US2850875A - Gas burner - Google Patents

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US2850875A
US2850875A US377204A US37720453A US2850875A US 2850875 A US2850875 A US 2850875A US 377204 A US377204 A US 377204A US 37720453 A US37720453 A US 37720453A US 2850875 A US2850875 A US 2850875A
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air
gas
nozzle
combustion
fuel
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US377204A
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Gahwyler Wolfgang
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BBC Brown Boveri AG Germany
BBC Brown Boveri France SA
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BBC Brown Boveri France SA
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    • D—TEXTILES; PAPER
    • D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
    • D06M—TREATMENT, NOT PROVIDED FOR ELSEWHERE IN CLASS D06, OF FIBRES, THREADS, YARNS, FABRICS, FEATHERS OR FIBROUS GOODS MADE FROM SUCH MATERIALS
    • D06M11/00—Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with inorganic substances or complexes thereof; Such treatment combined with mechanical treatment, e.g. mercerising
    • D06M11/32—Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with inorganic substances or complexes thereof; Such treatment combined with mechanical treatment, e.g. mercerising with oxygen, ozone, ozonides, oxides, hydroxides or percompounds; Salts derived from anions with an amphoteric element-oxygen bond
    • D06M11/36—Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with inorganic substances or complexes thereof; Such treatment combined with mechanical treatment, e.g. mercerising with oxygen, ozone, ozonides, oxides, hydroxides or percompounds; Salts derived from anions with an amphoteric element-oxygen bond with oxides, hydroxides or mixed oxides; with salts derived from anions with an amphoteric element-oxygen bond
    • D06M11/38—Oxides or hydroxides of elements of Groups 1 or 11 of the Periodic Table
    • D—TEXTILES; PAPER
    • D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
    • D06M—TREATMENT, NOT PROVIDED FOR ELSEWHERE IN CLASS D06, OF FIBRES, THREADS, YARNS, FABRICS, FEATHERS OR FIBROUS GOODS MADE FROM SUCH MATERIALS
    • D06M13/00—Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with non-macromolecular organic compounds; Such treatment combined with mechanical treatment
    • D06M13/10—Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with non-macromolecular organic compounds; Such treatment combined with mechanical treatment with compounds containing oxygen
    • D06M13/152—Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with non-macromolecular organic compounds; Such treatment combined with mechanical treatment with compounds containing oxygen having a hydroxy group bound to a carbon atom of a six-membered aromatic ring
    • D—TEXTILES; PAPER
    • D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
    • D06M—TREATMENT, NOT PROVIDED FOR ELSEWHERE IN CLASS D06, OF FIBRES, THREADS, YARNS, FABRICS, FEATHERS OR FIBROUS GOODS MADE FROM SUCH MATERIALS
    • D06M13/00—Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with non-macromolecular organic compounds; Such treatment combined with mechanical treatment
    • D06M13/244—Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with non-macromolecular organic compounds; Such treatment combined with mechanical treatment with compounds containing sulfur or phosphorus
    • D06M13/248—Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with non-macromolecular organic compounds; Such treatment combined with mechanical treatment with compounds containing sulfur or phosphorus with compounds containing sulfur
    • D06M13/256—Sulfonated compounds esters thereof, e.g. sultones
    • 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
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • 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
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • F23D14/24—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion
    • 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
    • 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
    • F23R3/34—Feeding into different combustion zones

