US3886736A - Combustion apparatus for gas turbine - Google Patents

Combustion apparatus for gas turbine Download PDF

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US3886736A
US3886736A US411497A US41149773A US3886736A US 3886736 A US3886736 A US 3886736A US 411497 A US411497 A US 411497A US 41149773 A US41149773 A US 41149773A US 3886736 A US3886736 A US 3886736A
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chamber
array
fuel
disposed
ports
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US411497A
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Katsuyuki Kawaguchi
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CBS Corp
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Westinghouse Electric Corp
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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

Definitions

  • ABSTRACT [30] Foreign Applicatlon Priority Data Nov. 9. m2 Japan 47-l1l6l9
  • a gas turbine having a Combustion Chamber with fuel nozzle is encompassed by a plurality of annular 52 us. Cl 60/3974 R; 239/400; 239/402; P m Chambers which are pp ith a pr 239/4O6 1zed fluid. The fluid is directed obliquely through ports 51 Int. Cl. 3051) 7/10; FOZc 3/00 f a fuel Stream being p y into the combus- 5 n w f Search 60/3974 R 3974 13; tion chamber.
  • the fluid also adds to the turbulence within the fuel vortex to reduce the [56] References Cited carbon pollutant outflow.
  • This invention relates to combustion apparatus for a gas turbine, and more particularly to means for mixing fluid streams with the fuel to atomize. disperse or convolute the fuel to provide complete combustion thereof.
  • a combustion apparatus for a gas turbine when made in accordance with this invention, cornprises a fuel supply conduit having a pore in fluid communication with a combustion chamber to direct the flow of fuel to the combustion chamber, an atomizing fluid chamber having an opening disposed to direct atomizing fluid to converge with the fluid flowing into the combustion chamber, an annular chamber disposed to encircle the fuel supply conduit having one end thereof in communication with the combustion chamber, the other end being in communication with the compressor portion of the gas turbine, the annular chamber having a plurality of angularly directed vanes so disposed therein to cause air flowing therethrough to follow a vortecular path as it leaves the exit end of the annular chamber and enters the combustion chamber, and generally radially inwardly disposed and generally radially outwardly disposed angularly directed annular array of ports, through which air is passed, which aid the vortecular motion and inner turbulence of the fuel-air mixture in the combustion chamber.
  • FIG. 2 is a view taken along lines ll-ll of FIG. 1;
  • FIG. 3 is a view taken along lines Illlll of FIG. 2.
  • FIG. 1 wherein there is shown a combustion apparatus 10 for a gas turbine, not shown, having a combustion chamber 12, a compressor 13, to supply pressurized air for combustion, and a supply conduit 14 to supply atomizing fluid to atomize the fuel.
  • a fuel supply conduit 16 delivers fuel to a fuel supply nozzle 18 which has at least one pore or opening 19 from which fuel is sprayed into the combustion chamber 12.
  • An outer plenum chamber 20 encircles the combustion apparatus 10 and it is in communication with an air source through a plurality of ports 22 disposed in a cylindrical outer wall 24 of the plenum chamber 20.
  • a plurality of angularly directed vanes 26 are fastened to and extend generally radially outward from an inner cylindrical wall 28 of the plenum chamber 20. The angularly directed vanes 26 are adapted to cause the air flowing through the plenum chamber 20 to follow a convolute path, directed at an angle of 30 to to axis of the combustion chamber 12, as it enters that combustion chamber.
  • a frustoconical baffle 30 has its small diameter end fastened to the inner wall 28 of the plenum chamber 20 and has a plurality of annularly disposed ports of jets 32 angularly directed to 30 to 35 from the axis of the combustion chamber 12.
  • the vanes 26 and the ports 32 both direct their respective air flows generally parallel to one another. Each air flow adds to and combines with the vortecular motion of the atomizing fuel spray.
  • the jets 32 may also direct their air flows normal to the fuel-air vortex to increase the turbulence and fuel-air mixing therein.
  • An inner plenum chamber 34 is provided adjacent the fuel nozzle 18 and is supplied with atomizing fluid through the atomizing conduit 14.
  • the atomizing fluid flows through an annular opening 36 adjacent the tip of the nozzle 18 and is directed at an angle toward the fuel converging with the fuel flowing into the combustion chamber.
  • An intermediate plenum chamber 38 is formed between the inner and outer annular chambers, 34 and 20, respectively, and a plurality of ports 40 are disposed in the inner wall 28 of the outer plenum chamber 20.
