US3915387A - Fuel injection devices - Google Patents

Fuel injection devices Download PDF

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Publication number
US3915387A
US3915387A US483573A US48357374A US3915387A US 3915387 A US3915387 A US 3915387A US 483573 A US483573 A US 483573A US 48357374 A US48357374 A US 48357374A US 3915387 A US3915387 A US 3915387A
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US
United States
Prior art keywords
air
sub
assembly
swirler
swirl
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
US483573A
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English (en)
Inventor
Jacques Emile Jules Caruel
Jean Robert Bedue
Jean Alfred Eugene Cha Dobigny
Roland Robert Charles Beyler
Michel Bernard Schenher
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
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Publication of US3915387A publication Critical patent/US3915387A/en
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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
    • 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

  • a fuel injection device includes means whereby a rotating flow of an air/fuel mixture is sandwiched between rotating intemal and external air flows.
  • the components of the device are grouped into separately mounted sub-assemblies which are movable slidably relative to one another.
  • This invention relates to a high-performance fuel injection device designed particularly for aircraft jet propulsion systems and in which an intermediate annular flow containing fuel is sandwiched between internal and external flows of air caused to rotate by means of inner and outer bladed elements which are normally referred to as swirlers.
  • this intermediate annular flow comprises a mixture of air and fuel and is itself caused to rotate by a third bladed element, for example a swirler having helical blades and the components of the device are grouped into two sub-assemblies which are movable slidably relative to one another and are fixed separately to different parts of a fixed structure such as the jet engine combustion chamber.
  • a third bladed element for example a swirler having helical blades and the components of the device are grouped into two sub-assemblies which are movable slidably relative to one another and are fixed separately to different parts of a fixed structure such as the jet engine combustion chamber.
  • the shearing effect which the internal and external flows of air exert on the sandwiched intermediate flow of fuel and air can be increased by giving different rotational angular settings to the vanes or blades of the internal and external swirlers, the external blades having preferably a smaller angular setting than the internal blades.
  • Relative sliding movement between the two subassemblies takes place preferably adjacent the swirler which serves to produce rotation of the external flow of air.
  • a slidable sleeve is located at the inner periphery of the external swirler.
  • FIGS. 1 and 2 are transverse and longitudinal crosssectional views showing the elements of the fuel injection device, FIG. 1 being a section along the line II of FIG. 2 and the latter being a section along the line IIII of FIG. 1,
  • FIG. 3 is an exploded schematic view of the device shown in FIGS. 1 and 2, and 4
  • FIG. 4 is a longitudinal sectional view of a device according to the invention and its mounting in a jet combustion chamber.
  • the fuel injection device shown in FIGS. 1 and 2 comprises an outer liner 1 and a concentric inner liner 2 defining between them an annular passage 3 which is traversed, as indicated by the arrows F1, by air caused to rotate by a swirler 4.
  • a shaped central body or bulb 5 defines, together with a concentric liner 6 placed between it and the inner liner 2, a second passage 7 where primary air, flowing in the manner indicated by the arrows F2, is made to rotate by a swirler 8.
  • Fuel reaches the injection device through a nozzle 9 opening into an annular inlet collector 10.
  • the air/fuel mixture flows into the annular space 11 bounded by the liners 2 and 6, between which is arranged a third swirler 12 ensuring rotation of this air/fuel mixture which flows in the manner indicated by the arrows F3.
  • FIG. 3 illustrates, in a different way, a fuel injection device according to the invention.
  • the outer passage 3 is effected between the outer liner 1 and the inner liner 2. These two elements are interconnected by the vanes or blades of the swirler 4.
  • the liner assembly has a cap 13 and at its base it supports a duct 14 for the entry of the air/fuel mixture.
  • the intermediate passage 11 is defined between the inner liner 2 and the concentric liner 6, which concentric liner 6 is terminated by a conical cap 15.
