GB616300A - Burner - Google Patents

Burner

Info

Publication number
GB616300A
GB616300A GB1339?/46A GB1339546A GB616300A GB 616300 A GB616300 A GB 616300A GB 1339546 A GB1339546 A GB 1339546A GB 616300 A GB616300 A GB 616300A
Authority
GB
United Kingdom
Prior art keywords
fuel
air
nozzle
tube
shield
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.)
Expired
Application number
GB1339?/46A
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.)
Bendix Aviation Corp
Original Assignee
Bendix Aviation 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 Bendix Aviation Corp filed Critical Bendix Aviation Corp
Publication of GB616300A publication Critical patent/GB616300A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L17/00—Inducing draught; Tops for chimneys or ventilating shafts; Terminals for flues
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2700/00—Installations for increasing draught in chimneys; Specific draught control devices for locomotives
    • F23L2700/002—Specific draught control devices for locomotives
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

616,300. Burners. BENDIX AVIATION CORPORATION. May 2, 1946, No. 13395. Convention date, May 16, 1945. [Class 75 (i)] [Also in Group XII] A burner comprises in combination a tubular combustion chamber having its outlet end open, the other end being closed by a wall supporting a fuel nozzle, a jacket surrounding the combustion tube forming an air supply duct through which air is supplied to a plurality of circumferentially spaced passages formed in the combustion tube adjacent the fuel nozzle tangentially oblique with respect to the tube axis and all pointing in the same rotational sense so that air passing therethrough imparts rotation to that air surrounding the fuel spray, and wherein (a) the fuel nozzle is of the whirl type and the rotation of the air surrounding the fuel is in the same sense as the whirl of the fuel, or (b) a cup shaped shield surrounds the fuel spray where it leaves the nozzle, an annular air space being provided between the outside of the said shield and the adjacent wall of the combustion chamber. A gaseous liquid or powdered fuel burner suitable for use in a gaseous turbine as jet propulsion aircraft power plant in which the fuel is injected and burnt in a moving air column comprises a whirl type nozzle 13, Fig. 1, discharging fuel through a cylindrical cup-shaped shield 16 into a burner tube 7 supported by a cap 6 in a shell 5 supplied with air under pressure by a compressor or the forward movement of the aircraft, the burner tube being provided with a series of holes 8, 9, 10, 11 of progressively increasing flow capacity and inclined at progressively decreasing angles, both tangentially and axially, as they approach the discharge end of the tube 7. Air is supplied to the fuel as it issues from the nozzle 13 by three small axial passages 19 and holes 20 in the forward end of the shield 16. The shield 16 is fitted with an electric spark igniter 26 and is surrounded by a conical wall 17 formed with holes 21, 22, 23 preferably of increasing flow capacity towards the forward end to control the air circulating in the breech end of the tube 7. In another construction the conical wall is formed with guide vanes extruding in reverse directions over radially spaced openings. The nozzle 13 may consist of a body 35, Fig. 6, having a nose 36 formed with a discharge orifice 37 and fitted with a spring-pressed valve member 38 having a spirally grooved enlargement 43 and a spirally grooved end 41. At low pressures liquid fuel supplied through a conduit 47 is swirled by passage through the grooves in the end 41. As the fuel pressure increases the member 38 moves backward against the resistance of the spring 39 and the swirling is produced by the grooves in the enlargement 43. Specifications 604,466 and 608,031 are referred to.
GB1339?/46A 1945-05-16 1946-05-02 Burner Expired GB616300A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US594006A US2517015A (en) 1945-05-16 1945-05-16 Combustion chamber with shielded fuel nozzle

Publications (1)

Publication Number Publication Date
GB616300A true GB616300A (en) 1949-01-19

Family

ID=24377126

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1339?/46A Expired GB616300A (en) 1945-05-16 1946-05-02 Burner

Country Status (2)

Country Link
US (1) US2517015A (en)
GB (1) GB616300A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE957003C (en) * 1951-11-20 1957-01-24 Hiller Helicopters Continuously working ramjet engine for rotor blades of helicopters
DE961672C (en) * 1953-01-19 1957-04-11 Lucas Industries Ltd Annular combustion chamber for jet engines, gas turbines or the like.
EP0111874A1 (en) * 1982-12-15 1984-06-27 Gewerkschaft Sophia-Jacoba Steinkohlenbergwerk A device for burning coal dust
US4488869A (en) * 1982-07-06 1984-12-18 Coen Company, Inc. High efficiency, low NOX emitting, staged combustion burner

