US2404335A - Liquid fuel burner, vaporizer, and combustion engine - Google Patents

Liquid fuel burner, vaporizer, and combustion engine Download PDF

Info

Publication number
US2404335A
US2404335A US379735A US37973541A US2404335A US 2404335 A US2404335 A US 2404335A US 379735 A US379735 A US 379735A US 37973541 A US37973541 A US 37973541A US 2404335 A US2404335 A US 2404335A
Authority
US
United States
Prior art keywords
air
combustion
flame
vaporizer
liquid fuel
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 - Lifetime
Application number
US379735A
Inventor
Whittle Frank
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development Ltd
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
Priority to GB258412X priority Critical
Application filed by Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Application granted granted Critical
Publication of US2404335A publication Critical patent/US2404335A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • F23R3/48Flame tube interconnectors, e.g. cross-over tubes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/10Air inlet arrangements for primary air
    • F23R3/12Air inlet arrangements for primary air inducing a vortex
    • F23R3/14Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft

Description

F. WHITTLE 2,404,335

LIQUID FUEL BURNER, VAPORIZER, AND COMBUSTION ENGINE Juli 16, 1946.

Filed Feb. 19, 194].

Pate'nted July 16, 1946' LIQUID FUEL BURNER, VAPORIZER, AND COMBUSTION ENGINE Frank Whittle, Rugby, England, assignor to Power Jets (Research London, England Application 2 Claims.

This invention relates to liquid fuel burners and vaporizers and to combustion engines or systems employing the same. In particular, although not exclusively, it is applicable to power units of aircraft propulsion systems of the previously known or proposed type in which the output of an air compressor takes part in combustion and then drives a gas turbine which in turn drives the compressor, the eilluent gases forming a propulsive reaction jet. The invention in some of its aspects is, however, applicable to liquid fuel burners and Vaporizers used in quite different connections, for example, in water heating apparatus, steam raising boilers or otherwise, wherever a plurality of combustion chambers and burners are to be operated in parallel and it is especially desired to equalize the performance of all.

The primary object of the invention is to provide highly efficient and uniform fuel combustion and air heating by a plurality of burners in different combustion chambers. A further object is to provide a burner and vaporizer arrangement which will be effective in an airstream of extremely high velocity; another object is to improve on igniting arrangements where a plurality of burners are in separate combustion chambers, and yet another object is to provide structurally simple yet efficient liquid fuel supply, Vaporizers, and burner arrangements in a power unit of the above mentioned type, wherein the compressor output is divided among a plurality of combustion chambers before being led into the turbine,

According to one feature of the invention, a

plurality of fuel jets are supplied from a common source, in parallel, and in each individual connectiona pressure-difference creating device such as a constriction, is provided, and is preferably so selected as to ensure the creation of a substantial pressure difference between the source and the jet in all ordinary running conditions. These constrictions are provided primarily to ensure that any disturbances of the resistance to flow occurring in one jet or associated vaporizer does not produce a surge of pressure or other inequality in a pipeline which is connected to another jet or jets and which may result in instability and fluctuation of fuel supply. According to another feature of the invention, each jet assembly preferably comprises a number of orifices arranged in spider or star fashion and directed substantially in an up-stream direction in a tubular combustion chamber through which an airstream of high velocity is created. Each jet is supplied by a vaporizer in the form of a pipe immediately Development) Limited,

February 19, 1941, Serial No. 379,735 Great Britain December 9, 1939 behind it in the airstream around which the combustion products pass. The combustion chamber surrounding the jets and vaporizers is preferably a tube which converges to the down-stream side of the jet and such tube is preferably co-axlally surrounded by a duct which leads the air into the combustion chamber, the sense of direction of flow of the air being reversed as it passes from the outer to the inner passage. Preferably in the air-flow immediately before the jet, means are provided for establishing a high degree of turbulence in the air, and such means may take the form of concentric rings of vanes arranged with opposite or different pitch. Each combustion chamber may be provided with a pilot or starter jet for the purpose of providing the initial heat for the Vaporizers, and each combustion chamber, or as is preferred, one chamber of a plurality, may be provided with igniting means comprising an electrical ignition plug. A feature of the invention resides in the interconnection of a plurality of combustion chambers by pipes for flame propagation as between one combustion chamber and its neighbor, and by this means only one chamber in a plurality need be equipped with igniting arrangements.

The invention as applied in a power unit as described in my co-pending application Serial No. 379,734, filed February 19, 1941, will now. be described more fully with the aid of the accompanying drawings, in which:

Figure 1 is a sectional view of a combustion chamber and its ignition arrangements and fuel distributor, whilst Figure 2 is an end view of the same, with the dome part removed, and

Fig. 3 is a diagrammatic view illustrating the interconnection of a plurality of combustion chambers.