  • the liner 6 supports the swirler l2, composed of helical blades 16 and a part-annular rib 17 which diverts part of the air/fuel mixture before it reaches the helical blades 16 so as to accelerate rotation of the mixture and improve the degree of mixing of the mixture.
  • the inner passage 7 is defined between the liner 6 and inner bulb 5; the latter carries the vanes or blades of the swirler 8.
  • the whole device is capped by a plate 18 which is of such size as to afford a circular slot 19 between its inner edge and the cap 13.
  • the fuel is injected at 9 into the inlet duct 14 which is itself fed by air.
  • the air/fuel mixture then reaches the annular collector 10 and separates into two streams, the first of which passes directly between the helical blades 16, and the second of which circulates around the half rib 17 before reaching the helical blades 16.
  • the air/fuel mixture is ejected through an annular slot 20 provided between the caps 13 and 15. Air caused to rotate by the outer swirler 4 emerges through the annular slot 19, whilst the air caused to rotate by the inner swirler 8 is ejected through a central opening 21.
  • a fuel injection device as shown in FIGS. 1 and 2 can with advantage be employed in accordance with the particular method of fitting illustrated in FIG. 4.
  • the outer liner 1 forms part of an external sub-assembly A and is screwed directly to the base 22 of the combustion chamber. Its rear part comprises a shoulder 23 on which is welded a thermal screen 24, and its front part carries a thread 25.
  • a threaded ring 26 fits on the thread 25 and holds the liner 1 tightly against the base of the chamber 22.
  • This liner 1 likewise supports, on its inner face, the swirler 4 and the inner periphery of the swirler 4 supports a sleeve 27.
  • an inner sub-assembly B comprising the liners 2 and 6, the inner swirler 8, the intermediate swirler 12, the central body 5 and the inlet duct 14, within which is located the nozzle 9 fed with fuel along a passage contained within a supporting arm 28.
  • the sub-assembly B integral with the latter can be introduced into the housing 29 through a suitable hole 30 which is closed by a plate 31 forming an integral part of the supporting arm 28 and fixed by screws 32 to the housing 29.
  • the outer swirler 4 which forms part of the subassembly A, is freely movable relative to the subassembly B, and this facilitates mounting and maintenance of the device.
  • the subassembly A is heated considerably and expands, whilst the sub-assembly B is cooled by the circulation of the air/fuel mixture.
  • the necessary play is provided by relative sliding movement between the liner 2 and the sleeve 27.
  • a multi-swirler fuel injection device to be fitted in a combustion chamber having separate and distinct wall elements (22,29) and of the kind designed to produce an inner air swirl (F2), an outer annular air swirl (F1) around and radially spaced from said inner air swirl, and an intermediate annular air/fuel swirl (F3) sandwiched between said inner and outer air swirls, in
  • the improvement comprising an assembly including a first sub-assembly (A) adapted to be secured to one (22) of said wall elements and comprising an air swirler (4), a second sub-assembly (B) adapted to be secured to another one (29) of said wall elements and comprising another air swirler (8), and guide means (27) mechanically associated with said subassemblies for telescoping one into the other in mutally fitting and relatively slidable relationship.
  • A first sub-assembly
  • B second sub-assembly adapted to be secured to another one (29) of said wall elements and comprising another air swirler (8)
  • guide means mechanically associated with said subassemblies for telescoping one into the other in mutally fitting and relatively slidable relationship.
  • said first sub-assembly (A) comprises the air swirler (4) of said outer annular air swirl (F1)
  • said second subassembly (B) comprises the air swirler (8) of said inner air swirl (F2) and is telescopingly fitted into said first sub-assembly (A).
  • said guide means comprises a sleeve (27) located inwardly of the air swirler (4) of said first sub-assembly (A) and outwardly of the third swirler (12) of said second subassembly (B).
  • a device wherein the blades of the inner and outer swirlers have different angular rotational settings.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Spray-Type Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)
US483573A 1973-06-28 1974-06-27 Fuel injection devices Expired - Lifetime US3915387A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7323661A FR2235274B1 (it) 1973-06-28 1973-06-28

Publications (1)

Publication Number Publication Date
US3915387A true US3915387A (en) 1975-10-28

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ID=9121707

Family Applications (1)

