EP0939275A2 - Brennstoffdüse und Führung für die Düse einer Gasturbine - Google Patents

Brennstoffdüse und Führung für die Düse einer Gasturbine Download PDF

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Publication number
EP0939275A2
EP0939275A2 EP98310791A EP98310791A EP0939275A2 EP 0939275 A2 EP0939275 A2 EP 0939275A2 EP 98310791 A EP98310791 A EP 98310791A EP 98310791 A EP98310791 A EP 98310791A EP 0939275 A2 EP0939275 A2 EP 0939275A2
Authority
EP
European Patent Office
Prior art keywords
air
swirler
outlet
fuel
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Withdrawn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
EP98310791A
Other languages
English (en)
French (fr)
Other versions
EP0939275A3 (de
Inventor
John J. Rup Jr.
James B. Hoke
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.)
RTX Corp
Original Assignee
United Technologies 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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP0939275A2 publication Critical patent/EP0939275A2/de
Publication of EP0939275A3 publication Critical patent/EP0939275A3/de
Withdrawn legal-status Critical Current

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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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • 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
    • 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
    • F23C7/02—Disposition of air supply not passing through burner
    • 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
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23C2900/03004—Tubular combustion chambers with swirling fuel/air flow
    • 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
    • F23C2900/06043—Burner staging, i.e. radially stratified flame core burners
    • 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
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • This invention relates generally to gas turbine engine combustors and more particularly to a fuel nozzle and nozzle guide for use in such a combustor.
  • NOx oxides of nitrogen
  • Gas turbine engines emit various pollutants including oxides of nitrogen (“NOx”). NOx is primarily formed through the thermal fixation of nitrogen and results from the high temperature combustion of fuel and air in the gas turbine engine.
  • Environmental concerns and more stringent governmental regulation of NOx emissions have prompted designers to investigate various methods for reducing the generation of NOx by gas turbine engines.
  • Illustrative devices for reducing or controlling NOx are disclosed in the following commonly-assigned patents: (1) Snyder et al., US 5256352 issued 26 October 1993 entitled “Air-Liquid Mixer”; (2) Mcvey et al., US 5263325 issued 23 November 1993 entitled “Low NOx Combustion”; and (3) Marshall, US 5406799 issued 18 April 1995 entitled “Combustion Chamber”.
  • Two basic approaches for a low NOx fuel injection system are (1) a locally lean stoichiometry system and (2) a locally rich stoichiometry system. Both approaches require good atomisation, mixing and uniformity in the fuel-air mixture. It is therefore desirable to provide a fuel injection system with improved atomization, mixing and/or uniformity.
  • a fuel injection nozzle/guide assembly having a fuel delivery passage with a discharge outlet for discharging fuel, a first axial inflow swirler with a first outlet positioned to provide swirled air to the discharged fuel, a second radial inflow swirler with a second outlet positioned to provide swirled air to the discharged fuel to produce a downstream-flowing fuel-air mixture, and a third radial inflow swirler with a third inflow swirler with a third outlet positioned to provide swirled air to the downstream-flowing fuel-air mixture.
  • each swirler may be selectively determined to provide co-swirling or counter-swirling dependent upon application.
  • a fourth radial inflow swirler is disposed with a fourth outlet about the third swirler outlet or alternatively a plurality of axially extending air passages with outlet ends are disposed about the third swirler outlet.
  • a fuel nozzle for a gas turbine engine having a base, a head, a fuel delivery passage having a discharge outlet for discharging fuel, an axial inflow swirler in the head having an outlet for directing swirled air to the discharge outlet, and a radial inflow swirler having an outlet for directing swirled air to the discharge outlet.
  • a nozzle guide for mounting a fuel nozzle in a gas turbine engine, comprising a base with an aperture for receiving a nozzle head, and a radial inflow swirler for directing swirled air to a fuel-air mixture discharged from the nozzle.