For convenience, in Figure 1, the interconnecting stub pipes intended to be employed when a plurality of chambers are used in parallel are illustrated in rotationally displaced positions.

The combustion chamber is constituted by a cylindrical air casing I, to which at one end is attached a dome end 2, and at the other end a suitable closure including a connection for compressed air supply, such as a dome 3 with a circular part 3A for the connection of an air trunk. Within the casing I is mounted co-axially a flame tube 4 comprising a frusto-conical tube with a cylindrical portion 4A at its larger end. The smaller end of the flame tube 4, fits into an elbow part 5, which leads combustion products through a right angle for exit through the wall of the casthe flame tube.

' 3 ing I. The casing I, if it is one of a plurality required to operate in parallel (as in the power unit above mentioned), has air stub pipes IA leading radially from it, to connect with neighboring casings. Within these air stubs IA are, substantially co-axially, connecting the flame tube of one combustion chamber, to the flame tubes of its neighbors.

The dome 2 has passing through it a central, coaxial, bushing 2A into which fits a pilot jet 5, which is an atomising spray jet, supplied with being fitted to any convenient adjacent parts.

Parts which would otherwise interfere with the electrode BA are cut away to such clearance as is necessary to avoid sparks jumping in undesired places.

In the otherwise open end of the flame tube portion 4A, a bafiie system is provided, the object of which is to produce a high degree of turbulence in air entering the flame tube at this end. This baiile system comprises a conical rim I, an outer co-axial cylindrical sleeve 8, and an inner. coaxial cylindrical sleeve 9. Between sleeves 8 and 9 is a series of swirl vanes 8A pitched one awaysay, clockwise looking downstream, and between sleeve 9 and the bush 2A is an inner series of swirl vanes 9A, oppositely pitched. Air coming from the casing I flows through these two series of vanes as shown diagrammatically by the arrow I0, and the result is a highly turbulent, high velocity, flow of air in the flame region within Some reversal of flow in the the axis is to be found with this arrangement, and this appears to be beneflcial in sustaining combustion.

Through the dome 2 and rim 1 there project eight fuel pipes II, which continue susbtantially parallel with (and symmetrical about) the flame tube axis, for about half the length of the flame tube, and then bend back upon themselves to point upstream. They terminate in jets at I IA. Th parts of these pipes which are exposed to the flame act as Vaporizers, so that whilst liquid fuel is fed into the pipes II, vaporized fuel'is projected upstream from the jets IIA. Such an arrangement by itself has the defect that it surges if a common source. It is obvious, for example, that slight inequalitiesof heat exchange as between the pipes of the vaporizer, can result in one tube starving of liquid fuel momentarily, whilst another gains. The starved pipe becomes hotter and the gaining pipe cooler, so the condition is self-aggravating, resulting in an unstable condition, cracking of fuel, and the building up of carbon in'the pipes. Since one of the objects of the invention is to produce uniform distribution of heat in the delivered gases (as well as uniformity in a plurality of combustion chambers), the following means are adopted to overcome this diflicul y.

The pipes I I come from a common equalizing chamber I2, which is fed with liquid fuel under messure by a fuel pipe I3, and which may contain a strainer such as a gauze I2A. Where each pipe II opens into the chamber I2, there is a small orifice IIB, which, conveniently, is a screwed-on nipple. 'I'he orifices of the nipples form restrictions, and they areselected so as to produce such pressure-drop across them, as will prevent surg in the vaporizers as a whole.

neighborhood of flame stubs 4B similarly fuel under pressure by a pipe 5A. The pilot jet the pipes I I are simply fed in parallel from secondary scribed,

It is not possible readily to lay down any proportions or dimensions for the restriction oriflces IIB; these depend on the nature, dimensions, running temperature, etc., of the pipes, the nature of the fuel, and the range of flow-rates t: Ible used, and the character of the jet orifices a A.

The flame tubes 4 are perforated as at 4C for the admission of air from the casing I. The air passing through these holes 40, is regarded as air, i. e. air not necessary to complete combustion. Th primary air is that which passes through the battle system. However, in practice it is found that with the high velocities and high rates of combustion for which the invention is intended to be used, the secondary air if properly admitted, speeds up combustion and shortens the flame.

tion is common to all, and ignition gnition in all, the flame stubs in one causes 43 communicatpressures in I claim: 1. In a combustion engine of 'coaxially within each oi said one open end and additional openingsin its side ,flame tube being that thereof. a circular-sectioned flame tube located air casings having wall for the entry of air, the open end or each or. the associated air casing through which air is supplied 'to the latter, means for supplying fuel to said flame tubes uniformly adjacent the open ends of said tubes, means interconnecting the interiors of all of said air casing to balance the pressures therein, and means interconnecting the interiors of said flame tubes, said means interconnecting the air casings comprising air stub pipes extending between adjacent casings, and said means interconnecting the flame tubes comprising additional stub pipes of less diameter than and passing through said air stub pipes.