Application Number Title Priority Date Filing Date
US483573A Expired - Lifetime US3915387A (en) 1973-06-28 1974-06-27 Fuel injection devices

Country Status (4)

Country Link
US (1) US3915387A (it)
DE (1) DE2429951C2 (it)
FR (1) FR2235274B1 (it)
GB (1) GB1429589A (it)

Cited By (65)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4092826A (en) * 1975-12-06 1978-06-06 Rolls-Royce Limited Fuel injectors for gas turbine engines
US4157889A (en) * 1976-04-16 1979-06-12 Societe Colmant Cuvelier Burner for powdered fuel
US4170108A (en) * 1975-04-25 1979-10-09 Rolls-Royce Limited Fuel injectors for gas turbine engines
US4189914A (en) * 1978-06-19 1980-02-26 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Supercritical fuel injection system
US4497170A (en) * 1982-07-22 1985-02-05 The Garrett Corporation Actuation system for a variable geometry combustor
US4532762A (en) * 1982-07-22 1985-08-06 The Garrett Corporation Gas turbine engine variable geometry combustor apparatus
US4546923A (en) * 1980-11-29 1985-10-15 Tadashi Ii Nozzle for atomizing fluids
US4580727A (en) * 1982-06-03 1986-04-08 Ransburg-Gema Ag Atomizer for coating with powder
US4587809A (en) * 1981-06-15 1986-05-13 Hitachi, Ltd. Premixing swirling burner
US4815664A (en) * 1987-03-19 1989-03-28 United Technologies Corporation Airblast fuel atomizer
US5020329A (en) * 1984-12-20 1991-06-04 General Electric Company Fuel delivery system
US5097666A (en) * 1989-12-11 1992-03-24 Sundstrand Corporation Combustor fuel injection system
US5165241A (en) * 1991-02-22 1992-11-24 General Electric Company Air fuel mixer for gas turbine combustor
US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
US5289685A (en) * 1992-11-16 1994-03-01 General Electric Company Fuel supply system for a gas turbine engine
US5303542A (en) * 1992-11-16 1994-04-19 General Electric Company Fuel supply control method for a gas turbine engine
US5323604A (en) * 1992-11-16 1994-06-28 General Electric Company Triple annular combustor for gas turbine engine
AU655340B2 (en) * 1991-12-06 1994-12-15 Haldor Topsoe A/S Burner
US5417070A (en) * 1992-11-24 1995-05-23 Rolls-Royce Plc Fuel injection apparatus
US5490380A (en) * 1992-06-12 1996-02-13 United Technologies Corporation Method for performing combustion
US5499768A (en) * 1989-05-31 1996-03-19 Ohkawara Kakohki Co., Ltd. Spray nozzle unit
US5505045A (en) * 1992-11-09 1996-04-09 Fuel Systems Textron, Inc. Fuel injector assembly with first and second fuel injectors and inner, outer, and intermediate air discharge chambers
US5966937A (en) * 1997-10-09 1999-10-19 United Technologies Corporation Radial inlet swirler with twisted vanes for fuel injector
US6161387A (en) * 1998-10-30 2000-12-19 United Technologies Corporation Multishear fuel injector
US6240732B1 (en) * 1997-12-19 2001-06-05 Rolls-Royce Plc Fluid manifold
US6272865B1 (en) * 1999-04-30 2001-08-14 United Technologies Corporation Swirler scoop and bearing plate for combustor
US6474569B1 (en) * 1997-12-18 2002-11-05 Quinetiq Limited Fuel injector
US6502399B2 (en) 1997-09-10 2003-01-07 Mitsubishi Heavy Industries, Ltd. Three-dimensional swirler in a gas turbine combustor
US20050061004A1 (en) * 2003-09-22 2005-03-24 Andrei Colibaba-Evulet Method and apparatus for reducing gas turbine engine emissions
FR2861137A1 (fr) * 2003-10-16 2005-04-22 Renault Sa Dispositif et procede de preparation d'un melange homogene de fluides gazeux pour moteur