Definitions

  • the invention relates to a gas burner adapted for use in the combustion chambers of gas turbine installations where a gaseous fuel such as one consisting principally of methane is available.
  • fuel gas is mixed with the combustion air as uniformly as possible. This mixing may occur either in the burner in front of the fire chamber or in the fire .chamber itself.
  • the turbulence of the gasair mixture is often artificially increased for example by generating a whirling movement thereof in the combustion chamber by the use of a so-called swirl body by means of which the combustion air, as it is introduced into the combustion chamber, is given a swirling motion.
  • the gas and air supplies are regulated simultaneously with changes in load so that the ratio thereof remains constant.
  • the gas burner according to the present invention is so constructed and designed that the above mentioned difiiculties are eliminated. It is characterized by a centrally arranged fuel gas nozzle with a radially outwardly directed ring shaped slit nozzle, a ring shaped swirl body arranged around this nozzle for imparting swirling motion to the combustion air entering the combustion chamber and a similarly ring shaped ignition chamber arranged around the fuel gas nozzle.
  • the hot combustion gases generated in the ignition chamber mix with the mixture of air and fuel gas flowing away from the zone between the swirl body and the fuel nozzle whereby the latter is heated and maintained in ignitable condition.
  • the burner is mounted on the upper end of a vertically disposed double walled combustion chamber only the upper portion of which is shown in the drawing.
  • the combustion chamber housing includes an outer cylindrical wall 1 having an upper end wall In and a concentrically arranged inner cylindrical Wall 2 spaced therefrom having an upper wall 2a.
  • the tubular fuel gas nozzle 3 is ar- 2,850,875 Patented Sept. 9, 1958 ranged in the axis of the combustion chamber and terminates at its lower end in the radial slit nozzle 4.
  • Connected to the upper end of the gas nozzle 3 is the gas supply conduit 5.
  • the fuel gas flows at a high variable velocity out of the slit 4 and'flow's outwardly and downwardly into the swirling current of combustion air which enters through the orifices of the swirl body 6 to which air is supplied through the pipe 7 adjacent the upper end of the combustion chamber.
  • the swirl body 6 may 'consist of a ring of diagonally disposed, spaced apart plates defining diagonal slits or orifices through which the air passes.
  • the fuel gas penetrates into the air stream flowing from 6 to a depth corresponding to its velocity and mixes therewith and burns.
  • the volume of air which mixes with the fuel gas therefore varies with the amount and velocity of fuel gas introduced.
  • the local excess of air in the flame zone is therefore smaller than the ratio of the total amount of air to the total amount of gas.
  • a second tubular conduit 9a Extending through the end walls of the combustion chamber and spaced concentrically around the fuel nozzle 3 is a second tubular conduit 9a which terminates a substantial distance from the inner end of the fuel nozzle. Ignition fuel gas is introduced into the upper end of the second tubular conduit 9a through the pipe 9 and is emitted radially outwardly from the lower end through the openings 10. Concentrically arranged about the inner end of the fuel nozzle 3 is a third tubular conduit 8a which extends inwardly over the inner end of the fuel nozzle 3 to form an ignition chamber 8. Five to ten percent of the total fuel gas supplied to the burner is fed through the second tubular conduit 9a and is introduced into the ignition chamber 8 through the openings 10.
  • Combustion air is also introduced into the ignition chamber 8 through the opposed openings 11 in the third tubular conduit 8a.
  • the hot combustion gas formed in the ignition chamber flows downwardly and mixes with the mixture of air and fuel gas formed adjacent the nozzle 4 and the swirl body 6 so that locally in this mixing zone a high temperature is attained which increases the combustion velocity of the mixture and broadens the ignition range.
  • a flange 12 extends inwardly from the wall of the ignition chamber 8 below the openings 10 and 11 and serves to define a more restricted mixing chamber or zone for the fuel gas and air admitted to the ignition chamber.
  • a series of holes 13 in the wall of the chamber 8 below the flange 12 permits a limited flow of air into the ignition chamber to provide additional air for the flame.
  • a series of holes 14 in the wall of the inner cylinder 2 permits a limited flow of air to the interior thereof.
  • the described burner it is possible to regulate the combustion in combustion chambers having constant air supplies within a considerable range without the use of additional mechanical means for regulating the air supply.
  • This is essential in gas turbine installations.
  • the burner provides a constructive solution to the problem which is simpler and cheaper than the gas burners heretofore proposed.
  • the burner is so designed that the gas nozzle is easily replaced by an oil jet nozzle.
  • the swirl bodies need not be changed.
  • the time required for the changeover from oil to gas or vice versa is only a fraction of the time which would be required to change the swirl body.
  • an oil jet nozzle can be built into the gas burner so that it is possible to burn a mixture of gas and oil or to shift from one to the other at any time without interruption.
  • a gas burner comprising a combustion chamber having concentric spaced apart cylindrical side walls and spaced apart upper end walls closing the adjacent ends of said side walls, a tubular fuel .nozzle extending axially through said end walls and having a ring shaped jet adjacent its inner end, a second tubular conduit extending through said end walls and surrounding said fuel nozzle and terminating at a substantial distance from the inner end of said fuel nozzle in jet openings, 'a third tubularconduit surrounding the inner end portion of said second tubular conduit and extending inwardly over the inner end of said fuel nozzle, jet openings in said third tubular conduit opposed to the jet openings in said second tubular conduit, a ring of orifices in the inner end wall of said combustion chamber surrounding the jet of said fuel nozzle, said orifices being so shaped as to impart a swirling motion to air passing therethrough, means for supplying air under pres- 5 said second tubular conduit.