  • the nozzle/guide assembly of the present invention is generally designated by the numeral 10 and is shown mounted in a combustor 12 which will be described in more detail hereafter.
  • the nozzle/guide assembly 10 generally comprises a nozzle 14 and nozzle guide 16.
  • the nozzle 14 has a head 18 connected to the base 22 by stem 20.
  • the base 22 has a fitting 24 for connection to a fuel source (not shown).
  • a fuel delivery system 26 has a fuel delivery passage 28 terminating in an annular discharge outlet 30 for delivering fuel from the fitting 24 to the discharge outlet 30.
  • the fuel delivery system 26 is the type that delivers a thin film or sheet of fuel at the discharge outlet 30 such as the system described in commonly assigned US Patent No. 4946105 to Pane, Jr. et al. issued August 7, 1990 entitled "Fuel Nozzle For Gas Turbine Engine” (the disclosure of which is incorporated by reference herein) and such system need not be described further for the purposes of the present invention.
  • the nozzle head 18 includes an axial inflow swirler 32 and a radial inflow swirler 34.
  • the swirler 32 comprises an air passage 36 concentric to the centreline 38 of the head 18 with an inlet end 44 to receive axially inflowing air, a vane assembly 40 to impart swirl to the air and an outlet end 42 adjoining the fuel discharge outlet 30.
  • the radial inflow swirler 34 has an annular air passage 46 concentric to centreline 38 with an outlet end 48 adjoining fuel discharge outlet 30 and an inner end 50.
  • the inner end 50 has a plurality of equispaced, circumferentially disposed air inlet ports 52.
  • the ports 52 open radially outwardly for the radial inflow of air into the passage 46.
  • Each port 52 has an adjoining swirl vane 54 disposed at a predetermined swirl angle to impart swirl to the inflowing air.
  • the angle of the vane determines the amount of swirl imparted to the inflowing air and the vanes 54 may by positioned to provide either clockwise or counterclockwise swirl, i.e., co-swirl or counter-swirl relative to the swirl from swirler 32 depending upon application. (Vane angle is usually measured relative to a perpendicular at the midpoint.)
  • the annular passage 46 generally converges radially inwardly as the passage extends longitudinally from the inner end 50 to the outlet end 48.
  • the fuel film produced at the fuel discharge outlet is concentric to and disposed between the air outlet 42 of swirler 32 and the air outlet 48 of swirler 34 to subject the fuel film on one side to high velocity air from swirler 32 and on the other side to high velocity air from swirler 34.
  • the high velocity swirling air on each side of the fuel film creates a shear layer which atomizes the fuel and produces a rapidly mixing, downstream flowing fuel-air mixture.
  • the radial inflow swirler is believed to provide more airflow compared to similarly dimensioned axial swirlers and it contributes to reducing vane wakes and providing a more uniform fuel-air mixture with rapid mixing.
  • the guide 16 of the present invention is used to mount the nozzle 14 in a combustor end wall (Fig. 7) and properly align the nozzle relative to the combustor as more fully described in commonly assigned US Patent 5463864 to Butler et al. issued 7 November 1995 entitled "Fuel Nozzle Guide For A Gas Turbine Engine Combustor".
  • the guide 16 has a generally annular base 56 with an outwardly extending frustoconical hub section 58 forming a central mounting aperture 60 dimensioned for snug slip-fit mounting of the head 18 (Fig. 1).
  • the centreline of the guide (not shown) is concurrent with the centreline 38 of head 18 when it is mounted within the guide 16.
  • the guide 16 includes a radial inflow swirler 62.
  • the swirler 62 has a frustoconical air passage 64 formed in the hub section 58 concentric to centreline 38 (when nozzle head 18 is mounted in the guide 16) with an annular outlet end 66 concentric about and adjacent to outlet 48 of swirler 34 (Fig. 1).
  • the inner end 68 of passage 64 is positioned in the annular base 56 and has a plurality of equispaced, circumferentially disposed air inlet ports 70.
  • the ports 70 open radially outwardly for the radial inflow of air into the passage 64.
  • Each port 70 has an adjoining swirl vane surface 72 disposed at a predetermined swirl angle to impart swirl to the inflowing air.
  • the angle of the vane surface determines the amount of swirl imparted to the inflowing air and the vane surfaces 72 may by positioned to provide either clockwise or counterclockwise swirl, i.e., co-swirl or counter-swirl relative to the swirl from swirlers 32, 34 depending upon application.