US20050127537A1 (en) * 2003-12-16 2005-06-16 Kawasaki Jukogyo Kabushiki Kaisha Premixed air-fuel mixture supply device
US20050268618A1 (en) * 2004-06-08 2005-12-08 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine
US20060026964A1 (en) * 2003-10-14 2006-02-09 Robert Bland Catalytic combustion system and method
JP2006090327A (ja) * 2004-09-23 2006-04-06 Snecma ターボ機械燃焼室に空気／燃料混合物を噴射する発泡性空気力式システム
US20070134608A1 (en) * 2003-07-18 2007-06-14 Hanno Tautz Gas burner
EP1826490A2 (en) * 2006-02-23 2007-08-29 General Electric Company Method and apparatus for gas turbine engines
US20080016876A1 (en) * 2005-06-02 2008-01-24 General Electric Company Method and apparatus for reducing gas turbine engine emissions
JP2010101540A (ja) * 2008-10-22 2010-05-06 Niigata Power Systems Co Ltd ガスタービン用燃料噴射装置
JP2010101514A (ja) * 2008-10-21 2010-05-06 Niigata Power Systems Co Ltd 燃料噴射装置
CN101220953B (zh) * 2007-01-10 2012-06-13 通用电气公司 燃料灵活的三方向旋转旋流器和其使用方法
US20120144832A1 (en) * 2010-12-10 2012-06-14 General Electric Company Passive air-fuel mixing prechamber
CN102588964A (zh) * 2011-02-27 2012-07-18 江西中船航海仪器有限公司 一种燃烧器配风器
US20130205788A1 (en) * 2012-02-10 2013-08-15 Rolls-Royce Deutschland Ltd & Co Kg Unknown
CN103499097A (zh) * 2013-09-29 2014-01-08 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃用中低热值燃料气的燃烧室燃烧组织方法及喷嘴
CN104019448A (zh) * 2014-06-13 2014-09-03 北京北机机电工业有限责任公司 一种加热器燃烧室双层旋风装置
CN104033899A (zh) * 2014-06-13 2014-09-10 北京北机机电工业有限责任公司 一种加热器燃烧室单层旋风装置
CN104154566A (zh) * 2014-07-08 2014-11-19 北京华清燃气轮机与煤气化联合循环工程技术有限公司 燃气轮机双燃料喷嘴结构
CN104180387A (zh) * 2013-05-23 2014-12-03 江苏汇能锅炉有限公司（丹阳锅炉辅机厂有限公司） 一种新型锅炉用旋风式喷头
WO2015017002A2 (en) 2013-07-15 2015-02-05 United Technologies Corporation Swirler mount interface for gas turbine engine combustor
CN105402724A (zh) * 2015-12-29 2016-03-16 云南航天工业有限公司 一种双旋风式一次配风结构的燃烧器
EP2935868A4 (en) * 2012-12-19 2016-04-20 United Technologies Corp SUPPLY DISTRIBUTION
US20160169178A1 (en) * 2013-12-02 2016-06-16 Rolls-Royce Plc Combustion chamber assembly
CN105716113A (zh) * 2016-02-06 2016-06-29 中国科学院工程热物理研究所 双旋预混燃烧器
WO2017044536A1 (en) * 2015-09-08 2017-03-16 Rutgers, The State University Of New Jersey Personal electrostatic bioaerosol sampler with high sampling flow rate
US20170284673A1 (en) * 2016-03-31 2017-10-05 Rolls-Royce Plc Fuel injector
WO2018060590A1 (fr) 2016-09-29 2018-04-05 Safran Helicopter Engines Dispositif d'alimentation en carburant d'une chambre de combustion de turbomachine améliorant l'homogénéité de l'alimentation des dispositifs d'injection du carburant
CN109595590A (zh) * 2018-11-28 2019-04-09 西北工业大学 一种网格结构整流支板火焰稳定器的一体化加力燃烧室
US20200033007A1 (en) * 2016-04-28 2020-01-30 Safran Aircraft Engines Air intake swirler for a turbomachine injection system comprising an aerodynamic deflector at its inlet
US20220082257A1 (en) * 2020-09-11 2022-03-17 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US11286858B2 (en) * 2017-03-21 2022-03-29 Toshiba Energy Systems & Solutions Corporation Gas turbine combustor
US11371708B2 (en) * 2018-04-06 2022-06-28 General Electric Company Premixer for low emissions gas turbine combustor
US20220333779A1 (en) * 2021-04-16 2022-10-20 General Electric Company Combustor swirl vane apparatus
US20220333780A1 (en) * 2021-04-16 2022-10-20 General Electric Company Combustor swirl vane apparatus
US11649963B2 (en) * 2018-06-01 2023-05-16 Ihi Corporation Liquid fuel injector
US20230417414A1 (en) * 2021-03-25 2023-12-28 Ihi Corporation Combustion device and gas turbine system