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

Description

Sept. 9, 1 958 w, GAHWYLER 2,850,875
' I GAS BURNER v Filed Aug. 28, 1953 INVENT OR ATTORNEYS United States Patent F GAS BURNER Wolfgang Giihwyler, Zurich, Switzerland, assignor to Aktiengesellschaft Brown, Boveri & Cie, Baden, Switzerland, a joint-stock company Application August 28, 1953, Serial N 0. 377,204
Claims priority, application Switzerland August 15, 1952 1 Claim. (Cl. 60--39.74)
The invention relates to a gas burner adapted for use in the combustion chambers of gas turbine installations where a gaseous fuel such as one consisting principally of methane is available.
The burning of such gases in a gas turbine combustion chamber gives rise to difficulties when the speed of the air compressor and the mass of air flowing through the combustion chamber remain constant at all loads as is customary in such installations. The very narrow ignition limits of methane-air mixtures beyond which they will not burn severely limits the possible range of control of a gas turbine installation operated therewith. In a combustion chamber of the usual dimensions the gas velocity often is a multiple of the flame propagation velocity.
Ordinarily, fuel gas is mixed with the combustion air as uniformly as possible. This mixing may occur either in the burner in front of the fire chamber or in the fire .chamber itself. In order to attain a high degree of loading of the combustion chamber the turbulence of the gasair mixture is often artificially increased for example by generating a whirling movement thereof in the combustion chamber by the use of a so-called swirl body by means of which the combustion air, as it is introduced into the combustion chamber, is given a swirling motion. Always, if possible, the gas and air supplies are regulated simultaneously with changes in load so that the ratio thereof remains constant.
With the known means for improving combustion it has not heretofore been possible in gas turbine combustion chambers with a constant air throughput to obtain a stable flame at less than full throttle. Even before reaching the ignition limit the flame begins to vibrate and becomes unstable and this vibration is communicated to the gas and air columns associated with the combustion process. As a result, as already stated, the regulation of the process is severely limited.
The gas burner according to the present invention is so constructed and designed that the above mentioned difiiculties are eliminated. It is characterized by a centrally arranged fuel gas nozzle with a radially outwardly directed ring shaped slit nozzle, a ring shaped swirl body arranged around this nozzle for imparting swirling motion to the combustion air entering the combustion chamber and a similarly ring shaped ignition chamber arranged around the fuel gas nozzle. The hot combustion gases generated in the ignition chamber mix with the mixture of air and fuel gas flowing away from the zone between the swirl body and the fuel nozzle whereby the latter is heated and maintained in ignitable condition.
The invention is schematically illustrated in the accompanying drawing.
The burner is mounted on the upper end of a vertically disposed double walled combustion chamber only the upper portion of which is shown in the drawing. The combustion chamber housing includes an outer cylindrical wall 1 having an upper end wall In and a concentrically arranged inner cylindrical Wall 2 spaced therefrom having an upper wall 2a. The tubular fuel gas nozzle 3 is ar- 2,850,875 Patented Sept. 9, 1958 ranged in the axis of the combustion chamber and terminates at its lower end in the radial slit nozzle 4. Connected to the upper end of the gas nozzle 3 is the gas supply conduit 5. The fuel gas flows at a high variable velocity out of the slit 4 and'flow's outwardly and downwardly into the swirling current of combustion air which enters through the orifices of the swirl body 6 to which air is supplied through the pipe 7 adjacent the upper end of the combustion chamber. The swirl body 6 may 'consist of a ring of diagonally disposed, spaced apart plates defining diagonal slits or orifices through which the air passes. The fuel gas penetrates into the air stream flowing from 6 to a depth corresponding to its velocity and mixes therewith and burns. The volume of air which mixes with the fuel gas therefore varies with the amount and velocity of fuel gas introduced. The local excess of air in the flame zone is therefore smaller than the ratio of the total amount of air to the total amount of gas.