2., In a combustion engine which is opposite the end l of the character described, a plurality of combustion units each I connecting said flame tubes arranged within the comprising a circular-sectioned air casing, means for delivering compressed. air to the interior or amass 6 said casing, a circular-sectioned flame tube mounted coaxially within said casing and having one end open whereby compressed air from said casing enters and traverses said tube, means adiacent said open end for creating turbulence in the air entering said tube, means for supplying uniformly distributed fuel into the turbulent air within said tube, the wall of said tilbe being periorated at both axially and peripherally spaced points for the passage of secondary air thereinto from said casing, and an outlet conduit for conducting products of combustion from the other end of said ilame tube to the exteriors! saidcaslng, means for interconnecting the air casings of said units, and 'means for interconnecting the flame tubes 'of said units, said. interconnecting means comprising concentric pipes with the pipes pipes connecting said air casings.

FRANK WHI'I'ILE;

US379735A 1939-12-09 1941-02-19 Liquid fuel burner, vaporizer, and combustion engine Expired - Lifetime US2404335A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB258412X 1939-12-09

Publications (1)

Publication Number Publication Date
US2404335A true US2404335A (en) 1946-07-16

Family

ID=10234212

Family Applications (1)

Application Number Title Priority Date Filing Date
US379735A Expired - Lifetime US2404335A (en) 1939-12-09 1941-02-19 Liquid fuel burner, vaporizer, and combustion engine

Country Status (7)

Country Link
US (1) US2404335A (en)
BE (1) BE460697A (en)
CH (1) CH258412A (en)
DE (1) DE951062C (en)
FR (1) FR916262A (en)
GB (1) GB577972A (en)
NL (2) NL70682C (en)