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1537671A (en) * 1975-04-25 1979-01-04 Rolls Royce Fuel injectors for gas turbine engines
DE3028003C1 (de) * 1980-07-24 1981-10-08 Basf Ag, 6700 Ludwigshafen Vorrichtung zur Verteilung eines aus einem Rohr ankommenden Gases auf den Querschnitt eines Behaelters
GB2097112B (en) * 1981-04-16 1984-12-12 Rolls Royce Fuel burners and combustion equipment for use in gas turbine engines
US4609150A (en) * 1983-07-19 1986-09-02 United Technologies Corporation Fuel nozzle for gas turbine engine
FR2575223B1 (fr) * 1984-12-20 1991-10-25 Gen Electric Systeme de fourniture de combustible
US4941617A (en) * 1988-12-14 1990-07-17 United Technologies Corporation Airblast fuel nozzle
US5117637A (en) * 1990-08-02 1992-06-02 General Electric Company Combustor dome assembly
RU2448300C2 (ru) * 2010-02-24 2012-04-20 Государственное образовательное учреждение высшего профессионального образования Томский государственный университет систем управления и радиоэлектроники (ТУСУР) Способ эффективного сжигания топлива и устройство для его осуществления
RU2567899C2 (ru) * 2014-02-19 2015-11-10 Андрей Аркадьевич Мельников Устройство для сжигания топлива
FR3057277B1 (fr) * 2016-10-12 2022-08-12 Commissariat Energie Atomique Generateur de vapeur d'eau, pour reacteur d'electrolyse ou de co-electrolyse de l'eau (soec) ou pile a combustible (sofc) a fonctionnement sous pression
CN109595589B (zh) * 2018-11-28 2020-12-08 西北工业大学 一种应用双级旋流器的一体化加力燃烧室

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1881359A (en) * 1929-10-05 1932-10-04 Jones James William Oil fuel burner
US2612405A (en) * 1949-06-03 1952-09-30 Ind Karlsruhe Ag Spraying nozzle
US2701164A (en) * 1951-04-26 1955-02-01 Gen Motors Corp Duplex fuel nozzle
US3039701A (en) * 1959-08-08 1962-06-19 Rolls Royce Fuel injectors
US3612737A (en) * 1968-11-27 1971-10-12 Sulzer Ag Turbulence muffle burner

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1108666B (de) * 1956-01-21 1961-06-15 Krauss Maffei Ag Vorrichtung zum Mischen eines stroemenden Arbeitsstoffes mit mindestens einem stroemenden Medium aus Gas oder einer Fluessigkeit
DE1244481B (de) * 1957-06-20 1967-07-13 Rolls Royce Brenner fuer Gasturbinenanlagen
US3584791A (en) * 1968-08-21 1971-06-15 Lucas Industries Ltd Fuel sprayers

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1881359A (en) * 1929-10-05 1932-10-04 Jones James William Oil fuel burner
US2612405A (en) * 1949-06-03 1952-09-30 Ind Karlsruhe Ag Spraying nozzle
US2701164A (en) * 1951-04-26 1955-02-01 Gen Motors Corp Duplex fuel nozzle
US3039701A (en) * 1959-08-08 1962-06-19 Rolls Royce Fuel injectors
US3612737A (en) * 1968-11-27 1971-10-12 Sulzer Ag Turbulence muffle burner