Extending through the end walls of the combustion chamber and spaced concentrically around the fuel nozzle 3 is a second tubular conduit 9a which terminates a substantial distance from the inner end of the fuel nozzle. Ignition fuel gas is introduced into the upper end of the second tubular conduit 9a through the pipe 9 and is emitted radially outwardly from the lower end through the openings 10. Concentrically arranged about the inner end of the fuel nozzle 3 is a third tubular conduit 8a which extends inwardly over the inner end of the fuel nozzle 3 to form an ignition chamber 8. Five to ten percent of the total fuel gas supplied to the burner is fed through the second tubular conduit 9a and is introduced into the ignition chamber 8 through the openings 10. Combustion air is also introduced into the ignition chamber 8 through the opposed openings 11 in the third tubular conduit 8a. The hot combustion gas formed in the ignition chamber flows downwardly and mixes with the mixture of air and fuel gas formed adjacent the nozzle 4 and the swirl body 6 so that locally in this mixing zone a high temperature is attained which increases the combustion velocity of the mixture and broadens the ignition range.
Referring to the drawing it will be seen that a flange 12 extends inwardly from the wall of the ignition chamber 8 below the openings 10 and 11 and serves to define a more restricted mixing chamber or zone for the fuel gas and air admitted to the ignition chamber. A series of holes 13 in the wall of the chamber 8 below the flange 12 permits a limited flow of air into the ignition chamber to provide additional air for the flame. Similarly a series of holes 14 in the wall of the inner cylinder 2 permits a limited flow of air to the interior thereof.
Withv the described burner it is possible to regulate the combustion in combustion chambers having constant air supplies within a considerable range without the use of additional mechanical means for regulating the air supply. This is essential in gas turbine installations. Thus the burner provides a constructive solution to the problem which is simpler and cheaper than the gas burners heretofore proposed. In installations which are designed to operate with either oil or gas, the burner is so designed that the gas nozzle is easily replaced by an oil jet nozzle. The swirl bodies need not be changed. The time required for the changeover from oil to gas or vice versa is only a fraction of the time which would be required to change the swirl body. Moreover an oil jet nozzle can be built into the gas burner so that it is possible to burn a mixture of gas and oil or to shift from one to the other at any time without interruption.
I claim:
A gas burner comprising a combustion chamber having concentric spaced apart cylindrical side walls and spaced apart upper end walls closing the adjacent ends of said side walls, a tubular fuel .nozzle extending axially through said end walls and having a ring shaped jet adjacent its inner end, a second tubular conduit extending through said end walls and surrounding said fuel nozzle and terminating at a substantial distance from the inner end of said fuel nozzle in jet openings, 'a third tubularconduit surrounding the inner end portion of said second tubular conduit and extending inwardly over the inner end of said fuel nozzle, jet openings in said third tubular conduit opposed to the jet openings in said second tubular conduit, a ring of orifices in the inner end wall of said combustion chamber surrounding the jet of said fuel nozzle, said orifices being so shaped as to impart a swirling motion to air passing therethrough, means for supplying air under pres- 5 said second tubular conduit.
References Cited in the file of this patent UNITED STATES PATENTS Lonergan Oct. 25, 1932 1,938,335 Hubbard et al Dec. 5, 1933 2,715,813 Holmes et al Aug. 23, 1955 2,745,249 Sanborn May 15, 1956
US377204A 1952-08-15 1953-08-28 Gas burner Expired - Lifetime US2850875A (en)