Cited By (84)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2460451A (en) * 1946-06-13 1949-02-01 Farhall Inc Gasifying fuel burner
US2488911A (en) * 1946-11-09 1949-11-22 Surface Combustion Corp Combustion apparatus for use with turbines
US2509577A (en) * 1946-05-02 1950-05-30 Phillips John Multiple combustion products operated turbine
US2517822A (en) * 1947-10-23 1950-08-08 Ingersoll Rand Co Intermittent explosion gas turbine plant with dilution air
US2520388A (en) * 1946-11-21 1950-08-29 Power Jets Res & Dev Ltd Apparatus for supporting combustion in fast-moving air streams
US2522081A (en) * 1947-06-23 1950-09-12 Armstrong Siddeley Motors Ltd Combustion chamber with fuel vaporizing pipes for internal-combustion turbine plants
US2525207A (en) * 1947-01-13 1950-10-10 Lucas Ltd Joseph Ignition torch for internal-combustion prime movers
US2526122A (en) * 1944-11-28 1950-10-17 Vickers Electrical Co Ltd Combustion chambers with perforated end walls and upstream fuel injection for combustion turbines
US2529506A (en) * 1944-04-15 1950-11-14 Power Jets Res & Dev Ltd Burner for liquid or gaseous fuels
US2532831A (en) * 1945-01-27 1950-12-05 Breese Burners Inc Combustion chamber and turbine arrangement
US2540665A (en) * 1946-02-01 1951-02-06 Daniel And Florence Guggenheim Mechanism for coaxial feeding of two combustion liquids to a combustion chamber
US2540991A (en) * 1942-03-06 1951-02-06 Lockheed Aircraft Corp Gas reaction aircraft power plant
US2540666A (en) * 1947-06-25 1951-02-06 Daniel And Florence Guggenheim Fuel feeding and premixing apparatus for combustion chambers
US2540642A (en) * 1947-06-19 1951-02-06 Armstrong Siddeley Motors Ltd Multiple combustion chamber torch igniter and auxiliary fuel spray device arrangement for initiating combustion
US2541900A (en) * 1948-12-24 1951-02-13 A V Roe Canada Ltd Multiple fuel jet burner and torch igniter unit with fuel vaporizing tubes
US2546432A (en) * 1944-03-20 1951-03-27 Power Jets Res & Dev Ltd Apparatus for deflecting a fuel jet towards a region of turbulence in a propulsive gaseous stream
US2560207A (en) * 1948-02-04 1951-07-10 Wright Aeronautical Corp Annular combustion chamber with circumferentially spaced double air-swirl burners
US2560223A (en) * 1948-02-04 1951-07-10 Wright Aeronautical Corp Double air-swirl baffle construction for fuel burners
US2560401A (en) * 1946-02-23 1951-07-10 Armstrong Siddeley Motors Ltd Liquid fuel combustion chamber for turbine units
US2577918A (en) * 1946-05-08 1951-12-11 Kellogg M W Co Air jacketed combustion chamber flame tube
US2579614A (en) * 1944-06-23 1951-12-25 Allis Chalmers Mfg Co Combustion chamber with rotating fuel and air stream surrounding a flame core
US2581316A (en) * 1945-10-01 1952-01-01 John J Wolfersperger High rating fire-tube boiler and method of boiler operation
US2581999A (en) * 1946-02-01 1952-01-08 Gen Electric Hemispherical combustion chamber end dome having cooling air deflecting means
US2603064A (en) * 1946-12-12 1952-07-15 Chrysler Corp Combustion chamber with multiple conical sections providing multiple air paths for gas turbines
US2611243A (en) * 1944-09-01 1952-09-23 Lucas Ltd Joseph Combustion chamber for prime movers
US2612752A (en) * 1944-05-20 1952-10-07 Daniel And Florence Guggenheim Feeding apparatus, including injectors adapted to supply combustion liquids under pressure to a combustion chamber
US2616258A (en) * 1946-01-09 1952-11-04 Bendix Aviat Corp Jet engine combustion apparatus, including pilot burner for ignition and vaporization of main fuel supply
US2618928A (en) * 1944-05-19 1952-11-25 Power Jets Res & Dev Ltd Combustion apparatus with vaned fuel injector means
US2623357A (en) * 1945-09-06 1952-12-30 Birmann Rudolph Gas turbine power plant having means to cool and means to compress combustion products passing through the turbine
US2625011A (en) * 1948-07-31 1953-01-13 Armstrong Siddeley Motors Ltd Igniter for liquid fuel combustion chambers
US2632296A (en) * 1947-12-06 1953-03-24 Eugene J Houdry Process of generating power involving catalytic oxidation
US2632994A (en) * 1948-04-05 1953-03-31 Mcdonnell Aircraft Corp Ram jet engine and flame holder therefor
US2635424A (en) * 1947-08-02 1953-04-21 Szczeniowski Boleslaw Combustor for high flow velocities
US2635421A (en) * 1949-10-24 1953-04-21 Felix A Blum Pulse jet convertible to ram jetpropulsion means
US2637974A (en) * 1944-03-16 1953-05-12 Power Jets Res & Dev Ltd Combustion apparatus for an air stream and propulsive system
US2638745A (en) * 1943-04-01 1953-05-19 Power Jets Res & Dev Ltd Gas turbine combustor having tangential air inlets for primary and secondary air
US2647369A (en) * 1946-09-06 1953-08-04 Leduc Rene Combustion chamber for fluid fuel burning in an air stream of high velocity
US2648197A (en) * 1951-01-06 1953-08-11 A V Roe Canada Ltd Vaporizer tube system
US2648951A (en) * 1949-03-31 1953-08-18 Gen Motors Corp Combustor igniter cup which becomes incandescent from combustion therein