  • the intermediate annular plenum chamber 38 is in fluid communication with the combustion chamber 12 by a plurality of angularly disposed ports or jets 42, which may be directed at at angle of 30 to with respect to the axis of the combustion chamber. the air flow therethrough being generally parallel to that vortecular air flow pattern caused by the vanes 26 and the outer array of ports 32.
  • the array of vanes 26 and the angular arrays of inner and outer ports, 42, and 32, are shown in FIG. 2.
  • the object of this invention is to provide a combustion apparatus in which the carbon that is produced in an initial combustion zone is decreased by supplying vortex air in three steps so as widen the angle of the fuel injection cone, thereby making the fuel particle size smaller, effectively improving the ignitability of the fuel and finally shortening the length of the flame.
  • the atomization of the fuel is increased by the application ofa swirl flow having the same vortex direction as that of the fuel injection cone. Additionally. the jetted air penetrates the fuel injection cone to provide internal turbulence and mixing thereof.
  • a pressure balance piston 44 admits additional air from the combustion air source. which may be a compressor, as shown in FIG.
  • a combustion apparatus for a gas turbine having a combustion chamber, a fuel supply. a compressor to supply a pressurized air for combustion, a supply of pressurized atomizing fluid to atomize the fuel, said combustion apparatus comprising:
  • a fuel supply nozzle having at least one port in com munication with said combustion chamber and disposed to direct the flow of fuel to said combustion chamber;
  • an atomizing fluid chamber having walls which define at least one duct disposed to direct atomizing fluid into said combustion chamber so that it converges with fuel flowing thereto;
  • a plenum chamber comprised of walls disposed about said atomizing fluid chamber
  • a first array of angularly arranged ports disposed through said wall of said plenum chamber and disposed about said fuel nozzle, said first array of angularly arranged ports providing jets of air to promote vortecular motion to the fuel in said combustion chamber;
  • a frustoconical baffle having its small diameter edge attached to said walls of said plenum chamber, said baffle being annularly disposed about said nozzle; a second array of angularly arranged ports disposed through said baffle about said fuel nozzle, said second array of angularly arranged ports providing jets of air to promote mixing and increase vortecular motion of the combustion components; an arcuate chamber disposed radially outwardly of said plenum chamber.
  • said arcuate chamber having walls with inlet ports therethrough, said arcuate chamber being in communication with said compressor and said combustion chamber, and a generally radially extending array of vanes disposed across said arcuate chamber for causing the air passing therethrough to have a vortecular motion as it enters the combustion chamber; said first and second arrays of ports and said array of vanes each directing generally the same angle to the fluid passing thereby, with respect to the axis of the combustion chamber;
  • said array of vanes and said first and Second arrays of ports being arranged as to cause the air and fuel to follow a vortecular motion, and to increase the turbulence therein, thereby reducing the smoke generated therewith.
  • combustion apparatus as recited in claim 1, wh erein said first array of ports have an angle betwee 3Q to 45 with the axis of the combustion chamber, said second array of ports having an angle of 30 to 35 with the axis of the combustion chamber, and said array of vanes having an angle of between 30 to 35 with the axis of the combustion chamber.
  • said first array of ports is disposed in an angular array about the downstream end of the fuel nozzle, and said second array of ports are disposed radially outwardly of the said first array of ports.
  • combustion apparatus as recited in claim 1, wherein said second array of ports is directed generally normal to the fuel vortex, the air passing through said second array of ports promoting turbulence and mixing of the'fuel and air within the center of said vortex, thereby reducing carbon and smoke production from the combustion chamber.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Air Supply (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

A gas turbine having a combustion chamber with a fuel nozzle is encompassed by a plurality of annular plenum chambers which are supplied with a pressurized fluid. The fluid is directed obliquely through ports toward a fuel stream being sprayed into the combustion chamber. The angle at which the fluid is directed aids in the formation of a vortex. The fluid also adds to the turbulence within the fuel vortex to reduce the carbon pollutant outflow.