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Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2982099A (en) * 1956-10-09 1961-05-02 Rolls Royce Fuel injection arrangement in combustion equipment for gas turbine engines
US3283502A (en) * 1964-02-26 1966-11-08 Arthur H Lefebvre Fuel injection system for gas turbine engines
US3703259A (en) * 1971-05-03 1972-11-21 Gen Electric Air blast fuel atomizer
US4105393A (en) * 1973-12-07 1978-08-08 Consultant Gas Engineer Limited Fuel burners
US4230445A (en) * 1977-06-17 1980-10-28 Sulzer Brothers Ltd. Burner for a fluid fuel
US4589260A (en) * 1982-11-08 1986-05-20 Kraftwerk Union Aktiengesellschaft Pre-mixing burner with integrated diffusion burner
US4653278A (en) * 1985-08-23 1987-03-31 General Electric Company Gas turbine engine carburetor
FR2592321A1 (en) * 1986-01-02 1987-07-03 Rhone Poulenc Chim Base PROCESS FOR OBTAINING A HIGH TEMPERATURE GASEOUS PHASE, AND DEVICE FOR CARRYING OUT THIS PROCESS. APPLICATION TO THE TREATMENT OF LIQUID OR GASEOUS PHASES, WITH OR WITHOUT SOLIDS, AND SPRAY SOLIDS.
EP0300079A1 (en) * 1986-04-22 1989-01-25 Cornel J. Dutescu Gaseous fuel reactor
US4842509A (en) * 1983-03-30 1989-06-27 Shell Oil Company Process for fuel combustion with low NOx soot and particulates emission
US4901524A (en) * 1987-11-20 1990-02-20 Sundstrand Corporation Staged, coaxial, multiple point fuel injection in a hot gas generator
US4967561A (en) * 1982-05-28 1990-11-06 Asea Brown Boveri Ag Combustion chamber of a gas turbine and method of operating it
US4974415A (en) * 1987-11-20 1990-12-04 Sundstrand Corporation Staged, coaxial multiple point fuel injection in a hot gas generator
US4977742A (en) * 1989-04-21 1990-12-18 Stirling Thermal Motors, Inc. Stirling engine with integrated gas combustor
EP0479174A2 (en) * 1990-10-02 1992-04-08 R.B.L. Riello Bruciatori Legnago Spa Combustion head for gas burners
US5263325A (en) * 1991-12-16 1993-11-23 United Technologies Corporation Low NOx combustion
US5388409A (en) * 1993-05-14 1995-02-14 Stirling Thermal Motors, Inc. Stirling engine with integrated gas combustor
WO1995032395A1 (en) * 1994-05-25 1995-11-30 Westinghouse Electric Corporation Gas turbine combustor
US5647215A (en) * 1995-11-07 1997-07-15 Westinghouse Electric Corporation Gas turbine combustor with turbulence enhanced mixing fuel injectors
US5761906A (en) * 1995-01-13 1998-06-09 European Gas Turbines Limited Fuel injector swirler arrangement having a shield means for creating fuel rich pockets in gas-or liquid-fuelled turbine
US5921764A (en) * 1997-07-18 1999-07-13 Stirling Thermal Motors, Inc. Heat engine combustor
US6389815B1 (en) * 2000-09-08 2002-05-21 General Electric Company Fuel nozzle assembly for reduced exhaust emissions
US6609376B2 (en) 2000-02-14 2003-08-26 Ulstein Turbine As Device in a burner for gas turbines
US20070151248A1 (en) * 2005-12-14 2007-07-05 Thomas Scarinci Gas turbine engine premix injectors
WO2008023011A1 (en) * 2006-08-22 2008-02-28 Danieli & C. Officine Meccaniche S.P.A. Burner
US20100071663A1 (en) * 2008-09-23 2010-03-25 Pratt & Whitney Canada Corp. External rigid fuel manifold
US20140075940A1 (en) * 2011-05-06 2014-03-20 Xiangtan Electric Manufacturing Co., Ltd Apparatus for heating working fluid of gas turbine-solar power generation system
US20140230448A1 (en) * 2009-03-23 2014-08-21 Siemens Aktiengesellschaft Method for preventing flashback in a burner having at least one swirl generator
US8893500B2 (en) 2011-05-18 2014-11-25 Solar Turbines Inc. Lean direct fuel injector
US8919132B2 (en) 2011-05-18 2014-12-30 Solar Turbines Inc. Method of operating a gas turbine engine
US9182124B2 (en) 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same
US20150354825A1 (en) * 2013-03-11 2015-12-10 Mitsubishi Hitachi Power Systems, Ltd. Fuel spray nozzle

