US3777983A - Gas cooled dual fuel air atomized fuel nozzle - Google Patents

Gas cooled dual fuel air atomized fuel nozzle Download PDF

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Publication number
US3777983A
US3777983A US3777983DA US3777983A US 3777983 A US3777983 A US 3777983A US 3777983D A US3777983D A US 3777983DA US 3777983 A US3777983 A US 3777983A
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nozzle
gas
plenum
atomizing air
liquid fuel
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Expired - Lifetime
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W Hibbins
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General Electric Co
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General Electric Co
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D11/00Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10Burners 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D11/00Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10Burners 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
    • F23D11/106Burners 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D17/00Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel

Abstract

A dual fuel, air-atomized, fuel nozzle of the type prevalent in some gas turbine combustion chambers wherein the hot atomizing air conduit is remotely positioned with respect to a central liquid fuel or oil conduit so that the nozzle will operate cooler during liquid fuel operation. A gaseous fuel conduit is interposed between the liquid fuel conduit and the atomizing air conduit to provide additional nozzle cooling during the gaseous fuel operation while preventing thermal breakdown of any liquid fuel residuum which could cause nozzle clogging.

Description

[45] Dec. 11, 1973 Mnited States Patent Hibbins GAS COOLED DUAL FUEL AIR ATOMIZED FUEL NOZZLE BACKGROUND OF THE INVENTION This invention pertains in general to fuel nozzles of the type prevalent in gas turbine combustion chambers and in particular relates to dual fuel nozzles utilizing high-temperature atomizing air.

Liquid fuel which is to be utilized in a gas turbine combustion chamber must be atomized at the nozzle portion before proper combustion may take place. Atomizing the fuel consists in breaking down the fuel into kfine particles to form a spray at the nozzle portion.

There are generally two methods of atomizing fuel, i.e., pressure atomizing and air atomizing'Pressure atomizing comprises the sending of liquid fuel under high pressure through a greatly restricted orifice or nozzle. Air atomizing consists of striking liquid fuel with va high-temperature, high-pressure jet of air as the liquid fuel leaves the nozzle. This causes the liquid fuel to be broken down into particles and form a cone-shaped spray. Air-atomized nozzles have ecological advantages in that they reduce the amount of smoke present in the combustion process.

A dual fuel nozzle is one which may run on either gaseous fuel or liquid fuel. The criteria which determines which fuel is used may be based on economic considerations or supply considerations. In a dual fuel, air-atomized nozzle, high-temperature atomizing air is used in conjunction with the flow of liquid fuel. A problem arises when a transfer is made from liquid fuel to gaseous fuel in that a residuum of liquid fuel remains in the liquid fuel or oil passages of the nozzle and is subject to long periods of heat soaking which breaks down the oil into gums, carbon and varnish. One source of heat is the high-temperature atomizing air which usually runs adjacent and parallel to the liquid fuel passageway. The deposits of gums, carbon and varnish clog the small orifices in the nozzle and upon retransferring from gaseous to liquid fuels, the liquid fuel pressure becomes excessive and the flow restricted.

One method of attempting to reduce residuum bluidup, is by passing a reduced flow of atomizing air through the liquid fuel nozzle while running on gas This method has not been 4successful because the atomizing air passes over any nozzle clogs, not through them, and hence does not purge the oil from the system; also, the temperature of the atomizing air is such that it may induce thermal breakdown ofthe residuum of liquid fuel.

In a dual fuel, atomizing air fuel nozzle for a gas turbine combustion chamber, it is one object of this invention to prevent thermal breakdown of residuum liquid fuels and consequent nozzle clogs while the nozzle is running on gaseous fuel.

Another object of this invention is to lower the operating temperatures of the nozzle while the nozzle is running on liquid fuels.

Other objects and advantages will become apparent from the following description of the invention and the novel features will be particularly pointed out hereinafter in the claims.