US2648950A (en) * 1949-08-24 1953-08-18 Westinghouse Electric Corp Gas turbine engine apparatus designed to burn wet pulverized fuel
US2650753A (en) * 1947-06-11 1953-09-01 Gen Electric Turbomachine stator casing
US2654996A (en) * 1948-10-26 1953-10-13 Oerlikon Maschf Gas turbine combustion chamber
US2658340A (en) * 1945-02-01 1953-11-10 Power Jets Res & Dev Ltd Apparatus for igniting fuel in fast-moving hot gas streams
US2664703A (en) * 1949-06-28 1954-01-05 A V Roe Canada Ltd Preheater and vaporizer for gas turbine engines
US2664702A (en) * 1947-08-11 1954-01-05 Power Jets Res & Dev Ltd Cooled flame tube
US2667033A (en) * 1947-01-09 1954-01-26 Power Jets Res & Dev Ltd Combustion apparatus for operation in fast-moving air streams
US2672729A (en) * 1950-10-28 1954-03-23 Boeing Co Spark plug
US2672727A (en) * 1951-05-31 1954-03-23 Westinghouse Electric Corp Fuel vaporizer system for combustion chambers
US2673445A (en) * 1949-06-21 1954-03-30 Bruno W Bruckmann Turbojet and rocket motor combination with hot gas ignition system for nonself-reaction rocket fuels
US2685168A (en) * 1948-01-02 1954-08-03 Phillips Petroleum Co Combustion chamber
US2694444A (en) * 1951-03-17 1954-11-16 American Mach & Foundry Jet-type burner for tobacco curers
US2697910A (en) * 1950-07-29 1954-12-28 Thermal Res And Engineering Co Fluid fuel burner with self-contained fuel vaporizing unit
US2720754A (en) * 1950-09-29 1955-10-18 Mcdonnell Aircraft Corp Flameholder for ram jet engine
US2722803A (en) * 1951-05-23 1955-11-08 Gen Electric Cooling means for combustion chamber cross ignition tubes
US2727358A (en) * 1952-03-27 1955-12-20 A V Roe Canada Ltd Reverse-flow vaporizer with single inlet and plural outlets
US2768497A (en) * 1951-02-03 1956-10-30 Gen Motors Corp Combustion chamber with swirler
US2773350A (en) * 1950-01-31 1956-12-11 Hillard E Barrett Combustion chamber assembly for ram jet fuel burner
US2775238A (en) * 1953-01-29 1956-12-25 Surface Combustion Corp Fuel burning and air heating apparatus
US2780062A (en) * 1951-04-03 1957-02-05 Curtiss Wright Corp Jet engine burner construction
US2798360A (en) * 1950-10-06 1957-07-09 Gen Motors Corp Ducted fan type jet propulsion engine
US2800768A (en) * 1954-08-19 1957-07-30 United Aircraft Corp Burner construction
US2807316A (en) * 1953-06-11 1957-09-24 Lucas Industries Ltd Liquid fuel combustion chambers for jet-propulsion engines, gas turbines, or other purposes
US2827759A (en) * 1950-01-18 1958-03-25 Bruno W Bruckmann Gas turbine aricraft power plant having a contraflow air-fuel combustion system
US2839048A (en) * 1952-09-08 1958-06-17 Jr Harold M Jacklin Fluid heater
US2844360A (en) * 1954-01-27 1958-07-22 Sulzer Ag Heat exchanger
US2854819A (en) * 1946-01-23 1958-10-07 Power Jets Res & Dev Ltd Apparatus for igniting fuel in a fastmoving hot gas stream by means of a spontaneously ignitable pilot fuel
US2867267A (en) * 1954-02-23 1959-01-06 Gen Electric Combustion chamber
US2906094A (en) * 1954-04-14 1959-09-29 Glenn H Damon Fuel and rapid ignition apparatus for ignition of fuel in ram jets and rockets
US2914912A (en) * 1955-10-24 1959-12-01 Gen Electric Combustion system for thermal powerplant
US2930194A (en) * 1956-11-19 1960-03-29 Bendix Aviat Corp Combustor having high turbulent mixing for turbine-type starter
US2941364A (en) * 1955-04-05 1960-06-21 Armstrong Siddeley Motors Ltd Igniter chamber for a gas turbine engine
US2984979A (en) * 1951-03-27 1961-05-23 Eldon R Babcock Vortex pilot flame source for ramjet engines
US3035413A (en) * 1950-01-17 1962-05-22 Linderoth Erik Torvald Thermodynamic combustion device using pulsating gas pressure
US3048014A (en) * 1955-07-07 1962-08-07 Fritz A F Schmidt Combustion chamber for jets and similar engines
US4466250A (en) * 1981-02-03 1984-08-21 Nissan Motor Company, Limited Air passageway to air injection valve for gas turbine engine
US4838029A (en) * 1986-09-10 1989-06-13 The United States Of America As Represented By The Secretary Of The Air Force Externally vaporizing system for turbine combustor
US5127229A (en) * 1988-08-08 1992-07-07 Hitachi, Ltd. Gas turbine combustor
US5657631A (en) * 1995-03-13 1997-08-19 B.B.A. Research & Development, Inc. Injector for turbine engines
US20030177768A1 (en) * 2002-03-22 2003-09-25 Pellizzari Roberto O. Method and apparatus for generating power by combustion of vaporized fuel
US20050126624A1 (en) * 2003-12-11 2005-06-16 Chrysalis Technologies, Inc. Hybrid system for generating power
US20070180814A1 (en) * 2006-02-03 2007-08-09 General Electric Company Direct liquid fuel injection and ignition for a pulse detonation combustor
US20150285503A1 (en) * 2014-04-03 2015-10-08 General Electric Company Air fuel premixer for low emissions gas turbine combustor
US20160169160A1 (en) * 2013-10-11 2016-06-16 Kawasaki Jukogyo Kabushiki Kaisha Fuel injection device for gas turbine
US20160223201A1 (en) * 2015-01-30 2016-08-04 Delavan Inc. Fuel injectors for gas turbine engines

