US3667221A - Fuel delivery apparatus - Google Patents

Fuel delivery apparatus Download PDF

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Publication number
US3667221A
US3667221A US816985A US3667221DA US3667221A US 3667221 A US3667221 A US 3667221A US 816985 A US816985 A US 816985A US 3667221D A US3667221D A US 3667221DA US 3667221 A US3667221 A US 3667221A
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United States
Prior art keywords
fuel
air
wall
upstream
generally
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Expired - Lifetime
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US816985A
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English (en)
Inventor
Jack R Taylor
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General Electric Co
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General Electric Co
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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
    • 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

Definitions

  • ABSTRACT Apparatus for premixing air and fuel or carbureting air prior to introduction thereof into the primary zone of a combustor, said apparatus including a housing defining a spin chamber therein; the spin chamber is adapted to receive air and fuel and vaporize and/or atomize said fuel and deliver said air and fuel into said combustor as a vertical flow.
  • spray atomizing nozzles of the type adapted to deliver a single or dual atomized conical fuel spray through a small discharge orifice have heretofore enjoyed widespread usage, such devices are generally complex and expensive in nature and generally require a relatively expensive and complex high pressure fuel delivery or distribution system. Furthermore, such spray atomizing nozzles tend to produce local fuel-rich pockets and are sensitive to fouling by carbon deposits or other deleterious matter.
  • This invention is concerned with an efiicient fuel delivery apparatus which overcomes the foregoing problems.
  • a primary object of this invention is to provide relatively simple and economical means for delivery of fuel into a combustion chamber in a highly dispersed manner.
  • Another object of this invention is a long life fuel delivery apparatus adapted to receive air and fuel, atomize and/or vaporize the fuel, and carburet the inlet air with such fuel or premix the fuel and air prior to introducing the fuel into the primary zone of the combustor.
  • a further object of this invention is an apparatus for supplying fuel to a combustion chamber which is relatively insensitive to fouling, does not require a high pressure fuel distribution system, and is of relatively short axial length.
  • Yet another object of this invention is an apparatus which is adapted toutilize the energy of the inlet air to effect delivery of the fuel to the combustion chamber in a highly dispersed manner.
  • a housing having a central or core outlet in flow communication with the combustion chamber and defining a spin chamber around the outlet.
  • the spin chamber is adapted to receive and circulate pressurized air and fuel around the outlet and generate a vortical discharge of air from the outlet. In this manner, the fuel is vaporized and/or atomized and delivered into the combustion chamber with the air vortex.
  • the spin chamber is preferably formed with an involute or spiral shaped outer wall and generally planar upstream and downstream end walls.
  • Inlet passage means may be provided for receiving a generally axially directed flow of pressurized air and directing such air in a generally streamline manner into the spin chamber.
  • the inlet passage means may also be adapted to receive and direct the fuel into the swirl chamber although separate passage means may be used.
  • Swirl vanes may be employed to enchance the rotational velocity of the vortex discharge as well as accurately locate the vortex centrally of the outlet.
  • FIG. 1 is a fragmentary axial cross section view ofan exemplary gas turbine engine combustion apparatus embodying the present invention
  • FIG. 2 is a front elevational view, in partial cross section, of the fuel delivery apparatus of this invention.
  • FIG. 3 is a side view, in partial cross section, of the apparatus of FIG. 2;
  • FIG. 4 is a cross sectional view taken along lines 4--4 of FIG. 2.
  • a continuous burning combustion apparatus of the type suitable for use in a gas turbine engine has been shown generally at 10 as comprising a hollow body 12 defining a combustion chamber 14 therein.
  • the hollow body 12 includes a domed upstream end 16 having an opening 18 therein for receiving a fuel/air mixture.
  • the combustion chamber 14 may be of the annular type, the cannula: type or the can type, with the apparatus 10 having a plurality of circumferentially spaced openings 18.
  • An outer shell 20 may be provided to enclose the hollow body 12 and define passages 22 and 24 in cooperation with the hollow body 12 and a snout assembly 26.
  • the passages 22 and 24 are adapted to deliver a flow of pressurized air from a suitable source, such as a compressor 28, into the combustion chamber 14 through suitable apertures or louvers 30 for cooling of the hollow body 12 and dilution of the gaseous products of combustion.
  • the snout assembly 26 is suitably secured to the upstream end of the hollow body 12 and is adapted to function as a flow splitter to divide the pressurized air delivered from the compressor 28 between passages 22, 24 and a passage 32 formed through the snout assembly.
  • the fuel injection or carbureting apparatus of this invention has been shown generally at 34 as comprising a housing having inlet passage means 36 for receiving pressurized air from snout assembly passage 32, a central or core outlet 38 in flow communication with the hollow body opening 18 for delivery of an air/fuel mixture into the combustion chamber 14 as a vortical flow 40, and means 42 for receiving fuel from a suitable conduit 44 which extends through the snout assembly 26 and outer shell 20 and communicates with a source of pressurized fuel.
  • the fuel injection apparatus 34 is particularly suited for use with liquid fuel and will be hereinafter described in connection with a liquid fuel, it will be appreciated that fuel in the liquid state, gaseous state,, solid state or a combination thereof may be employed.
  • suitable ignition means (not shown) of well known construction are provided within the combustion chamber 14 to provide initial ignition of the combustible air/fuel mixture discharged through outlet 38.
  • the housing comprises an involute outer wall 48 and generally planar, spaced, upstream and downstream end walls 50 and 52, respectively, peripherally joining the outer wall and defining, in cooperation therewith, an air vortex generator or spin chamber 46 within the housing outwardly of the core opening 38.
  • the outer wall 48 is generally involute or spiral in shape with a progressively decreasing radius from the inlet passage 36 to a terminal edge or lip 54 which defines, in part, the inlet opening from the passage 36 to the spin chamber 46.
  • the inlet passage 36 is formed with a generally axially facing, upstream end opening for receiving the flow of pressurized air from passage 32 and has one wall formed as a streamline continuation of the involute outer wall 48 so as to deliver the inlet air in a generally streamline manner into the spin chamber 46.
  • pressurized air is directed into the spin chamber 46 in a circular motion of ever-decreasing radius so as to generate the vortical or cyclonic discharge 40 having a hollow core 56.
  • a plurality of swirl vanes 58 each of which extends between the upstream and downstream walls 50 and 52, may be provided in a peripheral array about the outlet 38 as shown in FIG. 2. Such an array of swirl vanes may also be crease the rotational velocity of the vortical flow 40.
  • the spin chamber 46 and the passage means 36 have been shown and described as being involute, and such is the preferred construction, it should be understood that other vortex generator or spin chamber and passage means configurations may be employed.
  • the spin chamber may be circular and the passage means may be adapted to deliver the inlet air in a tangential manner.
  • the outlet 38 and swirl vanes 58 are preferably positioned with respect to the outer wall 48 so that the cross sectional flow area between the outer wall 48 and the vanes 58 or opening 38 progressively decreases from the inlet 36 to the lip
  • the apparatus 34 may be secured in the position of FIG. 1 by any suitable means, such as by welding to the snout assembly 26 and/or the hollow body 12 or by employing suitable bracketry (not shown).
  • liquid fuel 60 is delivered to inlet passage 36 through means 42. Some of this fuel is immediately vaporized and/or atomized and picked up by or entrained within the high velocity inlet air and carried into the combustion chamber 14. The remaining fuel lands on the interior surface of the inlet passage 36 and is drivenor pushed by the high velocity inlet air into the spin chamber 46 and centrifugally along the outer wall 48. During such flow, a portion of the fuel may be vaporized and entrained within the inlet air flow.
  • a portion of g the fuel flow along outer wall 48 which is not so evaporated is then sheared off the lip 54, as at 62, and again passes across the high velocity, generally high temperature, inlet air flow which results in more fuel being vaporized and/or atomized and entrained within the inlet air.
  • the inlet air from the compressor 28 may be at an elevated temperature of 700 F. or higher, it will be appreciated that significant vaporization may occur during such flow through the vortex generator or spin chamber 46.
  • the liquid fuel circulating within spin chamber 46 is carried in a swirling flow along the inner surface of upstream wall 50 by the swirling air flow.
  • This swirling flow liquid fuel is carried through vanes 58 and forms a ring of fuel 64 where the fuel velocity forces are balanced by the centrifugal forces.
  • some of the fuel may be vaporized from the surface by the high temperature inlet air and by radiant heat from the flames within the combustion chamber 14. It has been found that the liquid fuel within the ring of fuel 64 is spun off and atomized into extremely small fuel droplets by the high velocity vortical flow of air 40 and directed toward the combustion chamber 14 as a generally conical spray 66. Since these atomized fuel droplets are extremely small, they quickly vaporize and mix with the air vortex 40.
  • the present invention provides compact and economical means for carbureting air or premixing air and fuel prior to introduction thereof into the primary zone of combustor and, hence, for delivery of the fuel into a combustion chamber in a highly effective and dispersed manner.
  • a combustion apparatus including, in combination:
  • a hollow body defining a combustion chamber therein, said hollow body formed with an opening therein, and
  • said housing including a downstream wall fonned with an outlet of generally circular flow area in the fluid flow communication with said hollow body opening, an upstream wall facing said outlet, an involute outer wall extending between and joining said upstream and downstream walls so as to define a spin chamber internally of said housing and a generally tangential inlet to said spin chamber, an annular array of swirl vanes extending between said upstream and downstream walls around said outlet, and passage means in fluid flow connection with said tangential inlet for delivery of liquid fuel and air to said spin chamber at a point radially outwardly of said vanes.
  • passage means is formed with an upstream facing inlet for receiving a generally axially directed flow of air and includes one side wall formed as a generally streamline continuation of said involute outer wall.

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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)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
US816985A 1969-04-17 1969-04-17 Fuel delivery apparatus Expired - Lifetime US3667221A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US81698569A 1969-04-17 1969-04-17

Publications (1)

Publication Number Publication Date
US3667221A true US3667221A (en) 1972-06-06

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Application Number Title Priority Date Filing Date
US816985A Expired - Lifetime US3667221A (en) 1969-04-17 1969-04-17 Fuel delivery apparatus

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US (1) US3667221A (enrdf_load_stackoverflow)
BE (1) BE748911A (enrdf_load_stackoverflow)
CA (1) CA922907A (enrdf_load_stackoverflow)
CH (1) CH526043A (enrdf_load_stackoverflow)
DE (1) DE2018485A1 (enrdf_load_stackoverflow)
DK (1) DK130661B (enrdf_load_stackoverflow)
FR (1) FR2043412A5 (enrdf_load_stackoverflow)
GB (1) GB1302217A (enrdf_load_stackoverflow)
IL (1) IL34172A (enrdf_load_stackoverflow)
NL (1) NL7005473A (enrdf_load_stackoverflow)
NO (1) NO132165C (enrdf_load_stackoverflow)

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3804578A (en) * 1972-10-10 1974-04-16 D Robbins Cyclonic combustion burner
US3811278A (en) * 1973-02-01 1974-05-21 Gen Electric Fuel injection apparatus
US3944634A (en) * 1973-05-29 1976-03-16 John M. Anderson Carburetor idling system
US4036914A (en) * 1975-08-14 1977-07-19 John Hawryluk Liquid fuel mixing device
US4092826A (en) * 1975-12-06 1978-06-06 Rolls-Royce Limited Fuel injectors for gas turbine engines
US4177637A (en) * 1976-12-23 1979-12-11 Rolls-Royce Limited Inlet for annular gas turbine combustor
US4245961A (en) * 1978-09-08 1981-01-20 Martin Marietta Corporation Ejector utilizing a vortex flow
US4365951A (en) * 1980-06-13 1982-12-28 Jan Alpkvist Device for combustion of a volatile fuel with air
US4375801A (en) * 1981-10-01 1983-03-08 Eckman Donald E Charge mixing carburetor plate
US4388045A (en) * 1976-01-30 1983-06-14 Martin Marietta Corporation Apparatus and method for mixing and pumping fluids
FR2614361A1 (fr) * 1987-04-27 1988-10-28 Gen Electric Dispositif de carburation pour turbine a gaz
US5343691A (en) * 1992-07-27 1994-09-06 General Electric Company Reducing thermal deposits in propulsion systems
WO1995016881A1 (en) * 1993-12-17 1995-06-22 Abb Stal Ab Method and apparatus for atomizing liquid fuel
US5609655A (en) * 1993-08-27 1997-03-11 Northern Research & Engineering Corp. Gas turbine apparatus
US5672187A (en) * 1994-11-23 1997-09-30 Cyclone Technologies Inc. Cyclone vortex system and process
US5805973A (en) * 1991-03-25 1998-09-08 General Electric Company Coated articles and method for the prevention of fuel thermal degradation deposits
US5891584A (en) * 1991-03-25 1999-04-06 General Electric Company Coated article for hot hydrocarbon fluid and method of preventing fuel thermal degradation deposits
US6113078A (en) * 1998-03-18 2000-09-05 Lytesyde, Llc Fluid processing method
US6253538B1 (en) 1999-09-27 2001-07-03 Pratt & Whitney Canada Corp. Variable premix-lean burn combustor
US20050035219A1 (en) * 2003-08-15 2005-02-17 Rock Kelly P. Fuel processor apparatus and method
US20050254941A1 (en) * 2004-05-06 2005-11-17 Hitachi Industries Co., Ltd. Inlet casing and suction passage structure
US20070113555A1 (en) * 2004-08-27 2007-05-24 Richard Carroni Mixer Assembly
US20070169760A1 (en) * 2006-01-23 2007-07-26 Rock Kelly P Fuel processor apparatus and method
US20070169773A1 (en) * 2006-01-23 2007-07-26 Lytesyde, Llc Medical liquid processor apparatus and method
US20090038582A1 (en) * 2007-08-07 2009-02-12 Lytesyde, Llc Fuel Processor Apparatus and Method
US20090065957A1 (en) * 2005-04-15 2009-03-12 Chien-Pei Mao Integrated fuel injection and mixing systems for fuel reformers and methods of using the same
US20130187298A1 (en) * 2012-01-22 2013-07-25 Helpful Technologies, Inc. System for dissolving gases in fuel
US20150121886A1 (en) * 2013-03-08 2015-05-07 Rolls-Royce North American Technologies, Inc. Gas turbine engine afterburner
US11175046B2 (en) 2019-05-09 2021-11-16 General Electric Company Combustor premixer assembly including inlet lips

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4246757A (en) * 1979-03-27 1981-01-27 General Electric Company Combustor including a cyclone prechamber and combustion process for gas turbines fired with liquid fuel
FR2484020A1 (fr) * 1980-06-06 1981-12-11 Snecma Ensemble d'injection de carburant pour chambre de turboreacteur
CH680946A5 (enrdf_load_stackoverflow) * 1989-12-19 1992-12-15 Asea Brown Boveri
DE19532264C2 (de) * 1995-09-01 2001-09-06 Mtu Aero Engines Gmbh Einrichtung zur Aufbereitung eines Gemisches aus Brennstoff und Luft an Brennkammern für Gasturbinentriebwerke
US10976053B2 (en) * 2017-10-25 2021-04-13 General Electric Company Involute trapped vortex combustor assembly
US10976052B2 (en) * 2017-10-25 2021-04-13 General Electric Company Volute trapped vortex combustor assembly
CN108844098B (zh) * 2018-05-15 2021-01-12 中国科学院工程热物理研究所 一种基于蜗壳结构的燃烧室头部

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2097255A (en) * 1937-10-26 Method of and apparatus fob burn
US2438858A (en) * 1943-01-21 1948-03-30 Armstrong Siddeley Motors Ltd Liquid-fuel combustion chamber
US2560074A (en) * 1948-12-21 1951-07-10 Lummus Co Method and apparatus for burning fuel
US2560076A (en) * 1949-06-14 1951-07-10 Lummus Co Method and apparatus for burning fuel
GB675092A (en) * 1949-01-25 1952-07-02 Rolls Royce Improvements relating to combustion systems of gas-turbine engines
US2674846A (en) * 1950-12-18 1954-04-13 Lummus Co Combustion chamber with baffle means to control secondary air
US2698050A (en) * 1949-06-10 1954-12-28 Lummus Co Combustion for liquid fuels
GB726538A (en) * 1953-01-14 1955-03-23 Lucas Industries Ltd Liquid fuel vaporisers
GB765327A (en) * 1954-02-23 1957-01-09 Gen Electric Improvements relating to combustion chambers
US3121996A (en) * 1961-10-02 1964-02-25 Lucas Industries Ltd Liquid fuel combustion apparatus
US3242674A (en) * 1961-05-05 1966-03-29 Lucas Industries Ltd Liquid fuel combustion apparatus
US3483699A (en) * 1967-02-22 1969-12-16 Rolls Royce Fuel injector for a gas turbine engine

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2097255A (en) * 1937-10-26 Method of and apparatus fob burn
US2438858A (en) * 1943-01-21 1948-03-30 Armstrong Siddeley Motors Ltd Liquid-fuel combustion chamber
US2560074A (en) * 1948-12-21 1951-07-10 Lummus Co Method and apparatus for burning fuel
GB675092A (en) * 1949-01-25 1952-07-02 Rolls Royce Improvements relating to combustion systems of gas-turbine engines
US2698050A (en) * 1949-06-10 1954-12-28 Lummus Co Combustion for liquid fuels
US2560076A (en) * 1949-06-14 1951-07-10 Lummus Co Method and apparatus for burning fuel
US2674846A (en) * 1950-12-18 1954-04-13 Lummus Co Combustion chamber with baffle means to control secondary air
GB726538A (en) * 1953-01-14 1955-03-23 Lucas Industries Ltd Liquid fuel vaporisers
GB765327A (en) * 1954-02-23 1957-01-09 Gen Electric Improvements relating to combustion chambers
US3242674A (en) * 1961-05-05 1966-03-29 Lucas Industries Ltd Liquid fuel combustion apparatus
US3121996A (en) * 1961-10-02 1964-02-25 Lucas Industries Ltd Liquid fuel combustion apparatus
US3483699A (en) * 1967-02-22 1969-12-16 Rolls Royce Fuel injector for a gas turbine engine