SUMMARY OF THE INVENTION A dual fuel, air-atomized fuel nozzle including a nozzle support ring having concentric flange portions and a center opening. A liquid fuel or oil pipe is disposed into the center opening and engages a first flange portion. A nozzle cap is disposed about the oil pipe and engages a second flange portion while defining an annular gas plenum. A retaining ring is partially disposed over the nozzle cap and engages a third flange portion while defining an annular atomizing air plenum. The atomizing air plenum is remotely positioned from the liquid fuel pipe to prevent the atomizing air from heating the liquid fuel or liquid fuel residuum. The gas plenum provides additional nozzle cooling when the nozzle is operating on gaseous fuel and further acts to prevent thermal breakdown of residuum liquid fuel.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. l is an elevation view, partially in cross section. of a dual fuel, air-atomized nozzle with a swirler cap having the present invention applied thereto.

FIG. 2 is an elevation', partial cross section of a dual fuel, air-atomized nozzle with a shrouded nozzle cap having the present invention applied thereto.

DETAILED DESCRIPTION OF THE INVENTION `ring 15.

An air swirler nozzle cap 3l of the type disclosed in U. S. Patent Application Ser. No. 7,947, filed Feb. 2, 1970, for Edward P. Hopkins, now matured into U. S. Pat. No. 3,630,024, and assigned to the assignee of the present invention, is placed around the oil pipe casing 25. The swirler cap 3l has external threads which are secured into a second threaded flange portion 35 on the nozzle support ring 15. The swirler cap has a plurality of swirler blades 37 circumferentially arranged at the forward end of the swirler cap and having gas distribution holes 38 positioned between selected blades. A circumferential mounting ring 39 surrounds the swirler blades and positions a combustion chamber casing 40 and liner 4l.

An annular gas plenum 45 is defined by the nozzle support ring 15, the oil pipe casing 25 and the nozzle cap 3l. The gas plenum is fed through a plurality (only one shown) of circumferentially arranged inlet pipes 49 which are connected to an outside supply pipe. Gas is then distributed from the plenum through selected swirler blades by means of a plurality (only one shown) of gas passages 51 which are circumferentially arrayed within the gas nozzle, each terminating in a gas distribution hole 38.

A retaining ring 59 having an exterior threaded portion is secured into a third threaded flange portion 6l on the nozzle support ring 15 and is formed with an inwardly directed flange which abuts the swirler cap formed with a mating outwardly directed flange to form a seal 65.

An annular atomizing air plenum 7l is defined within the retaining ring 59, the nozzle cap 3l and the nozzle support ring 15. The plenum 7l is supplied by means of a plurality (only one shown) of circumferentially arranged inlet pipes 75 which are connected to an outside supply pipe. Atomizing air is delivered to the nozzle face through a plurality of air passages 79 (only one shown) into a distribution ring 80. The distribution ring 80 is an annulus adjacent the nozzle casing which feeds atomizing air to circumferentially arranged slots or openings 8l in the face of the casing 25 to distribute atomizing air to the fuel emanating from the fuel nozzle.

Referring now to FIG. 2, a second embodiment of a dual fuel atomized fuel nozzle lll is shown including a nozzle support ring 115. A centrally mounted oil supply pipe 119 is connected at one end to an oil supply source and terminates at the other end in an oil nozzle 121. The oil pipe is formed within a casing 125 having an exterior threaded portion. The threaded portion is secured within a first threaded flange portion 129 on the nozzle support ring.

A shrouded nozzle cap 131 is positioned about the front end of the oil pipe casing 125 and includes an exterior threaded portion which is secured within a second threaded flange portion 13S of the nozzle support ring. The outer portions of the shrouded nozzle cap contact a combustion chamber casing 140 and liner 141. The nozzle support ring, the oil pipe casing and the shrouded nozzle cap define an annular gas plenum 145. A plurality (only one shown) of circumferentially arranged inlet pipes 149 feed gaseous fuel from a supply pipe to the plenum which is distributed to the shrouded nozzle cap face through gas passages 151 and outlet holes 153 in the face of the nozzle cap. Both the gas passages and the outlet holes are circumferentially arranged about the nozzle cap.

A retaining ring 159 having an exterior threaded portion is secured into a third threaded flange portion 161 on the nozzle support ring 115 and is formed with an inwardly directed flange which abuts the nozzle cap 131 at an outwardly directed mating flange and holds it in place, as well as forming a seal 165.