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE955465C (en) * 1954-09-01 1957-01-03 Daimler Benz Ag Fuel vaporizer for combustion chambers, particularly of gas turbines
DE1167594B (en) * 1960-04-25 1964-04-09 Rolls Royce Kreisringfoermige combustion chamber for gas turbine jet engines
DE1214940B (en) * 1963-03-12 1966-04-21 Licentia Gmbh Pipe-type gas turbine combustor
NL7801395A (en) * 1977-02-23 1978-08-25 Foerenade Fabriksverken Method and apparatus for burning of liquid, gaseous or pulverulent fuels.

Cited By (90)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2540991A (en) * 1942-03-06 1951-02-06 Lockheed Aircraft Corp Gas reaction aircraft power plant
US2638745A (en) * 1943-04-01 1953-05-19 Power Jets Res & Dev Ltd Gas turbine combustor having tangential air inlets for primary and secondary air
US2637974A (en) * 1944-03-16 1953-05-12 Power Jets Res & Dev Ltd Combustion apparatus for an air stream and propulsive system
US2546432A (en) * 1944-03-20 1951-03-27 Power Jets Res & Dev Ltd Apparatus for deflecting a fuel jet towards a region of turbulence in a propulsive gaseous stream
US2529506A (en) * 1944-04-15 1950-11-14 Power Jets Res & Dev Ltd Burner for liquid or gaseous fuels
US2618928A (en) * 1944-05-19 1952-11-25 Power Jets Res & Dev Ltd Combustion apparatus with vaned fuel injector means
US2612752A (en) * 1944-05-20 1952-10-07 Daniel And Florence Guggenheim Feeding apparatus, including injectors adapted to supply combustion liquids under pressure to a combustion chamber
US2579614A (en) * 1944-06-23 1951-12-25 Allis Chalmers Mfg Co Combustion chamber with rotating fuel and air stream surrounding a flame core
US2611243A (en) * 1944-09-01 1952-09-23 Lucas Ltd Joseph Combustion chamber for prime movers
US2526122A (en) * 1944-11-28 1950-10-17 Vickers Electrical Co Ltd Combustion chambers with perforated end walls and upstream fuel injection for combustion turbines
US2532831A (en) * 1945-01-27 1950-12-05 Breese Burners Inc Combustion chamber and turbine arrangement
US2658340A (en) * 1945-02-01 1953-11-10 Power Jets Res & Dev Ltd Apparatus for igniting fuel in fast-moving hot gas streams
US2623357A (en) * 1945-09-06 1952-12-30 Birmann Rudolph Gas turbine power plant having means to cool and means to compress combustion products passing through the turbine
US2581316A (en) * 1945-10-01 1952-01-01 John J Wolfersperger High rating fire-tube boiler and method of boiler operation
US2616258A (en) * 1946-01-09 1952-11-04 Bendix Aviat Corp Jet engine combustion apparatus, including pilot burner for ignition and vaporization of main fuel supply
US2854819A (en) * 1946-01-23 1958-10-07 Power Jets Res & Dev Ltd Apparatus for igniting fuel in a fastmoving hot gas stream by means of a spontaneously ignitable pilot fuel
US2540665A (en) * 1946-02-01 1951-02-06 Daniel And Florence Guggenheim Mechanism for coaxial feeding of two combustion liquids to a combustion chamber
US2581999A (en) * 1946-02-01 1952-01-08 Gen Electric Hemispherical combustion chamber end dome having cooling air deflecting means
US2560401A (en) * 1946-02-23 1951-07-10 Armstrong Siddeley Motors Ltd Liquid fuel combustion chamber for turbine units
US2509577A (en) * 1946-05-02 1950-05-30 Phillips John Multiple combustion products operated turbine
US2577918A (en) * 1946-05-08 1951-12-11 Kellogg M W Co Air jacketed combustion chamber flame tube
US2460451A (en) * 1946-06-13 1949-02-01 Farhall Inc Gasifying fuel burner
US2647369A (en) * 1946-09-06 1953-08-04 Leduc Rene Combustion chamber for fluid fuel burning in an air stream of high velocity
US2488911A (en) * 1946-11-09 1949-11-22 Surface Combustion Corp Combustion apparatus for use with turbines
US2520388A (en) * 1946-11-21 1950-08-29 Power Jets Res & Dev Ltd Apparatus for supporting combustion in fast-moving air streams
US2603064A (en) * 1946-12-12 1952-07-15 Chrysler Corp Combustion chamber with multiple conical sections providing multiple air paths for gas turbines
US2667033A (en) * 1947-01-09 1954-01-26 Power Jets Res & Dev Ltd Combustion apparatus for operation in fast-moving air streams
US2525207A (en) * 1947-01-13 1950-10-10 Lucas Ltd Joseph Ignition torch for internal-combustion prime movers
US2650753A (en) * 1947-06-11 1953-09-01 Gen Electric Turbomachine stator casing
US2540642A (en) * 1947-06-19 1951-02-06 Armstrong Siddeley Motors Ltd Multiple combustion chamber torch igniter and auxiliary fuel spray device arrangement for initiating combustion
US2522081A (en) * 1947-06-23 1950-09-12 Armstrong Siddeley Motors Ltd Combustion chamber with fuel vaporizing pipes for internal-combustion turbine plants
US2540666A (en) * 1947-06-25 1951-02-06 Daniel And Florence Guggenheim Fuel feeding and premixing apparatus for combustion chambers
US2635424A (en) * 1947-08-02 1953-04-21 Szczeniowski Boleslaw Combustor for high flow velocities
US2664702A (en) * 1947-08-11 1954-01-05 Power Jets Res & Dev Ltd Cooled flame tube
US2517822A (en) * 1947-10-23 1950-08-08 Ingersoll Rand Co Intermittent explosion gas turbine plant with dilution air
US2632296A (en) * 1947-12-06 1953-03-24 Eugene J Houdry Process of generating power involving catalytic oxidation
US2685168A (en) * 1948-01-02 1954-08-03 Phillips Petroleum Co Combustion chamber
US2560223A (en) * 1948-02-04 1951-07-10 Wright Aeronautical Corp Double air-swirl baffle construction for fuel burners
US2560207A (en) * 1948-02-04 1951-07-10 Wright Aeronautical Corp Annular combustion chamber with circumferentially spaced double air-swirl burners
US2632994A (en) * 1948-04-05 1953-03-31 Mcdonnell Aircraft Corp Ram jet engine and flame holder therefor