Description

United States Patent 1 1 [111 3,886,736 Kawaguchi June 3, 1975 l l COMBUSTlON APPARATUS FOR GAS 3.684.186 8/1972 Helmrich 239/400 3.700,l73 10/1972 Kctchum.... 239/405 1 3.731169 5/1973 Lefebvrew 239/405 X [75] Inventor: Katsuyuki Kawaguchi. Akzishi. 3,735.930 5/1973 Mori 239/406 X Japan 3.777.983 12/1973 l-libbins 60/3974 B [73] Assignee: Westinghouse Electric Corporation.
Pittsburgh. Pa. Primary Eraminer-C. J. Husar Ass-[slant Examiner-Robert E. Garrett [22 Filed 1973 Attorney. Agent, or FirmG. H. Telfer [21] Appl. No: 411,497
[57] ABSTRACT [30] Foreign Applicatlon Priority Data Nov. 9. m2 Japan 47-l1l6l9 A gas turbine having a Combustion Chamber with fuel nozzle is encompassed by a plurality of annular 52 us. Cl 60/3974 R; 239/400; 239/402; P m Chambers which are pp ith a pr 239/4O6 1zed fluid. The fluid is directed obliquely through ports 51 Int. Cl. 3051) 7/10; FOZc 3/00 f a fuel Stream being p y into the combus- 5 n w f Search 60/3974 R 3974 13; tion chamber. The angle at which the fluid is directed 239/400, 403-406, 4245 ands 1n the formation of a vortex. The fluid also adds to the turbulence within the fuel vortex to reduce the [56] References Cited carbon pollutant outflow.
LNITED STATES PATENTS 4 Claims, 3 Drawing Figures 3.498 055 3/1970 Fuituni et ul. 60/3974 R 1 COMBUSTION APPARATUS FOR GAS TURBINE CROSS REFERENCES TO RELATED APPLICATIONS This invention is based on an application filed by the same inventor in Japan. The Japanese application number and its filing date is as follows:
111619/72 filed Nov. 9, 1972.
BACKGROUND OF THE INVENTION l. Field of the Invention:
This invention relates to combustion apparatus for a gas turbine, and more particularly to means for mixing fluid streams with the fuel to atomize. disperse or convolute the fuel to provide complete combustion thereof.
2. Prior Art:
Early arrangements of baffling and mixing of atomizing fluids and fuels have generally been concerned with increasing the thermal combustion efficiency and optimizing the temperature distribution of the products of combustion to eliminate hot spots and prevent burnout of the components in the flow path of the products of the combustion. However, with the increased interest in ecology, interest has been generated in providing a thorough mixing of the fuel and an abatement of the production of smoke and obnoxious nitrogen-oxygen compounds produced by the combustion of fuel in the gas turbine. An earlier application filed in the name of this inventor showing some prior art is US. Pat. No. 3,768,250.
SUMMARY OF THE INVENTION In general, a combustion apparatus for a gas turbine, when made in accordance with this invention, cornprises a fuel supply conduit having a pore in fluid communication with a combustion chamber to direct the flow of fuel to the combustion chamber, an atomizing fluid chamber having an opening disposed to direct atomizing fluid to converge with the fluid flowing into the combustion chamber, an annular chamber disposed to encircle the fuel supply conduit having one end thereof in communication with the combustion chamber, the other end being in communication with the compressor portion of the gas turbine, the annular chamber having a plurality of angularly directed vanes so disposed therein to cause air flowing therethrough to follow a vortecular path as it leaves the exit end of the annular chamber and enters the combustion chamber, and generally radially inwardly disposed and generally radially outwardly disposed angularly directed annular array of ports, through which air is passed, which aid the vortecular motion and inner turbulence of the fuel-air mixture in the combustion chamber. Each of the annular arrays of ports and the vanes direct their respective air flows generally parallel to one another, while also contributing to the generally overall convolute flow pattern.
BRIEF DESCRIPTION OF THE DRAWING];
I he objects and advantages of the invention will be come more apparent from reading the following detailed description in connection with the accompany ng FIG. 2 is a view taken along lines ll-ll of FIG. 1; and,
FIG. 3 is a view taken along lines Illlll of FIG. 2.
BRIEF DESCRIPTION OF THE PREFERRED EMBODIMENTS Referring now to the drawings in detail, and more particularly to FIG. 1, wherein there is shown a combustion apparatus 10 for a gas turbine, not shown, having a combustion chamber 12, a compressor 13, to supply pressurized air for combustion, and a supply conduit 14 to supply atomizing fluid to atomize the fuel.
A fuel supply conduit 16 delivers fuel to a fuel supply nozzle 18 which has at least one pore or opening 19 from which fuel is sprayed into the combustion chamber 12. An outer plenum chamber 20 encircles the combustion apparatus 10 and it is in communication with an air source through a plurality of ports 22 disposed in a cylindrical outer wall 24 of the plenum chamber 20. A plurality of angularly directed vanes 26 are fastened to and extend generally radially outward from an inner cylindrical wall 28 of the plenum chamber 20. The angularly directed vanes 26 are adapted to cause the air flowing through the plenum chamber 20 to follow a convolute path, directed at an angle of 30 to to axis of the combustion chamber 12, as it enters that combustion chamber. A frustoconical baffle 30 has its small diameter end fastened to the inner wall 28 of the plenum chamber 20 and has a plurality of annularly disposed ports of jets 32 angularly directed to 30 to 35 from the axis of the combustion chamber 12. The vanes 26 and the ports 32 both direct their respective air flows generally parallel to one another. Each air flow adds to and combines with the vortecular motion of the atomizing fuel spray. The jets 32 may also direct their air flows normal to the fuel-air vortex to increase the turbulence and fuel-air mixing therein.