An annular atomized air plenum 171 is defined within the retaining ring 159, the nozzle cap 131 and the nozzle support ring 115. The plenum 171 is supplied by means of a plurality (only one shown) of circumferentially arranged inlet pipes 175 which are connected to an outside supply pipe. Atomizing air is delivered to the nozzle face through a plurality of air passages 179 (only one shown) into a distribution ring 180. The distribution ring includes an annulus adjacent the nozzle casing 125 face which distributes atomizing air thereto through slots or openings 181 adjacent the fuel nozzle 121 opening.

OPERATION There are two modes of operation inherent in the operation of a dual fuel nozzle. The nozzle may operate on liquid fuels such as oil or it may operate on gaseous fuel. When the nozzle operates on liquid fuel, hot atomizing air is sent through the air passages so that oil flowing through the oil nozzle is atomized. The atomizing air is at a temperature of about 350F.

The nozzle may be switched to operate on gaseous fuel which is usually at a temperature of 70-90F. When the nozzle operates on gaseous fuel, the atomizing air passages carry a reduced amount of air and the oil pipe is shut off.

The problem arises when the nozzle is running on gaseous fuel in that a residuum of liquid fuel remains in the oil pipe and will break down into clogs of gum,

carbon and varnish if the hot atomizing air pipe is adjacent the oil pipe. By transposing the gas and atomizing air conduits as taught by the present invention, residuum oil clogs are prevented because the atomizing air conduit is farther away from and separated from the oil pipe by the gas plenum 45, and because the flow of relatively cool gaseous fuel cools the nozzle when the gaseous operation of the nozzle is in use.

A further benefit of the transportation of the gaseous and air atomizing pipes is that the nozzle itself will run cooler about l50F when operating on liquid fuel.

While there is shown what is considered to be, at present, the preferred embodiment of the invention, it is, of course, understood that various other modifications may be made therein and it is intended to cover in the appended claims all such modifications as fall within the true spirit and scope of the invention.

What is claimed is:

l. A dual fuel, air-atomized fuel nozzle of the type used in a combustion chamber for a gas turbine, said nozzle including:

a nozzle support ring having concentric flange portions and a center opening;

a liquid fuel conduit partially disposed within said center opening and engaging a first concentric flange;

an annular nozzle cap partially disposed about said liquid fuel conduit and engaging a second concentric flange to define an annular gas plenum with said support ring and said liquid fuel conduit;

at least one gas supply pipe interconnecting said gas plenum with a gas supply through said nozzle support ring; and, gas passageways through said nozzle cap interconnecting the gas plenum with said combusion chamber; and,

an annular retaining ring abutting said nozzle cap and engaging a third concentric flange to define an annular atomizing air plenum with said support ring and said nozzle cap, whereby said liquid fuel conduit is insulated from said atomizing air plenum by said gas plenum, gas supply pipe and said gas passageways.

2. The nozzle as recited in claim 1 wherein the nozzle cap is formed with a plurality of circumferentially arrayed blades disposed within the combustion chamber and having holes between selected blades; the gas passages interconnecting thegas plenum with the holes between circumferentially arrayed blades.

3. The nozzle as recited in claim 1 wherein the nozzle cap is formed with a plurality of concentrically arrayed outlet holes communicating with the combustion chamber and through the face of the nozzle cap; the gas passageways interconnecting the gas plenum with said circumferentially arrayed holes.

4. The nozzle as recited in claim l further including a plurality of atomizing air inlet pipes passing through the nozzle support ring and interconnecting the atomizing air plenum with an atomizing air supply.

5. The nozzle as recited in claim 4 further including a plurality of atomizing air passageways interconnecting the atomizing air plenum with a distribution ring in communication with an oil nozzle within the liquid fuel conduit.

6. The nozzle as recited in claim l wherein the first, second and third concentric flanges are threaded for easy assembly and disassembly.

7. The nozzle as recited in claim 1 wherein said nozzle cap and retaining ring are formed with inwardly and outwardly directed flanges forming a seal.