  • the frustoconical passage 64 generally converges radially inwardly as the passage extends longitudinally from the inner end 68 to the outlet end 66 such that a progressively converging helical air pathway is followed by the swirled air.
  • the swirled air from outlet 66 is directed into the fuel-air mixture from the nozzle head 18 producing (above idle power) a fuel rich, more uniform fuel-air mixture with rapid mixing as the mixture moves downstream.
  • the guide 16 includes an additional air source to the fuel-air mixture in the form of a plurality of axial inflow air passages 74 in a flange portion 76 of base 56.
  • Each passage 74 has an inlet end 78 and an outlet end 80 (Fig. 6) and is disposed generally parallel to passage 64, i.e., extending outwardly from the base and radially inwardly.
  • the outlets 80 are disposed in a concentric array about the outlet 66 of swirler 62. It is believed that air from the outlets 80 purges the area about the nozzle and contributes to the mixing and flow of the fuel-air mixture.
  • the passages 74 can be disposed to provide some swirl to the discharged air so as provide an outer curtain or pattern which may tend to confine the rich fuel-air mixture central core downstream.
  • Fig. 7 the embodiment of Fig. 1 is shown mounted in the end wall or dome 82 of combustor 12.
  • the vane angle for the swirler 32 is 70 degrees
  • the vane angle for swirler 34 is 47 degrees
  • the vane angle for swirler 62 is 22 degrees.
  • the nozzle/guide assembly 10 is positioned to provide a rapidly mixing, highly uniform downstream flowing fuel-air mixture into the combustion chamber 84 which contributes to a low NOx combustion process.
  • an alternate embodiment guide 86 is shown having a radial inflow swirler 88 instead of the air passages 74.
  • the swirler 88 has an annular or frustoconical air passage 90 formed in the hub section 58 concentric about the air passage 64 of swirler 62 with an annular outlet end 92 concentric about and adjacent to outlet 66 of swirler 62.
  • the inner end 94 of passage 90 is positioned in the annular base 56 and has a plurality of equispaced, circumferentially disposed air inlet ports 96. The ports 96 open radially outwardly for the radial inflow of air into the passage 90.
  • Each port 96 has an adjoining swirl vane surface 98 disposed at a predetermined swirl angle to impart swirl to the inflowing air.
  • the vane angles may be selected as desired and the vane surfaces 72 may by positioned to provide either clockwise or counterclockwise swirl relative to the other swirlers depending upon application.
  • FIG. 9 the swirl orientation for the embodiment of Fig. 8 is shown whereby the swirl direction from swirlers 32, 34 (in the nozzle) is counter to the swirl direction from swirlers 62, 88.
  • the vane angles of swirlers 32, 34 are unchanged while the vane angle of the swirler 88 is 10 degrees and the vane angle of the swirler 62 is 45 degrees.
  • the emanating fuel-air mixture pattern is tighter being confined by the swirled air 100 from the outer swirler 88 as diagrammatically shown (not to scale) in Fig. 8 while the swirled air 102 (counter to the air from swirlers 32, 24) contributes to rapidly mixing the fuel-air mixture to an improved uniform condition for combustion.
  • a new and improved fuel nozzle and nozzle guide have been described which achieves enhanced atomization, mixing and uniform distribution in the fuel-air mixture so as to contribute to the reduction or control of NOx and other pollutant emissions in a gas turbine engine.
  • the nozzle/guide assembly can produce a rapidly mixed rich fuel-air mixture with the rapid mixing process controlled at some distance downstream of the fuel injection mechanism.
  • the described invention is adaptable to varied applications through selective variation of swirler components for control of the mixing process and the fuel-air spray pattern downstream in the combustor.
  • the present invention provides a new and improved fuel injection nozzle and guide assembly which contributes to the reduction or control of NOx emission in a gas turbine engine, an assembly which achieves improved atomization, mixing and uniformity in the fuel-air mixture, an assembly which affords a rapid mixing process controlled at some distance downstream of the fuel injection mechanism, a nozzle and nozzle guide which can produce a rapidly-mixed rich fuel-air mixture, a nozzle and nozzle guide design which is adaptable to varied applications and which facilitates selective variation of components for control of the fuel-air spray pattern downstream in the combustor, such as to achieve a coherent central flow structure downstream from the nozzle, and a nozzle and nozzle guide assemble which is dimensionally compact for a given airflow and durable in use.