An inner plenum chamber 34 is provided adjacent the fuel nozzle 18 and is supplied with atomizing fluid through the atomizing conduit 14. The atomizing fluid flows through an annular opening 36 adjacent the tip of the nozzle 18 and is directed at an angle toward the fuel converging with the fuel flowing into the combustion chamber.
An intermediate plenum chamber 38 is formed between the inner and outer annular chambers, 34 and 20, respectively, and a plurality of ports 40 are disposed in the inner wall 28 of the outer plenum chamber 20. The intermediate annular plenum chamber 38 is in fluid communication with the combustion chamber 12 by a plurality of angularly disposed ports or jets 42, which may be directed at at angle of 30 to with respect to the axis of the combustion chamber. the air flow therethrough being generally parallel to that vortecular air flow pattern caused by the vanes 26 and the outer array of ports 32.
The array of vanes 26 and the angular arrays of inner and outer ports, 42, and 32, are shown in FIG. 2.
The angularity of the vanes 26 and the outer ports 32 are shown in FIG, 3. The object of this invention is to provide a combustion apparatus in which the carbon that is produced in an initial combustion zone is decreased by supplying vortex air in three steps so as widen the angle of the fuel injection cone, thereby making the fuel particle size smaller, effectively improving the ignitability of the fuel and finally shortening the length of the flame. The atomization of the fuel is increased by the application ofa swirl flow having the same vortex direction as that of the fuel injection cone. Additionally. the jetted air penetrates the fuel injection cone to provide internal turbulence and mixing thereof. As the combustion pressure increases during combustion operation, a pressure balance piston 44 admits additional air from the combustion air source. which may be a compressor, as shown in FIG. I, the air being passed through an annular chamber 46 disposed about the fuel supply conduit, to mix with the air in the intermediate annular chamber 38 prior to injection into the combustion chamber 12. The air from the outer annular array of ports 32 passes into the fuel injection Cone without contracting the injection cone because the air flow has its own vortecular components, and the conical angle of the vortex is increased by the air flow from the inner annular array of ports 42. The mixing of fresh air with the circulating combustible fuel gas flow can be achieved quickly, and the combustion load factor can be increased to the state in which a stable combustion zone and fuel air ratio is effectively and highly maintained. Thus the mixture of air and fuel is sufficiently promoted and the carbon output due to incomplete combustion is reduced.
I claim:
1. A combustion apparatus for a gas turbine having a combustion chamber, a fuel supply. a compressor to supply a pressurized air for combustion, a supply of pressurized atomizing fluid to atomize the fuel, said combustion apparatus comprising:
a fuel supply nozzle having at least one port in com munication with said combustion chamber and disposed to direct the flow of fuel to said combustion chamber;
an atomizing fluid chamber having walls which define at least one duct disposed to direct atomizing fluid into said combustion chamber so that it converges with fuel flowing thereto;
a plenum chamber comprised of walls disposed about said atomizing fluid chamber;
a first array of angularly arranged ports disposed through said wall of said plenum chamber and disposed about said fuel nozzle, said first array of angularly arranged ports providing jets of air to promote vortecular motion to the fuel in said combustion chamber;
a frustoconical baffle having its small diameter edge attached to said walls of said plenum chamber, said baffle being annularly disposed about said nozzle; a second array of angularly arranged ports disposed through said baffle about said fuel nozzle, said second array of angularly arranged ports providing jets of air to promote mixing and increase vortecular motion of the combustion components; an arcuate chamber disposed radially outwardly of said plenum chamber. said arcuate chamber having walls with inlet ports therethrough, said arcuate chamber being in communication with said compressor and said combustion chamber, and a generally radially extending array of vanes disposed across said arcuate chamber for causing the air passing therethrough to have a vortecular motion as it enters the combustion chamber; said first and second arrays of ports and said array of vanes each directing generally the same angle to the fluid passing thereby, with respect to the axis of the combustion chamber;
said array of vanes and said first and Second arrays of ports being arranged as to cause the air and fuel to follow a vortecular motion, and to increase the turbulence therein, thereby reducing the smoke generated therewith.
2. combustion apparatus as recited in claim 1, wh erein said first array of ports have an angle betwee 3Q to 45 with the axis of the combustion chamber, said second array of ports having an angle of 30 to 35 with the axis of the combustion chamber, and said array of vanes having an angle of between 30 to 35 with the axis of the combustion chamber.
combustion apparatus as recited in claim 1, wherein said first array of ports is disposed in an angular array about the downstream end of the fuel nozzle, and said second array of ports are disposed radially outwardly of the said first array of ports.
combustion apparatus as recited in claim 1, wherein said second array of ports is directed generally normal to the fuel vortex, the air passing through said second array of ports promoting turbulence and mixing of the'fuel and air within the center of said vortex, thereby reducing carbon and smoke production from the combustion chamber.