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Claims (7)

1. A dual fuel, air-atomized fuel nozzle of the type used in a combustion chamber for a gas turbine, said nozzle including: a nozzle support ring having concentric flange portions and a center opening; a liquid fuel conduit partially disposed within said center opening and engaging a first concentric flange; an annular nozzle cap partially disposed about said liquid fuel conduit and engaging a second concentric flange to define an annular gas plenum with said support ring and said liquid fuel conduit; at least one gas supply pipe interconnecting said gas plenum with a gas supply through said nozzle support ring; and, gas passageways through said nozzle cap interconnecting the gas plenum with said combusion chamber; and, an annular retaining ring abutting said nozzle cap and engaging a third concentric flange to define an annular atomizing air plenum with said support ring and said nozzle cap, whereby said liquid fuel conduit is insulated from said atomizing air plenum by said gas plenum, gas supply pipe and said gas passageways.
2. The nozzle as recited in claim 1 wherein the nozzle cap is formed with a plurality of circumferentially arrayed blades disposed within the combustion chamber and having holes between selected blades; the gas passages interconnecting the gas plenum with the holes between circumferentially arrayed blades.
3. The nozzle as recited in claim 1 wherein the nozzle cap is formed with a plurality of concentrically arrayed outlet holes communicating with the combustion chamber and through the face of the nozzle cap; the gas passageways interconnecting the gas plenum with said circumferentially arrayed holes.
4. The nozzle as recited in claim 1 further including a plurality of atomizing air inlet pipes passing through the nozzle support ring and interconnecting the atomizing air plenum with an atomizing air supply.
5. The nozzle as recited in claim 4 further including a plurality of atomizing air passageways interconnecting the atomizing air plenum with a distribution ring in communication with an oil nozzle within the liquid fuel conduit.
6. The nozzle as recited in claim 1 wherein the first, second and third concentric flanges are threaded for easy assembly and disassembly.
7. The nozzle as recited in claim 1 wherein said nozzle cap and retaining ring are formed with inwardly and outwardly directed flanges forming a seal.
US3777983A 1971-12-16 1971-12-16 Gas cooled dual fuel air atomized fuel nozzle Expired - Lifetime US3777983A (en)