US2625011A (en) * 1948-07-31 1953-01-13 Armstrong Siddeley Motors Ltd Igniter for liquid fuel combustion chambers
US2654996A (en) * 1948-10-26 1953-10-13 Oerlikon Maschf Gas turbine combustion chamber
US2541900A (en) * 1948-12-24 1951-02-13 A V Roe Canada Ltd Multiple fuel jet burner and torch igniter unit with fuel vaporizing tubes
US2648951A (en) * 1949-03-31 1953-08-18 Gen Motors Corp Combustor igniter cup which becomes incandescent from combustion therein
US2673445A (en) * 1949-06-21 1954-03-30 Bruno W Bruckmann Turbojet and rocket motor combination with hot gas ignition system for nonself-reaction rocket fuels
US2664703A (en) * 1949-06-28 1954-01-05 A V Roe Canada Ltd Preheater and vaporizer for gas turbine engines
US2648950A (en) * 1949-08-24 1953-08-18 Westinghouse Electric Corp Gas turbine engine apparatus designed to burn wet pulverized fuel
US2635421A (en) * 1949-10-24 1953-04-21 Felix A Blum Pulse jet convertible to ram jetpropulsion means
US3035413A (en) * 1950-01-17 1962-05-22 Linderoth Erik Torvald Thermodynamic combustion device using pulsating gas pressure
US2827759A (en) * 1950-01-18 1958-03-25 Bruno W Bruckmann Gas turbine aricraft power plant having a contraflow air-fuel combustion system
US2773350A (en) * 1950-01-31 1956-12-11 Hillard E Barrett Combustion chamber assembly for ram jet fuel burner
US2697910A (en) * 1950-07-29 1954-12-28 Thermal Res And Engineering Co Fluid fuel burner with self-contained fuel vaporizing unit
US2720754A (en) * 1950-09-29 1955-10-18 Mcdonnell Aircraft Corp Flameholder for ram jet engine
US2798360A (en) * 1950-10-06 1957-07-09 Gen Motors Corp Ducted fan type jet propulsion engine
US2672729A (en) * 1950-10-28 1954-03-23 Boeing Co Spark plug
US2648197A (en) * 1951-01-06 1953-08-11 A V Roe Canada Ltd Vaporizer tube system
US2768497A (en) * 1951-02-03 1956-10-30 Gen Motors Corp Combustion chamber with swirler
US2694444A (en) * 1951-03-17 1954-11-16 American Mach & Foundry Jet-type burner for tobacco curers
US2984979A (en) * 1951-03-27 1961-05-23 Eldon R Babcock Vortex pilot flame source for ramjet engines
US2780062A (en) * 1951-04-03 1957-02-05 Curtiss Wright Corp Jet engine burner construction
US2722803A (en) * 1951-05-23 1955-11-08 Gen Electric Cooling means for combustion chamber cross ignition tubes
US2672727A (en) * 1951-05-31 1954-03-23 Westinghouse Electric Corp Fuel vaporizer system for combustion chambers
US2727358A (en) * 1952-03-27 1955-12-20 A V Roe Canada Ltd Reverse-flow vaporizer with single inlet and plural outlets
US2839048A (en) * 1952-09-08 1958-06-17 Jr Harold M Jacklin Fluid heater
US2775238A (en) * 1953-01-29 1956-12-25 Surface Combustion Corp Fuel burning and air heating apparatus
US2807316A (en) * 1953-06-11 1957-09-24 Lucas Industries Ltd Liquid fuel combustion chambers for jet-propulsion engines, gas turbines, or other purposes
US2844360A (en) * 1954-01-27 1958-07-22 Sulzer Ag Heat exchanger
US2867267A (en) * 1954-02-23 1959-01-06 Gen Electric Combustion chamber
US2906094A (en) * 1954-04-14 1959-09-29 Glenn H Damon Fuel and rapid ignition apparatus for ignition of fuel in ram jets and rockets
US2800768A (en) * 1954-08-19 1957-07-30 United Aircraft Corp Burner construction
US2941364A (en) * 1955-04-05 1960-06-21 Armstrong Siddeley Motors Ltd Igniter chamber for a gas turbine engine
US3048014A (en) * 1955-07-07 1962-08-07 Fritz A F Schmidt Combustion chamber for jets and similar engines
US2914912A (en) * 1955-10-24 1959-12-01 Gen Electric Combustion system for thermal powerplant
US2930194A (en) * 1956-11-19 1960-03-29 Bendix Aviat Corp Combustor having high turbulent mixing for turbine-type starter
US4466250A (en) * 1981-02-03 1984-08-21 Nissan Motor Company, Limited Air passageway to air injection valve for gas turbine engine
US4838029A (en) * 1986-09-10 1989-06-13 The United States Of America As Represented By The Secretary Of The Air Force Externally vaporizing system for turbine combustor
US5127229A (en) * 1988-08-08 1992-07-07 Hitachi, Ltd. Gas turbine combustor
US5657631A (en) * 1995-03-13 1997-08-19 B.B.A. Research & Development, Inc. Injector for turbine engines
WO1998040614A1 (en) * 1995-03-13 1998-09-17 B.B.A. Research & Development, Inc. Injector for turbine engines
US20030177768A1 (en) * 2002-03-22 2003-09-25 Pellizzari Roberto O. Method and apparatus for generating power by combustion of vaporized fuel
US7313916B2 (en) * 2002-03-22 2008-01-01 Philip Morris Usa Inc. Method and apparatus for generating power by combustion of vaporized fuel
US20050126624A1 (en) * 2003-12-11 2005-06-16 Chrysalis Technologies, Inc. Hybrid system for generating power
US8502064B2 (en) 2003-12-11 2013-08-06 Philip Morris Usa Inc. Hybrid system for generating power
US20070180814A1 (en) * 2006-02-03 2007-08-09 General Electric Company Direct liquid fuel injection and ignition for a pulse detonation combustor
US10330050B2 (en) * 2013-10-11 2019-06-25 Kawasaki Jukogyo Kabushiki Kaisha Fuel injection device for gas turbine
US20160169160A1 (en) * 2013-10-11 2016-06-16 Kawasaki Jukogyo Kabushiki Kaisha Fuel injection device for gas turbine
US20150285503A1 (en) * 2014-04-03 2015-10-08 General Electric Company Air fuel premixer for low emissions gas turbine combustor
US9534788B2 (en) * 2014-04-03 2017-01-03 General Electric Company Air fuel premixer for low emissions gas turbine combustor
US20160223201A1 (en) * 2015-01-30 2016-08-04 Delavan Inc. Fuel injectors for gas turbine engines
US9765972B2 (en) * 2015-01-30 2017-09-19 Delavan Inc. Fuel injectors for gas turbine engines