Claims (4)

1. A combustion apparatus for a gas turbine having a combustion chamber, a fuel supply, a compressor to supply a pressurized air for combustion, a supply of pressurized atomizing fluid to atomize the fuel, said combustion apparatus comprising: a fuel supply nozzle having at least one port in communication with said combustion chamber and disposed to direct the flow of fuel to said combustion chamber; an atomizing fluid chamber having walls which define at least one duct disposed to direct atomizing fluid into said combustion chamber so that it converges with fuel flowing thereto; a plenum chamber comprised of walls disposed about said atomizing fluid chamber; a first array of angularly arranged ports disposed through said wall of said plenum chamber and disposed about said fuel nozzle, said first array of angularly arranged ports providing jets of air to promote vortecular motion to the fuel in said combustion chamber; a frustoconical baffle having its small diameter edge attached to said walls of said plenum chamber, said baffle being annularly disposed about said nozzle; a second array of angularly arranged ports disposed through said baffle about said fuel nozzle, said second array of angularly arranged ports providing jets of air to promote mixing and increase vortecular motion of the combustion components; an arcuate chamber disposed radially outwardly of said plenum chamber, said arcuate chamber having walls with inlet ports therethrough, said arcuate chamber being in communication with said compressor and said combustion chamber, and a generally radially extending array of vanes disposed across said arcuate chamber for causing the air passing therethrough to have a vortecular motion as it enters the combustion chamber; said first and second arrays of ports and said array of vanes each directing generally the same angle to the fluid passing thereby, with respect to the axis of the combustion chamber; said array of vanes and said first and second arrays of ports being arranged as to cause the air and fuel to follow a vortecular motion, and to increase the turbulence therein, thereby reducing the smoke generated therewith.
1. A combustion apparatus for a gas turbine having a combustion chamber, a fuel supply, a compressor to supply a pressurized air for combustion, a supply of pressurized atomizing fluid to atomize the fuel, said combustion apparatus comprising: a fuel supply nozzle having at least one port in communication with said combustion chamber and disposed to direct the flow of fuel to said combustion chamber; an atomizing fluid chamber having walls which define at least one duct disposed to direct atomizing fluid into said combustion chamber so that it converges with fuel flowing thereto; a plenum chamber comprised of walls disposed about said atomizing fluid chamber; a first array of angularly arranged ports disposed through said wall of said plenum chamber and disposed about said fuel nozzle, said first array of angularly arranged ports providing jets of air to promote vortecular motion to the fuel in said combustion chamber; a frustoconical baffle having its small diameter edge attached to said walls of said plenum chamber, said baffle being annularly disposed about said nozzle; a second array of angularly arranged ports disposed through said baffle about said fuel nozzle, said second array of angularly arranged ports providing jets of air to promote mixing and increase vortecular motion of the combustion components; an arcuate chamber disposed radially outwardly of said plenum chamber, said arcuate chamber having walls with inlet ports therethrough, said arcuate chamber being in communication with said compressor and said combustion chamber, and a generally radially extending array of vanes disposed across said arcuate chamber for causing the air passing therethrough to have a vortecular motion as it enters the combustion chamber; said first and second arrays of ports and said array of vanes each directing generally the same angle to the fluid passing thereby, with respect to the axis of the combustion chamber; said array of vanes and said first and second arrays of ports being arranged as to cause the air and fuel to follow a vortecular motion, and to increase the turbulence therein, thereby reducing the smoke generated therewith.
2. A combustion apparatus as recited in claim 1, wherein said first array of ports have an angle betwee 30* to 45* with the axis of the combustion chamber, said second array of ports having an angle of 30* to 35* with the axis of the combustion chamber, and said array of vanes having an angle of between 30* to 35* with the axis of the combustion chamber.
3. A combustion apparatus as recited in claim 1, wherein said first array of ports is disposed in an angular array about the downstream end of the fuel nozzle, and said second array of ports are disposed radially outwardly of the said first array of ports.
US411497A 1972-11-09 1973-10-31 Combustion apparatus for gas turbine Expired - Lifetime US3886736A (en)