Cited By (89)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4170108A (en) * 1975-04-25 1979-10-09 Rolls-Royce Limited Fuel injectors for gas turbine engines
US4092826A (en) * 1975-12-06 1978-06-06 Rolls-Royce Limited Fuel injectors for gas turbine engines
US4157889A (en) * 1976-04-16 1979-06-12 Societe Colmant Cuvelier Burner for powdered fuel
US4189914A (en) * 1978-06-19 1980-02-26 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Supercritical fuel injection system
US4546923A (en) * 1980-11-29 1985-10-15 Tadashi Ii Nozzle for atomizing fluids
US4587809A (en) * 1981-06-15 1986-05-13 Hitachi, Ltd. Premixing swirling burner
US4580727A (en) * 1982-06-03 1986-04-08 Ransburg-Gema Ag Atomizer for coating with powder
US4497170A (en) * 1982-07-22 1985-02-05 The Garrett Corporation Actuation system for a variable geometry combustor
US4532762A (en) * 1982-07-22 1985-08-06 The Garrett Corporation Gas turbine engine variable geometry combustor apparatus
US5020329A (en) * 1984-12-20 1991-06-04 General Electric Company Fuel delivery system
US4815664A (en) * 1987-03-19 1989-03-28 United Technologies Corporation Airblast fuel atomizer
US5499768A (en) * 1989-05-31 1996-03-19 Ohkawara Kakohki Co., Ltd. Spray nozzle unit
US5097666A (en) * 1989-12-11 1992-03-24 Sundstrand Corporation Combustor fuel injection system
US5165241A (en) * 1991-02-22 1992-11-24 General Electric Company Air fuel mixer for gas turbine combustor
US5496170A (en) * 1991-12-06 1996-03-05 Haldor Topsoe A/S Swirling-flow burner
AU655340B2 (en) * 1991-12-06 1994-12-15 Haldor Topsoe A/S Burner
US5490380A (en) * 1992-06-12 1996-02-13 United Technologies Corporation Method for performing combustion
US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
US5505045A (en) * 1992-11-09 1996-04-09 Fuel Systems Textron, Inc. Fuel injector assembly with first and second fuel injectors and inner, outer, and intermediate air discharge chambers
US5323604A (en) * 1992-11-16 1994-06-28 General Electric Company Triple annular combustor for gas turbine engine
US5303542A (en) * 1992-11-16 1994-04-19 General Electric Company Fuel supply control method for a gas turbine engine
US5289685A (en) * 1992-11-16 1994-03-01 General Electric Company Fuel supply system for a gas turbine engine
US5417070A (en) * 1992-11-24 1995-05-23 Rolls-Royce Plc Fuel injection apparatus
US6502399B2 (en) 1997-09-10 2003-01-07 Mitsubishi Heavy Industries, Ltd. Three-dimensional swirler in a gas turbine combustor
US5966937A (en) * 1997-10-09 1999-10-19 United Technologies Corporation Radial inlet swirler with twisted vanes for fuel injector
US6474569B1 (en) * 1997-12-18 2002-11-05 Quinetiq Limited Fuel injector
US6240732B1 (en) * 1997-12-19 2001-06-05 Rolls-Royce Plc Fluid manifold
US6161387A (en) * 1998-10-30 2000-12-19 United Technologies Corporation Multishear fuel injector
US6272865B1 (en) * 1999-04-30 2001-08-14 United Technologies Corporation Swirler scoop and bearing plate for combustor
US20070134608A1 (en) * 2003-07-18 2007-06-14 Hanno Tautz Gas burner
US6968693B2 (en) * 2003-09-22 2005-11-29 General Electric Company Method and apparatus for reducing gas turbine engine emissions