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3124193A (en) * 1964-03-10 Oil burner assembly
US2734560A (en) * 1956-02-14 Burner and combustion system
US2575889A (en) * 1946-03-26 1951-11-20 Rolls Royce Burner assembly for the combustion chambers of internal-combustion turbines
US2627721A (en) * 1947-01-30 1953-02-10 Packard Motor Car Co Combustion means for jet propulsion units
GB684670A (en) * 1947-10-21 1952-12-24 Power Jets Res & Dev Ltd Improvements in or relating to combustion apparatus
NL72524C (en) * 1947-11-03
US2720078A (en) * 1948-03-01 1955-10-11 Solar Aircraft Co Burner for use in high velocity ducts
US2644302A (en) * 1948-06-17 1953-07-07 Gen Electric Combustion chamber having a flat wall liner with oppositely disposed apertures
US2654996A (en) * 1948-10-26 1953-10-13 Oerlikon Maschf Gas turbine combustion chamber
BE503026A (en) * 1950-07-17
US2651178A (en) * 1951-01-18 1953-09-08 A V Roe Canada Ltd Combination injector and stabilizer for gas turbine afterburners
US2780062A (en) * 1951-04-03 1957-02-05 Curtiss Wright Corp Jet engine burner construction
US2941362A (en) * 1953-11-02 1960-06-21 Curtiss Wright Corp Flame holder construction
US2941363A (en) * 1955-04-11 1960-06-21 Bendix Aviat Corp Dual baffled igniter for combustion chamber
US3046731A (en) * 1955-10-07 1962-07-31 Edward Pohlmann Flame stabilization in jet engines
US2930195A (en) * 1956-02-14 1960-03-29 United Aircraft Corp Oscillating flow combustion chamber
US3002819A (en) * 1958-02-20 1961-10-03 Phillips Petroleum Co Apparatus for testing fuels
US2960983A (en) * 1959-01-28 1960-11-22 Goss Gas Inc Heating unit
US3138193A (en) * 1960-11-23 1964-06-23 James L Hagerman Combustion of liquid fuel
US3854503A (en) * 1971-08-05 1974-12-17 Lucas Industries Ltd Flame tubes
GB1595224A (en) * 1977-02-04 1981-08-12 Rolls Royce Combustion equipment for gas turbine engines
US4765136A (en) * 1985-11-25 1988-08-23 United Technologies Corporation Gas turbine engine augmentor
FR2748088B1 (en) * 1996-04-24 1998-05-29 Snecma OPTIMIZATION OF THE MIXTURE OF BURNED GASES IN AN ANNULAR COMBUSTION CHAMBER
US7513098B2 (en) 2005-06-29 2009-04-07 Siemens Energy, Inc. Swirler assembly and combinations of same in gas turbine engine combustors
US20140338340A1 (en) * 2013-03-12 2014-11-20 General Electric Company System and method for tube level air flow conditioning
CN105060247B (en) * 2015-08-06 2017-12-08 广东合即得能源科技有限公司 A kind of activation system for being used to start reforming hydrogen production device
FR3041742B1 (en) * 2015-09-30 2017-11-17 Ifp Energies Now COMBUSTION CHAMBER FOR A TURBINE, IN PARTICULAR A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, ESPECIALLY ELECTRICAL ENERGY.
FR3049044B1 (en) * 2016-03-18 2019-12-20 IFP Energies Nouvelles COMBUSTION CHAMBER OF A TURBINE, IN PARTICULAR OF A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, PARTICULARLY ELECTRICAL ENERGY.
CN106621149A (en) * 2016-11-30 2017-05-10 福建天广消防有限公司 Suspended gas extinguishing device
WO2021242229A1 (en) * 2020-05-27 2021-12-02 Aerojet Rocketdyne, Inc. Two-piece combustor
EP4083509A1 (en) * 2021-04-30 2022-11-02 Ansaldo Energia Switzerland AG Method for calibrating a gas turbine burner during recondition or production by using a calibrating pin

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US478295A (en) * 1892-07-05 george h
US1336261A (en) * 1919-08-21 1920-04-06 Lewis L Scott Combustion apparatus
US1412023A (en) * 1920-05-11 1922-04-04 Todd Shipyards Corp Oil-burning apparatus
FR25719E (en) * 1921-12-03 1923-05-17 Burners improvements
US1603032A (en) * 1924-11-19 1926-10-12 Hauck Mfg Co Burner apparatus for liquid fuels
GB259044A (en) * 1925-10-26 1926-10-07 Theodore Livinus Reepmaker Improvements in burners for liquid fuel
US1828326A (en) * 1929-08-10 1931-10-20 Lanser Alfred Burner
US1924878A (en) * 1929-09-03 1933-08-29 Richard W Parry Method and apparatus for burning pulverized fuel
US2049150A (en) * 1932-03-12 1936-07-28 Texas Gulf Sulphur Co Fuel burner
CH164037A (en) * 1932-09-10 1933-09-15 Schwer Edouard Burner for liquid fuel.
US2072731A (en) * 1934-12-03 1937-03-02 Steam Motors Inc Oil burner
US2156121A (en) * 1937-04-07 1939-04-25 James N Macrae Burner
US2398654A (en) * 1940-01-24 1946-04-16 Anglo Saxon Petroleum Co Combustion burner
US2353438A (en) * 1941-06-16 1944-07-11 Oil Devices Pot type burner and means for the delivery of secondary air

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE957003C (en) * 1951-11-20 1957-01-24 Hiller Helicopters Continuously working ramjet engine for rotor blades of helicopters
DE961672C (en) * 1953-01-19 1957-04-11 Lucas Industries Ltd Annular combustion chamber for jet engines, gas turbines or the like.
US4488869A (en) * 1982-07-06 1984-12-18 Coen Company, Inc. High efficiency, low NOX emitting, staged combustion burner
EP0111874A1 (en) * 1982-12-15 1984-06-27 Gewerkschaft Sophia-Jacoba Steinkohlenbergwerk A device for burning coal dust

Also Published As

Publication number Publication date
US2517015A (en) 1950-08-01

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