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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)
EP98310791A 1997-12-30 1998-12-30 Brennstoffdüse und Führung für die Düse einer Gasturbine Withdrawn EP0939275A3 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US89797A 1997-12-30 1997-12-30
US897 1997-12-30

Publications (2)

Publication Number Publication Date
EP0939275A2 true EP0939275A2 (de) 1999-09-01
EP0939275A3 EP0939275A3 (de) 1999-09-29

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JP (1) JPH11257664A (de)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006102765A1 (en) * 2005-04-01 2006-10-05 Pratt & Whitney Canada Corp. Internal fuel manifold with airblast nozzles
US7559142B2 (en) 2006-09-26 2009-07-14 Pratt & Whitney Canada Corp. Method of manufacturing a heat shield for a fuel manifold
US7565807B2 (en) 2005-01-18 2009-07-28 Pratt & Whitney Canada Corp. Heat shield for a fuel manifold and method
US7703289B2 (en) 2006-09-18 2010-04-27 Pratt & Whitney Canada Corp. Internal fuel manifold having temperature reduction feature
US7716933B2 (en) 2006-10-04 2010-05-18 Pratt & Whitney Canada Corp. Multi-channel fuel manifold
US7765808B2 (en) 2006-08-22 2010-08-03 Pratt & Whitney Canada Corp. Optimized internal manifold heat shield attachment
US7775047B2 (en) 2006-09-22 2010-08-17 Pratt & Whitney Canada Corp. Heat shield with stress relieving feature
US7856825B2 (en) 2007-05-16 2010-12-28 Pratt & Whitney Canada Corp. Redundant mounting system for an internal fuel manifold
US7937926B2 (en) 2005-01-14 2011-05-10 Pratt & Whitney Canada Corp. Integral heater for fuel conveying member
US8033113B2 (en) 2006-08-31 2011-10-11 Pratt & Whitney Canada Corp. Fuel injection system for a gas turbine engine
US8096130B2 (en) 2006-07-20 2012-01-17 Pratt & Whitney Canada Corp. Fuel conveying member for a gas turbine engine
US8146365B2 (en) 2007-06-14 2012-04-03 Pratt & Whitney Canada Corp. Fuel nozzle providing shaped fuel spray
US8353166B2 (en) 2006-08-18 2013-01-15 Pratt & Whitney Canada Corp. Gas turbine combustor and fuel manifold mounting arrangement
EP2639505A1 (de) * 2012-03-13 2013-09-18 Siemens Aktiengesellschaft Gasturbinen-Verbrennungssystem und -verfahren der Flammenstabilisierung in solch einem System
US8572976B2 (en) 2006-10-04 2013-11-05 Pratt & Whitney Canada Corp. Reduced stress internal manifold heat shield attachment
EP2113717A3 (de) * 2008-04-30 2017-05-24 General Electric Company Zufuhrinjektorsysteme und -verfahren
EP3524886A1 (de) * 2018-02-12 2019-08-14 Rolls-Royce plc Luftwirbleranordnung für einen kraftstoffinjektor einer brennkammer
CN110697823A (zh) * 2019-11-03 2020-01-17 中国华电科工集团有限公司 一种脱硫废水干燥装置及方法
US10955138B2 (en) 2017-04-25 2021-03-23 Parker-Hannifin Corporation Airblast fuel nozzle

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WO2006090466A1 (ja) * 2005-02-25 2006-08-31 Ihi Corporation 燃料噴射弁とこれを用いた燃焼器及びその燃料噴射方法
CN100368667C (zh) * 2006-04-13 2008-02-13 中国科学院工程热物理研究所 燃气轮机稀释扩散燃烧喷嘴
CN114811656B (zh) * 2022-05-19 2024-12-03 上海和兰透平动力技术有限公司 燃料喷嘴
CN118423716B (zh) * 2024-07-04 2024-09-17 中国航发湖南动力机械研究所 低温冷浸环境下可靠点火的回流燃烧室

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US5256352A (en) 1992-09-02 1993-10-26 United Technologies Corporation Air-liquid mixer
US5263325A (en) 1991-12-16 1993-11-23 United Technologies Corporation Low NOx combustion
US5406799A (en) 1992-06-12 1995-04-18 United Technologies Corporation Combustion chamber
US5463864A (en) 1993-12-27 1995-11-07 United Technologies Corporation Fuel nozzle guide for a gas turbine engine combustor

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US4946105A (en) 1988-04-12 1990-08-07 United Technologies Corporation Fuel nozzle for gas turbine engine
US5263325A (en) 1991-12-16 1993-11-23 United Technologies Corporation Low NOx combustion
US5406799A (en) 1992-06-12 1995-04-18 United Technologies Corporation Combustion chamber
US5256352A (en) 1992-09-02 1993-10-26 United Technologies Corporation Air-liquid mixer
US5463864A (en) 1993-12-27 1995-11-07 United Technologies Corporation Fuel nozzle guide for a gas turbine engine combustor