US7260935B2 (en) 2003-09-22 2007-08-28 General Electric Company Method and apparatus for reducing gas turbine engine emissions
US20050061004A1 (en) * 2003-09-22 2005-03-24 Andrei Colibaba-Evulet Method and apparatus for reducing gas turbine engine emissions
US7096671B2 (en) * 2003-10-14 2006-08-29 Siemens Westinghouse Power Corporation Catalytic combustion system and method
US20060026964A1 (en) * 2003-10-14 2006-02-09 Robert Bland Catalytic combustion system and method
FR2861137A1 (fr) * 2003-10-16 2005-04-22 Renault Sa Dispositif et procede de preparation d'un melange homogene de fluides gazeux pour moteur
US20050127537A1 (en) * 2003-12-16 2005-06-16 Kawasaki Jukogyo Kabushiki Kaisha Premixed air-fuel mixture supply device
JP2005180729A (ja) * 2003-12-16 2005-07-07 Kawasaki Heavy Ind Ltd 予混合燃料噴射弁の燃焼性改善装置
US7090205B2 (en) * 2003-12-16 2006-08-15 Kawasaki Jukogyo Kabushiki Kaisha Premixed air-fuel mixture supply device
US20050268618A1 (en) * 2004-06-08 2005-12-08 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine
US6993916B2 (en) * 2004-06-08 2006-02-07 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine
JP2006090327A (ja) * 2004-09-23 2006-04-06 Snecma ターボ機械燃焼室に空気／燃料混合物を噴射する発泡性空気力式システム
JP4695952B2 (ja) * 2004-09-23 2011-06-08 スネクマ ターボ機械燃焼室に空気／燃料混合物を噴射する発泡性空気力式システム
US20080016876A1 (en) * 2005-06-02 2008-01-24 General Electric Company Method and apparatus for reducing gas turbine engine emissions
EP1826490A2 (en) * 2006-02-23 2007-08-29 General Electric Company Method and apparatus for gas turbine engines
EP1826490A3 (en) * 2006-02-23 2013-11-06 General Electric Company Method and apparatus for gas turbine engines
CN101220953B (zh) * 2007-01-10 2012-06-13 通用电气公司 燃料灵活的三方向旋转旋流器和其使用方法
JP2010101514A (ja) * 2008-10-21 2010-05-06 Niigata Power Systems Co Ltd 燃料噴射装置
JP2010101540A (ja) * 2008-10-22 2010-05-06 Niigata Power Systems Co Ltd ガスタービン用燃料噴射装置
US20120144832A1 (en) * 2010-12-10 2012-06-14 General Electric Company Passive air-fuel mixing prechamber
CN102588964A (zh) * 2011-02-27 2012-07-18 江西中船航海仪器有限公司 一种燃烧器配风器
US20130205788A1 (en) * 2012-02-10 2013-08-15 Rolls-Royce Deutschland Ltd & Co Kg Unknown
US8752388B2 (en) * 2012-02-10 2014-06-17 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine premix burner
US9476429B2 (en) 2012-12-19 2016-10-25 United Technologies Corporation Flow feed diffuser
EP2935868A4 (en) * 2012-12-19 2016-04-20 United Technologies Corp SUPPLY DISTRIBUTION
CN104180387A (zh) * 2013-05-23 2014-12-03 江苏汇能锅炉有限公司（丹阳锅炉辅机厂有限公司） 一种新型锅炉用旋风式喷头
US10088166B2 (en) 2013-07-15 2018-10-02 United Technologies Corporation Swirler mount interface for gas turbine engine combustor
EP3022422A4 (en) * 2013-07-15 2016-11-30 United Technologies Corp MOUNTING INTERFACE FOR A TURBULENCE BLADE ASSEMBLY FOR THE COMBUSTION CHAMBER OF A GAS TURBINE ENGINE
WO2015017002A2 (en) 2013-07-15 2015-02-05 United Technologies Corporation Swirler mount interface for gas turbine engine combustor
CN103499097B (zh) * 2013-09-29 2016-05-11 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃用中低热值燃料气的燃烧室燃烧组织方法及喷嘴
CN103499097A (zh) * 2013-09-29 2014-01-08 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃用中低热值燃料气的燃烧室燃烧组织方法及喷嘴
US10018167B2 (en) * 2013-12-02 2018-07-10 Rolls-Royce Plc Combustion chamber assembly with an air swirler and a fuel injector having inter-engaging faces
US20160169178A1 (en) * 2013-12-02 2016-06-16 Rolls-Royce Plc Combustion chamber assembly
CN104033899A (zh) * 2014-06-13 2014-09-10 北京北机机电工业有限责任公司 一种加热器燃烧室单层旋风装置
CN104019448A (zh) * 2014-06-13 2014-09-03 北京北机机电工业有限责任公司 一种加热器燃烧室双层旋风装置
CN104154566B (zh) * 2014-07-08 2018-03-23 北京华清燃气轮机与煤气化联合循环工程技术有限公司 燃气轮机双燃料喷嘴结构
CN104154566A (zh) * 2014-07-08 2014-11-19 北京华清燃气轮机与煤气化联合循环工程技术有限公司 燃气轮机双燃料喷嘴结构
US10919047B2 (en) 2015-09-08 2021-02-16 Rutgers, The State University Of New Jersey Personal electrostatic bioaerosol sampler with high sampling flow rate
WO2017044536A1 (en) * 2015-09-08 2017-03-16 Rutgers, The State University Of New Jersey Personal electrostatic bioaerosol sampler with high sampling flow rate
CN105402724A (zh) * 2015-12-29 2016-03-16 云南航天工业有限公司 一种双旋风式一次配风结构的燃烧器
CN105716113A (zh) * 2016-02-06 2016-06-29 中国科学院工程热物理研究所 双旋预混燃烧器
CN105716113B (zh) * 2016-02-06 2019-03-12 中国科学院工程热物理研究所 双旋预混燃烧器
US10429071B2 (en) * 2016-03-31 2019-10-01 Rolls-Royce Plc Fuel injector
US20170284673A1 (en) * 2016-03-31 2017-10-05 Rolls-Royce Plc Fuel injector
US10883718B2 (en) * 2016-04-28 2021-01-05 Safran Aircraft Engines Air intake swirler for a turbomachine injection system comprising an aerodynamic deflector at its inlet
US20200033007A1 (en) * 2016-04-28 2020-01-30 Safran Aircraft Engines Air intake swirler for a turbomachine injection system comprising an aerodynamic deflector at its inlet
WO2018060590A1 (fr) 2016-09-29 2018-04-05 Safran Helicopter Engines Dispositif d'alimentation en carburant d'une chambre de combustion de turbomachine améliorant l'homogénéité de l'alimentation des dispositifs d'injection du carburant
US11286858B2 (en) * 2017-03-21 2022-03-29 Toshiba Energy Systems & Solutions Corporation Gas turbine combustor
US11371708B2 (en) * 2018-04-06 2022-06-28 General Electric Company Premixer for low emissions gas turbine combustor
US11649963B2 (en) * 2018-06-01 2023-05-16 Ihi Corporation Liquid fuel injector
CN109595590A (zh) * 2018-11-28 2019-04-09 西北工业大学 一种网格结构整流支板火焰稳定器的一体化加力燃烧室
US11421883B2 (en) * 2020-09-11 2022-08-23 Raytheon Technologies Corporation Fuel injector assembly with a helical swirler passage for a turbine engine
US20220082257A1 (en) * 2020-09-11 2022-03-17 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US20230417414A1 (en) * 2021-03-25 2023-12-28 Ihi Corporation Combustion device and gas turbine system
US20220333779A1 (en) * 2021-04-16 2022-10-20 General Electric Company Combustor swirl vane apparatus
US20220333780A1 (en) * 2021-04-16 2022-10-20 General Electric Company Combustor swirl vane apparatus
CN115218213A (zh) * 2021-04-16 2022-10-21 通用电气公司 燃烧器旋流轮叶设备
US11598526B2 (en) * 2021-04-16 2023-03-07 General Electric Company Combustor swirl vane apparatus
US11802693B2 (en) * 2021-04-16 2023-10-31 General Electric Company Combustor swirl vane apparatus

Also Published As

Publication number Publication date
DE2429951C2 (de) 1983-05-11
DE2429951A1 (de) 1975-01-16
FR2235274A1 (it) 1975-01-24
FR2235274B1 (it) 1976-09-17
GB1429589A (en) 1976-03-24

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