Also Published As

Publication number Publication date
NL82403C (en)
DE951062C (en) 1956-10-18
NL70682C (en)
FR916262A (en) 1946-12-02
CH258412A (en) 1948-11-30
BE460697A (en)
GB577972A (en) 1941-07-26

Similar Documents

Publication Publication Date Title
RU2627759C2 (en) Consequent burning with the dilution gas mixer
CN103322592B (en) Micromixer combustion head end component
CN102330978B (en) Flame tolerant secondary fuel nozzle
US3899882A (en) Gas turbine combustor basket cooling
KR100354306B1 (en) Gas turbine
US4963089A (en) High turndown burner with integral pilot
US3811278A (en) Fuel injection apparatus
EP2589877B1 (en) Annular combustor with multipoint fuel injection arrangements
US3724207A (en) Combustion apparatus
US2635426A (en) Annular vaporizer
US3099134A (en) Combustion chambers
US2794319A (en) Afterburner shell construction
AU2002240309B2 (en) Gas pipe ignitor
US2398654A (en) Combustion burner
US3691765A (en) Fuel injector for a gas turbine engine
JP5468812B2 (en) Combustor assembly and fuel nozzle for gas turbine engine
CN101509670B (en) Fuel nozzle for a gas turbine engine and method for fabricating the same
JP5960969B2 (en) Apparatus and method for ignition combustion of a combustor
DE102014102780A1 (en) System and method for air flow conditioning at a rape level
US5802854A (en) Gas turbine multi-stage combustion system
US2601000A (en) Combustor for thermal power plants having toroidal flow path in primary mixing zone
US2602292A (en) Fuel-air mixing device
US2856755A (en) Combustion chamber with diverse combustion and diluent air paths
US7661269B2 (en) Gas turbine burner
US2621477A (en) Combustion apparatus having valve controlled passages for preheating the fuel-air mixture