have any size, shape, or configuration. Any number of the curtain slots 350 may be used herein.
  • the curtain slots 350 may extend from about the air inlet 320 to the downstream face 240 .
  • the flow of air 20 thus may be divided into a swirler flow 370 passing through the air chambers 300 of the swirler 280 and a curtain flow 380 extending through the curtain slots 350 of the collar 330 .
  • the respective proportions of the swirler flows 370 and the curtain flows 380 may vary. Other components and other configurations may be used herein.
  • the flow of gas fuel 110 extends through the gas fuel passages 230 , through the swirler vane gas fuel passages 310 , and into the air chambers 300 of the swirler 280 .
  • the flow of liquid fuel 115 , the atomizing airflow, and the water flow pass through the tip outlets 250 .
  • the flow of air 20 flows through the air inlet 320 and then may be split into the swirler flow 370 passing through the air chambers 300 and the curtain flow 380 passing through the curtain slots 350 of the collar 300 .
  • the flow of gas fuel 110 and the swirler flow 370 begin to mix within the air chambers 300 of the swirler 280 to create a mixed fuel-air flow 390 extending into the combustion chamber 70 .
  • the curtain flow 380 may be injected at an angle given the angled configuration 360 of the curtain slots 350 . The curtain flow 380 thus serves to blanket this mixed fuel-air flow 390 .
  • Injecting the curtain flow 380 prevents the mixed fuel-air flow 390 and/or the flow of combustion gases 35 from being entrained in a recirculation zone about the fuel nozzle 200 .
  • the blanketing effect of the curtain flow 380 thus may provide a reduction in NO x emissions and the like.
  • the flammable value of the fuel-air flow 390 may be reduced so as to improve emissions and also extend the useful lifetime of the liner 80 and other components in the hot gas path.
  • the water to fuel ratio also may be reduced herein.
  • the fuel nozzle 200 described herein thus provides low natural gas emissions with wide liquid fuel flexibility. As opposed to the current approach of increasing fuel-air premixing, the fuel nozzle 200 described herein actually lowers premixing so as to improve overall NO x emissions. This non-intuitive approach of lowering fuel-air premixing is distinct from such current fuel nozzle designs and operational theories. The use of the curtain flow 380 herein thus improves emissions and overall component lifetime.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
US13/438,851 2012-04-04 2012-04-04 Diffusion Combustor Fuel Nozzle Abandoned US20130263605A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US13/438,851 US20130263605A1 (en) 2012-04-04 2012-04-04 Diffusion Combustor Fuel Nozzle
JP2013067726A JP2013217635A (ja) 2012-04-04 2013-03-28 拡散燃焼器燃料ノズル
EP13161763.1A EP2647910A2 (en) 2012-04-04 2013-03-28 Diffusion combustor fuel nozzle
RU2013114768/06A RU2013114768A (ru) 2012-04-04 2013-04-03 Топливная форсунка (варианты) и способ работы топливной форсунки в камере сгорания
CN2013101195727A CN103363524A (zh) 2012-04-04 2013-04-08 扩散燃烧器燃料喷嘴

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/438,851 US20130263605A1 (en) 2012-04-04 2012-04-04 Diffusion Combustor Fuel Nozzle

Publications (1)

Publication Number Publication Date
US20130263605A1 true US20130263605A1 (en) 2013-10-10

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ID=48050472

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/438,851 Abandoned US20130263605A1 (en) 2012-04-04 2012-04-04 Diffusion Combustor Fuel Nozzle

Country Status (5)

Country Link
US (1) US20130263605A1 (ru)
EP (1) EP2647910A2 (ru)
JP (1) JP2013217635A (ru)
CN (1) CN103363524A (ru)
RU (1) RU2013114768A (ru)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150253010A1 (en) * 2013-11-18 2015-09-10 United Technologies Corporation Dual fuel nozzle with concentric fuel passages for a gas turbine engine
US20160209038A1 (en) * 2013-08-30 2016-07-21 United Technologies Corporation Dual fuel nozzle with swirling axial gas injection for a gas turbine engine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
UA108721C2 (xx) * 2014-07-14 2015-05-25 Форсунка двопаливна
CN114046539B (zh) * 2021-09-26 2023-04-07 中国航发湖南动力机械研究所 一种回流燃烧室机匣头部结构
US12359813B2 (en) * 2021-12-29 2025-07-15 General Electric Company Engine fuel nozzle and swirler
US11774100B2 (en) * 2022-01-14 2023-10-03 General Electric Company Combustor fuel nozzle assembly
CN116293816B (zh) * 2023-04-18 2025-03-28 西安热工研究院有限公司 双燃料贫预混的多级旋流喷嘴
CN119959450B (zh) * 2025-01-13 2025-12-16 华南理工大学 一种面向零碳与碳中性燃料的燃烧实验装置及其工作方法

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US20040035114A1 (en) * 2002-08-22 2004-02-26 Akinori Hayashi Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor
US7000403B2 (en) * 2004-03-12 2006-02-21 Power Systems Mfg., Llc Primary fuel nozzle having dual fuel capability

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160209038A1 (en) * 2013-08-30 2016-07-21 United Technologies Corporation Dual fuel nozzle with swirling axial gas injection for a gas turbine engine
US10228137B2 (en) * 2013-08-30 2019-03-12 United Technologies Corporation Dual fuel nozzle with swirling axial gas injection for a gas turbine engine
US20150253010A1 (en) * 2013-11-18 2015-09-10 United Technologies Corporation Dual fuel nozzle with concentric fuel passages for a gas turbine engine
US10731861B2 (en) * 2013-11-18 2020-08-04 Raytheon Technologies Corporation Dual fuel nozzle with concentric fuel passages for a gas turbine engine

Also Published As

Publication number Publication date
CN103363524A (zh) 2013-10-23
JP2013217635A (ja) 2013-10-24
RU2013114768A (ru) 2014-10-10
EP2647910A2 (en) 2013-10-09

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AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BARUAH, ABINASH;KRAEMER, GILBERT OTTO;POPOVIC, PREDRAG;AND OTHERS;SIGNING DATES FROM 20120315 TO 20120326;REEL/FRAME:027983/0737

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION