US2404335A - Liquid fuel burner, vaporizer, and combustion engine - Google Patents
Liquid fuel burner, vaporizer, and combustion engine Download PDFInfo
- 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
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- air
- combustion
- flame
- vaporizer
- liquid fuel
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Classifications
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- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
- F23R3/48—Flame tube interconnectors, e.g. cross-over tubes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- 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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
- F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
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- 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
Definitions
- This invention relates to liquid fuel burners and vaporizers and to combustion engines or systems employing the same.
- 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,
- 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,
- 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.
- 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.
- 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.
- 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.
- 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.
- 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.
- a pilot jet 5 which is an atomising spray jet
- 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 bave 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.
- 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.
- 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.
- the secondary air if properly admitted, speeds up combustion and shortens the flame.
- 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
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;
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB258412X | 1939-12-09 |
Publications (1)
Publication Number | Publication Date |
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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 |
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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)
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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 |
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 |
US2540991A (en) * | 1942-03-06 | 1951-02-06 | Lockheed Aircraft Corp | Gas reaction aircraft power plant |
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 |
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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 |
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US2664703A (en) * | 1949-06-28 | 1954-01-05 | A V Roe Canada Ltd | Preheater and vaporizer for gas turbine engines |
US2667033A (en) * | 1947-01-09 | 1954-01-26 | Power Jets Res & Dev Ltd | Combustion apparatus for operation in fast-moving air streams |
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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 |
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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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE955465C (en) * | 1954-09-01 | 1957-01-03 | Daimler Benz Ag | Fuel evaporator for combustion chambers, especially of gas turbines |
DE1167594B (en) * | 1960-04-25 | 1964-04-09 | Rolls Royce | Annular combustion chamber for gas turbine jet engines |
DE1214940B (en) * | 1963-03-12 | 1966-04-21 | Licentia Gmbh | Tubular gas turbine combustor |
NL7801395A (en) * | 1977-02-23 | 1978-08-25 | Foerenade Fabriksverken | METHOD AND DEVICE FOR THE COMBUSTION OF LIQUID, GAS OR POWDER FUELS. |
-
0
- NL NL82403D patent/NL82403C/xx active
- BE BE460697D patent/BE460697A/xx unknown
- NL NL70682D patent/NL70682C/xx active
-
1939
- 1939-12-09 GB GB31884/39A patent/GB577972A/en not_active Expired
-
1941
- 1941-02-19 US US379735A patent/US2404335A/en not_active Expired - Lifetime
-
1945
- 1945-09-15 FR FR916262D patent/FR916262A/en not_active Expired
- 1945-10-06 CH CH258412D patent/CH258412A/en unknown
-
1950
- 1950-09-26 DE DEP7269A patent/DE951062C/en not_active Expired
Cited By (90)
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 |
WO1998040614A1 (en) * | 1995-03-13 | 1998-09-17 | B.B.A. Research & Development, Inc. | Injector for turbine engines |
US5657631A (en) * | 1995-03-13 | 1997-08-19 | B.B.A. Research & Development, Inc. | Injector for turbine engines |
US7313916B2 (en) * | 2002-03-22 | 2008-01-01 | Philip Morris Usa Inc. | Method and apparatus for generating power by combustion of vaporized fuel |
US20030177768A1 (en) * | 2002-03-22 | 2003-09-25 | Pellizzari Roberto O. | Method and apparatus for generating power by combustion of vaporized fuel |
US8502064B2 (en) | 2003-12-11 | 2013-08-06 | Philip Morris Usa Inc. | Hybrid system for generating power |
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 |
US20160169160A1 (en) * | 2013-10-11 | 2016-06-16 | Kawasaki Jukogyo Kabushiki Kaisha | Fuel injection device for gas turbine |
US10330050B2 (en) * | 2013-10-11 | 2019-06-25 | 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) | |
BE460697A (en) | |
FR916262A (en) | 1946-12-02 |
NL70682C (en) | |
CH258412A (en) | 1948-11-30 |
GB577972A (en) | 1941-07-26 |
DE951062C (en) | 1956-10-18 |
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