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DE (1) DE2261038C2 (en)
FR (1) FR2163494B1 (en)
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US3886736A (en) * 1972-11-09 1975-06-03 Westinghouse Electric Corp Combustion apparatus for gas turbine
US3980417A (en) * 1973-11-29 1976-09-14 Afga-Gevaert N.V. Apparatus for incinerating non-halogenated waste liquids
US4036434A (en) * 1974-07-15 1977-07-19 Aerojet-General Corporation Fluid delivery nozzle with fluid purged face
US4253301A (en) * 1978-10-13 1981-03-03 General Electric Company Fuel injection staged sectoral combustor for burning low-BTU fuel gas
JPS5625607A (en) * 1979-08-01 1981-03-12 Rolls Royce Duplex fufl injection device for gas turbine engine
US4288980A (en) * 1979-06-20 1981-09-15 Brown Boveri Turbomachinery, Inc. Combustor for use with gas turbines
US4327547A (en) * 1978-11-23 1982-05-04 Rolls-Royce Limited Fuel injectors
US4337618A (en) * 1979-06-06 1982-07-06 Rolls-Royce Limited Gas turbine engine fuel burners
US4412808A (en) * 1980-06-19 1983-11-01 Trw Inc. Dual fueled burner gun
US4463568A (en) * 1981-07-28 1984-08-07 Rolls-Royce Limited Fuel injector for gas turbine engines
US4735044A (en) * 1980-11-25 1988-04-05 General Electric Company Dual fuel path stem for a gas turbine engine
US4850194A (en) * 1986-12-11 1989-07-25 Bbc Brown Boveri Ag Burner system
US4854127A (en) * 1988-01-14 1989-08-08 General Electric Company Bimodal swirler injector for a gas turbine combustor
US4967561A (en) * 1982-05-28 1990-11-06 Asea Brown Boveri Ag Combustion chamber of a gas turbine and method of operating it
US5203796A (en) * 1990-08-28 1993-04-20 General Electric Company Two stage v-gutter fuel injection mixer
US5222357A (en) * 1992-01-21 1993-06-29 Westinghouse Electric Corp. Gas turbine dual fuel nozzle
US5351489A (en) * 1991-12-24 1994-10-04 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
US5361578A (en) * 1992-08-21 1994-11-08 Westinghouse Electric Corporation Gas turbine dual fuel nozzle assembly with steam injection capability
US6047926A (en) * 1996-06-28 2000-04-11 Alliedsignal Inc. Hybrid deicing system and method of operation
US6360992B1 (en) 1996-06-28 2002-03-26 Honeywell International Inc. Hybrid deicing system and method of operation
US6402059B1 (en) * 1999-02-15 2002-06-11 Alstom (Switzerland) Ltd Fuel lance for spraying liquid and/or gaseous fuels into a combustion chamber, and method of operating such a fuel lance
US6539724B2 (en) * 2001-03-30 2003-04-01 Delavan Inc Airblast fuel atomization system
US6547163B1 (en) * 1999-10-01 2003-04-15 Parker-Hannifin Corporation Hybrid atomizing fuel nozzle
US20030089111A1 (en) * 2001-11-09 2003-05-15 Enel Produzione S.P.A. Low NOx emission diffusion flame combustor for gas turbines
US20050028532A1 (en) * 2001-12-20 2005-02-10 Stefano Bernero Method for injecting a fuel-air mixture into a combustion chamber
US20050028525A1 (en) * 2003-08-08 2005-02-10 Toon Ian J. Fuel injection
US20050217270A1 (en) * 2004-04-02 2005-10-06 Pratt & Whitney Canada Corp. Fuel injector head
US20070044477A1 (en) * 2005-09-01 2007-03-01 General Electric Company Fuel nozzle for gas turbine engines
US20080078183A1 (en) * 2006-10-03 2008-04-03 General Electric Company Liquid fuel enhancement for natural gas swirl stabilized nozzle and method
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US20090230215A1 (en) * 2008-03-11 2009-09-17 Microjet Gmbh Apparatus for generating and spraying an aerosol
US20090291401A1 (en) * 2006-08-11 2009-11-26 Mitsubishi Heavy Industries, Ltd. Burner
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US20110083442A1 (en) * 2009-10-08 2011-04-14 General Electric Company Apparatus and method for cooling nozzles
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US20130029032A1 (en) * 2007-08-30 2013-01-31 Optomec, Inc. Mechanically Integrated and Closely Coupled Print Head and Mist Source
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CN103486592A (en) * 2013-10-23 2014-01-01 中国船舶重工集团公司第七�三研究所 Gas-liquid dual-fuel integrated nozzle
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US8919095B2 (en) * 2003-11-15 2014-12-30 Astrium Gmbh Injection element
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Cited By (68)