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US6550696B2 (en) 2000-02-28 2003-04-22 Adel B. Mansour Integrated fuel injection and mixing system with impingement cooling face
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US20100132364A1 (en) * 2008-12-01 2010-06-03 Myers Geoffrey D Fuel nozzle detachable burner tube
US20140060059A1 (en) * 2012-09-06 2014-03-06 United Technologies Corporation Fuel delivery system with a cavity coupled fuel injector
US20140246518A1 (en) * 2013-03-01 2014-09-04 Delavan Inc Fuel nozzle with discrete jet inner air swirler
US8893500B2 (en) 2011-05-18 2014-11-25 Solar Turbines Inc. Lean direct fuel injector
US8919132B2 (en) 2011-05-18 2014-12-30 Solar Turbines Inc. Method of operating a gas turbine engine
US9182124B2 (en) 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same
US11421883B2 (en) 2020-09-11 2022-08-23 Raytheon Technologies Corporation Fuel injector assembly with a helical swirler passage for a turbine engine
US11649964B2 (en) 2020-12-01 2023-05-16 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US11754287B2 (en) 2020-09-11 2023-09-12 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US11808455B2 (en) 2021-11-24 2023-11-07 Rtx Corporation Gas turbine engine combustor with integral fuel conduit(s)
US11846249B1 (en) 2022-09-02 2023-12-19 Rtx Corporation Gas turbine engine with integral bypass duct
US12116934B2 (en) 2023-02-10 2024-10-15 Rtx Corporation Turbine engine fuel injector with oxygen circuit