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BE535905A (en) * 1954-02-23
DE1074920B (en) * 1955-07-07 1960-02-04 Ing habil Fritz A F Schmidt Murnau Dr (Obb) Method and device for regulating gas turbine combustion chambers with subdivided combustion and several pressure levels
US3231201A (en) * 1963-04-29 1966-01-25 Magic Servant Products Company Burner assembly
DE1262492B (en) * 1965-10-21 1968-03-07 Ray Oel Und Gasbrenner G M B H Fan burner for gaseous fuels
US3368605A (en) * 1966-02-03 1968-02-13 Zink Co John Burner assembly for lean fuel gases
NL171191C (en) * 1973-12-20 1983-02-16 Shell Int Research GAS BURNER AND METHOD FOR PARTIAL BURNING OF A GASEOUS FUEL.
DE3317035A1 (en) * 1983-05-10 1984-11-15 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau MULTIPLE BURNER
SE441775B (en) * 1983-09-30 1985-11-04 Hb Consult Raodgivande Ing Ab BRENNARE
JPS60207820A (en) * 1984-03-26 1985-10-19 ザ　ギヤレツト　コーポレーシヨン Method and device for ejecting and atomizing fuel
EP2829797A1 (en) 2013-07-23 2015-01-28 Shell Internationale Research Maatschappij B.V. Burner, reactor and process for gasification of a hydrocarbon feed
DE102022202936A1 (en) 2022-03-24 2023-09-28 Rolls-Royce Deutschland Ltd & Co Kg Nozzle assembly with central fuel tube sealed against inflow of air
DE102022202937A1 (en) 2022-03-24 2023-09-28 Rolls-Royce Deutschland Ltd & Co Kg Nozzle assembly with central fuel supply and at least two air channels

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US1884764A (en) * 1927-12-28 1932-10-25 Bastian Morley Co Burner structure
US1938335A (en) * 1927-10-20 1933-12-05 Babcock & Wilcox Co Combined gas and oil burner
US2715813A (en) * 1952-04-14 1955-08-23 Frederick T Holmes Fuel injector and flame holder
US2745249A (en) * 1946-10-22 1956-05-15 Ryan Aeronautical Co Reheater and fuel vaporizer for jet propulsion engines

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DE577854C (en) * 1930-12-24 1933-06-06 Hugo Kratz Dr Insertable nozzle body for pipe-shaped mixed gas burners
US1922348A (en) * 1931-08-13 1933-08-15 Vernon S Beck Burner

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Publication number Priority date Publication date Assignee Title
US1938335A (en) * 1927-10-20 1933-12-05 Babcock & Wilcox Co Combined gas and oil burner
US1884764A (en) * 1927-12-28 1932-10-25 Bastian Morley Co Burner structure
US2745249A (en) * 1946-10-22 1956-05-15 Ryan Aeronautical Co Reheater and fuel vaporizer for jet propulsion engines
US2715813A (en) * 1952-04-14 1955-08-23 Frederick T Holmes Fuel injector and flame holder

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2982099A (en) * 1956-10-09 1961-05-02 Rolls Royce Fuel injection arrangement in combustion equipment for gas turbine engines
US3283502A (en) * 1964-02-26 1966-11-08 Arthur H Lefebvre Fuel injection system for gas turbine engines
US3703259A (en) * 1971-05-03 1972-11-21 Gen Electric Air blast fuel atomizer
US4105393A (en) * 1973-12-07 1978-08-08 Consultant Gas Engineer Limited Fuel burners
US4230445A (en) * 1977-06-17 1980-10-28 Sulzer Brothers Ltd. Burner for a fluid fuel
US4967561A (en) * 1982-05-28 1990-11-06 Asea Brown Boveri Ag Combustion chamber of a gas turbine and method of operating it
US4589260A (en) * 1982-11-08 1986-05-20 Kraftwerk Union Aktiengesellschaft Pre-mixing burner with integrated diffusion burner
US4842509A (en) * 1983-03-30 1989-06-27 Shell Oil Company Process for fuel combustion with low NOx soot and particulates emission
US4653278A (en) * 1985-08-23 1987-03-31 General Electric Company Gas turbine engine carburetor
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DE1062873B (en) 1959-08-06
GB721126A (en) 1954-12-29
CH303030A (en) 1954-11-15

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