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7937926B2 (en) 2005-01-14 2011-05-10 Pratt & Whitney Canada Corp. Integral heater for fuel conveying member
US8276387B2 (en) 2005-01-14 2012-10-02 Pratt & Whitney Canada Corp. Gas turbine engine fuel conveying member
US7565807B2 (en) 2005-01-18 2009-07-28 Pratt & Whitney Canada Corp. Heat shield for a fuel manifold and method
WO2006102765A1 (en) * 2005-04-01 2006-10-05 Pratt & Whitney Canada Corp. Internal fuel manifold with airblast nozzles
US8096130B2 (en) 2006-07-20 2012-01-17 Pratt & Whitney Canada Corp. Fuel conveying member for a gas turbine engine
US8353166B2 (en) 2006-08-18 2013-01-15 Pratt & Whitney Canada Corp. Gas turbine combustor and fuel manifold mounting arrangement
US7765808B2 (en) 2006-08-22 2010-08-03 Pratt & Whitney Canada Corp. Optimized internal manifold heat shield attachment
US8033113B2 (en) 2006-08-31 2011-10-11 Pratt & Whitney Canada Corp. Fuel injection system for a gas turbine engine
US7703289B2 (en) 2006-09-18 2010-04-27 Pratt & Whitney Canada Corp. Internal fuel manifold having temperature reduction feature
US7775047B2 (en) 2006-09-22 2010-08-17 Pratt & Whitney Canada Corp. Heat shield with stress relieving feature
US7926286B2 (en) 2006-09-26 2011-04-19 Pratt & Whitney Canada Corp. Heat shield for a fuel manifold
US7559142B2 (en) 2006-09-26 2009-07-14 Pratt & Whitney Canada Corp. Method of manufacturing a heat shield for a fuel manifold
US7716933B2 (en) 2006-10-04 2010-05-18 Pratt & Whitney Canada Corp. Multi-channel fuel manifold
US8572976B2 (en) 2006-10-04 2013-11-05 Pratt & Whitney Canada Corp. Reduced stress internal manifold heat shield attachment
US7856825B2 (en) 2007-05-16 2010-12-28 Pratt & Whitney Canada Corp. Redundant mounting system for an internal fuel manifold
US8146365B2 (en) 2007-06-14 2012-04-03 Pratt & Whitney Canada Corp. Fuel nozzle providing shaped fuel spray
EP2113717A3 (de) * 2008-04-30 2017-05-24 General Electric Company Zufuhrinjektorsysteme und -verfahren
WO2013135324A1 (en) 2012-03-13 2013-09-19 Siemens Aktiengesellschaft Gas turbine combustion system and method of flame stabilization in such a system
EP2639505A1 (de) * 2012-03-13 2013-09-18 Siemens Aktiengesellschaft Gasturbinen-Verbrennungssystem und -verfahren der Flammenstabilisierung in solch einem System
US10955138B2 (en) 2017-04-25 2021-03-23 Parker-Hannifin Corporation Airblast fuel nozzle
US11391463B2 (en) 2017-04-25 2022-07-19 Parker-Hannifin Corporation Airblast fuel nozzle
US11655979B2 (en) 2017-04-25 2023-05-23 Parker-Hannifin Corporation Airblast fuel nozzle
USD1073858S1 (en) 2017-04-25 2025-05-06 Parker-Hannifin Corporation Airblast fuel nozzle
EP3524886A1 (de) * 2018-02-12 2019-08-14 Rolls-Royce plc Luftwirbleranordnung für einen kraftstoffinjektor einer brennkammer
EP3839349A1 (de) * 2018-02-12 2021-06-23 Rolls-Royce plc Luftverwirbleranordnung für einen kraftstoffinjektor einer brennkammer
US11085643B2 (en) 2018-02-12 2021-08-10 Rolls-Royce Plc Air swirler arrangement for a fuel injector of a combustion chamber
CN110697823A (zh) * 2019-11-03 2020-01-17 中国华电科工集团有限公司 一种脱硫废水干燥装置及方法

Also Published As

Publication number Publication date
EP0939275A3 (de) 1999-09-29
JPH11257664A (ja) 1999-09-21

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