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US5813232A (en) * 1995-06-05 1998-09-29 Allison Engine Company, Inc. Dry low emission combustor for gas turbine engines
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US4395874A (en) * 1980-12-02 1983-08-02 United Technologies Corporation Fuel nozzles with water injection for gas turbine engines
US4863105A (en) * 1985-02-13 1989-09-05 Westinghouse Electric Corp. High reliability fuel oil nozzle for a gas turbine
US4996837A (en) * 1987-12-28 1991-03-05 Sundstrand Corporation Gas turbine with forced vortex fuel injection
US5040371A (en) * 1988-12-12 1991-08-20 Sundstrand Corporation Fuel injectors for use with combustors
US5224333A (en) * 1990-03-13 1993-07-06 Delavan Inc Simplex airblast fuel injection
US5115634A (en) * 1990-03-13 1992-05-26 Delavan Inc. Simplex airblade fuel injection method
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US5309709A (en) * 1992-06-25 1994-05-10 Solar Turbines Incorporated Low emission combustion system for a gas turbine engine
US5288021A (en) * 1992-08-03 1994-02-22 Solar Turbines Incorporated Injection nozzle tip cooling
US5467926A (en) * 1994-02-10 1995-11-21 Solar Turbines Incorporated Injector having low tip temperature
US5873237A (en) * 1997-01-24 1999-02-23 Westinghouse Electric Corporation Atomizing dual fuel nozzle for a combustion turbine
US6082113A (en) * 1998-05-22 2000-07-04 Pratt & Whitney Canada Corp. Gas turbine fuel injector
US6289676B1 (en) 1998-06-26 2001-09-18 Pratt & Whitney Canada Corp. Simplex and duplex injector having primary and secondary annular lud channels and primary and secondary lud nozzles
US7083122B2 (en) 2000-02-28 2006-08-01 Parker-Hannifin Corporation Integrated fluid injection air mixing system
US20030155325A1 (en) * 2000-02-28 2003-08-21 Mansour Adel B. Integrated fluid injection air mixing system
US6533954B2 (en) 2000-02-28 2003-03-18 Parker-Hannifin Corporation Integrated fluid injection air mixing system
US6550696B2 (en) 2000-02-28 2003-04-22 Adel B. Mansour Integrated fuel injection and mixing system with impingement cooling face
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EP2003398A3 (en) * 2007-06-14 2012-10-03 Pratt & Whitney Canada Corp. Fuel nozzle providing shaped fuel spray
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US20100132364A1 (en) * 2008-12-01 2010-06-03 Myers Geoffrey D Fuel nozzle detachable burner tube
US8505304B2 (en) * 2008-12-01 2013-08-13 General Electric Company Fuel nozzle detachable burner tube with baffle plate assembly
CN101806460B (en) * 2008-12-01 2014-11-26 通用电气公司 Fuel nozzle detachable burner tube
US8893500B2 (en) 2011-05-18 2014-11-25 Solar Turbines Inc. Lean direct fuel injector
US8919132B2 (en) 2011-05-18 2014-12-30 Solar Turbines Inc. Method of operating a gas turbine engine
US9182124B2 (en) 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same
US20140060059A1 (en) * 2012-09-06 2014-03-06 United Technologies Corporation Fuel delivery system with a cavity coupled fuel injector
US10619855B2 (en) * 2012-09-06 2020-04-14 United Technologies Corporation Fuel delivery system with a cavity coupled fuel injector
US20140246518A1 (en) * 2013-03-01 2014-09-04 Delavan Inc Fuel nozzle with discrete jet inner air swirler
US9284933B2 (en) * 2013-03-01 2016-03-15 Delavan Inc Fuel nozzle with discrete jet inner air swirler
US11421883B2 (en) 2020-09-11 2022-08-23 Raytheon Technologies Corporation Fuel injector assembly with a helical swirler passage for a turbine engine
US11754287B2 (en) 2020-09-11 2023-09-12 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US11649964B2 (en) 2020-12-01 2023-05-16 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US11808455B2 (en) 2021-11-24 2023-11-07 Rtx Corporation Gas turbine engine combustor with integral fuel conduit(s)
US11846249B1 (en) 2022-09-02 2023-12-19 Rtx Corporation Gas turbine engine with integral bypass duct
US12116934B2 (en) 2023-02-10 2024-10-15 Rtx Corporation Turbine engine fuel injector with oxygen circuit

Also Published As

Publication number Publication date
CH560356A5 (en) 1975-03-27
FR2206441A1 (en) 1974-06-07
CA985514A (en) 1976-03-16
JPS5342897B2 (en) 1978-11-15
DE2355127C2 (en) 1983-11-03
FR2206441B1 (en) 1976-06-25
GB1450190A (en) 1976-09-22
JPS4968929A (en) 1974-07-04
DE2355127A1 (en) 1974-05-22
IT996392B (en) 1975-12-10

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