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Publication number Priority date Publication date Assignee Title
US3886736A (en) * 1972-11-09 1975-06-03 Westinghouse Electric Corp Combustion apparatus for gas turbine
US3980417A (en) * 1973-11-29 1976-09-14 Afga-Gevaert N.V. Apparatus for incinerating non-halogenated waste liquids
US4036434A (en) * 1974-07-15 1977-07-19 Aerojet-General Corporation Fluid delivery nozzle with fluid purged face
US4253301A (en) * 1978-10-13 1981-03-03 General Electric Company Fuel injection staged sectoral combustor for burning low-BTU fuel gas
US4327547A (en) * 1978-11-23 1982-05-04 Rolls-Royce Limited Fuel injectors
US4337618A (en) * 1979-06-06 1982-07-06 Rolls-Royce Limited Gas turbine engine fuel burners
US4288980A (en) * 1979-06-20 1981-09-15 Brown Boveri Turbomachinery, Inc. Combustor for use with gas turbines
JPS5625607A (en) * 1979-08-01 1981-03-12 Rolls Royce Duplex fufl injection device for gas turbine engine
JPS5828491B2 (en) * 1979-08-01 1983-06-16 Rolls Royce 1971 Ltd
US4412808A (en) * 1980-06-19 1983-11-01 Trw Inc. Dual fueled burner gun
US4735044A (en) * 1980-11-25 1988-04-05 General Electric Company Dual fuel path stem for a gas turbine engine
US4463568A (en) * 1981-07-28 1984-08-07 Rolls-Royce Limited Fuel injector for gas turbine engines
US4967561A (en) * 1982-05-28 1990-11-06 Asea Brown Boveri Ag Combustion chamber of a gas turbine and method of operating it
US4850194A (en) * 1986-12-11 1989-07-25 Bbc Brown Boveri Ag Burner system
US4854127A (en) * 1988-01-14 1989-08-08 General Electric Company Bimodal swirler injector for a gas turbine combustor
US5203796A (en) * 1990-08-28 1993-04-20 General Electric Company Two stage v-gutter fuel injection mixer
US5351489A (en) * 1991-12-24 1994-10-04 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
US5222357A (en) * 1992-01-21 1993-06-29 Westinghouse Electric Corp. Gas turbine dual fuel nozzle
US5361578A (en) * 1992-08-21 1994-11-08 Westinghouse Electric Corporation Gas turbine dual fuel nozzle assembly with steam injection capability
US7431240B1 (en) 1996-06-28 2008-10-07 Honeywell International Inc. Hybrid deicing system and method of operation
US6047926A (en) * 1996-06-28 2000-04-11 Alliedsignal Inc. Hybrid deicing system and method of operation
US6293498B1 (en) 1996-06-28 2001-09-25 Honeywell International Inc. Hybrid deicing system and method of operation
US6360992B1 (en) 1996-06-28 2002-03-26 Honeywell International Inc. Hybrid deicing system and method of operation
US6402059B1 (en) * 1999-02-15 2002-06-11 Alstom (Switzerland) Ltd Fuel lance for spraying liquid and/or gaseous fuels into a combustion chamber, and method of operating such a fuel lance
US6547163B1 (en) * 1999-10-01 2003-04-15 Parker-Hannifin Corporation Hybrid atomizing fuel nozzle
US6539724B2 (en) * 2001-03-30 2003-04-01 Delavan Inc Airblast fuel atomization system
US20030089111A1 (en) * 2001-11-09 2003-05-15 Enel Produzione S.P.A. Low NOx emission diffusion flame combustor for gas turbines
US6945051B2 (en) * 2001-11-09 2005-09-20 Enel Produzione S.P.A. Low NOx emission diffusion flame combustor for gas turbines
US20080163626A1 (en) * 2001-12-20 2008-07-10 Alstom Technology Ltd Apparatus for injecting a fuel-air mixture into a combustion chamber
US7406827B2 (en) 2001-12-20 2008-08-05 Alstom Technology Ltd Apparatus for injecting a fuel-air mixture into a combustion chamber
US7082768B2 (en) * 2001-12-20 2006-08-01 Alstom Technology Ltd Method for injecting a fuel-air mixture into a combustion chamber
US20050028532A1 (en) * 2001-12-20 2005-02-10 Stefano Bernero Method for injecting a fuel-air mixture into a combustion chamber
US20090108105A1 (en) * 2003-08-08 2009-04-30 Toon Ian J Fuel injection
US7117679B2 (en) * 2003-08-08 2006-10-10 Rolls-Royce Plc Fuel injection
US20050028525A1 (en) * 2003-08-08 2005-02-10 Toon Ian J. Fuel injection
US7533532B1 (en) * 2003-08-08 2009-05-19 Rolls-Royce Plc Fuel injection
US8919095B2 (en) * 2003-11-15 2014-12-30 Astrium Gmbh Injection element
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Also Published As

Publication number Publication date Type
FR2163494B1 (en) 1980-04-18 grant
NL7213675A (en) 1973-06-19 application
NL172785C (en) 1983-10-17 grant
FR2163494A1 (en) 1973-07-27 application
DE2261038C2 (en) 1982-07-08 grant
JPS4865316A (en) 1973-09-08 application
GB1371116A (en) 1974-10-23 application
DE2261038A1 (en) 1973-06-20 application
NL172785B (en) 1983-05-16 application

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