Cited By (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3804578A (en) * 1972-10-10 1974-04-16 D Robbins Cyclonic combustion burner
US3811278A (en) * 1973-02-01 1974-05-21 Gen Electric Fuel injection apparatus
US3944634A (en) * 1973-05-29 1976-03-16 John M. Anderson Carburetor idling system
US4036914A (en) * 1975-08-14 1977-07-19 John Hawryluk Liquid fuel mixing device
US4092826A (en) * 1975-12-06 1978-06-06 Rolls-Royce Limited Fuel injectors for gas turbine engines
US4388045A (en) * 1976-01-30 1983-06-14 Martin Marietta Corporation Apparatus and method for mixing and pumping fluids
US4177637A (en) * 1976-12-23 1979-12-11 Rolls-Royce Limited Inlet for annular gas turbine combustor
US4245961A (en) * 1978-09-08 1981-01-20 Martin Marietta Corporation Ejector utilizing a vortex flow
US4365951A (en) * 1980-06-13 1982-12-28 Jan Alpkvist Device for combustion of a volatile fuel with air
US4375801A (en) * 1981-10-01 1983-03-08 Eckman Donald E Charge mixing carburetor plate
FR2614361A1 (fr) * 1987-04-27 1988-10-28 Gen Electric Dispositif de carburation pour turbine a gaz
US4974416A (en) * 1987-04-27 1990-12-04 General Electric Company Low coke fuel injector for a gas turbine engine
US5805973A (en) * 1991-03-25 1998-09-08 General Electric Company Coated articles and method for the prevention of fuel thermal degradation deposits
US5891584A (en) * 1991-03-25 1999-04-06 General Electric Company Coated article for hot hydrocarbon fluid and method of preventing fuel thermal degradation deposits
US5343691A (en) * 1992-07-27 1994-09-06 General Electric Company Reducing thermal deposits in propulsion systems
US5609655A (en) * 1993-08-27 1997-03-11 Northern Research & Engineering Corp. Gas turbine apparatus
WO1995016881A1 (en) * 1993-12-17 1995-06-22 Abb Stal Ab Method and apparatus for atomizing liquid fuel
US5672187A (en) * 1994-11-23 1997-09-30 Cyclone Technologies Inc. Cyclone vortex system and process
US6648306B2 (en) 1998-03-18 2003-11-18 Lytesyde, Llc Fluid processing system and method
US6244573B1 (en) 1998-03-18 2001-06-12 Lytesyde, Llc Fluid processing system
US6347789B1 (en) 1998-03-18 2002-02-19 Lytesyde, L.L.C. Fluid processing system
US6113078A (en) * 1998-03-18 2000-09-05 Lytesyde, Llc Fluid processing method
US6253538B1 (en) 1999-09-27 2001-07-03 Pratt & Whitney Canada Corp. Variable premix-lean burn combustor
US20050035219A1 (en) * 2003-08-15 2005-02-17 Rock Kelly P. Fuel processor apparatus and method
US7104528B2 (en) 2003-08-15 2006-09-12 Lytesyde, Llc Fuel processor apparatus and method
US20050254941A1 (en) * 2004-05-06 2005-11-17 Hitachi Industries Co., Ltd. Inlet casing and suction passage structure
US7559742B2 (en) * 2004-05-06 2009-07-14 Hitachi Industries Co., Ltd. Inlet casing and suction passage structure
US20070113555A1 (en) * 2004-08-27 2007-05-24 Richard Carroni Mixer Assembly
US7780151B2 (en) * 2004-08-27 2010-08-24 Alstom Technology Ltd. Mixer assembly
US7547002B2 (en) * 2005-04-15 2009-06-16 Delavan Inc Integrated fuel injection and mixing systems for fuel reformers and methods of using the same
US20090065957A1 (en) * 2005-04-15 2009-03-12 Chien-Pei Mao Integrated fuel injection and mixing systems for fuel reformers and methods of using the same
US20070169760A1 (en) * 2006-01-23 2007-07-26 Rock Kelly P Fuel processor apparatus and method
US20070169773A1 (en) * 2006-01-23 2007-07-26 Lytesyde, Llc Medical liquid processor apparatus and method
US7681569B2 (en) 2006-01-23 2010-03-23 Lytesyde, Llc Medical liquid processor apparatus and method
US7717096B2 (en) 2006-01-23 2010-05-18 Lytesyde, Llc Fuel processor apparatus and method
US8028674B2 (en) 2007-08-07 2011-10-04 Lytesyde, Llc Fuel processor apparatus and method
US20090038582A1 (en) * 2007-08-07 2009-02-12 Lytesyde, Llc Fuel Processor Apparatus and Method
US20130187298A1 (en) * 2012-01-22 2013-07-25 Helpful Technologies, Inc. System for dissolving gases in fuel
US8641020B2 (en) * 2012-01-22 2014-02-04 Mark W. Baehr System for dissolving gases in fuel
US20150121886A1 (en) * 2013-03-08 2015-05-07 Rolls-Royce North American Technologies, Inc. Gas turbine engine afterburner
US9879862B2 (en) * 2013-03-08 2018-01-30 Rolls-Royce North American Technologies, Inc. Gas turbine engine afterburner
US10634352B2 (en) 2013-03-08 2020-04-28 Rolls-Royce North American Technologies Inc. Gas turbine engine afterburner
US11175046B2 (en) 2019-05-09 2021-11-16 General Electric Company Combustor premixer assembly including inlet lips
US11971172B2 (en) 2019-05-09 2024-04-30 General Electric Company Combustor premixer assembly including inlet lips

Also Published As

Publication number Publication date
CA922907A (en) 1973-03-20
IL34172A0 (en) 1970-05-21
DK130661C (enrdf_load_stackoverflow) 1975-08-25
NL7005473A (enrdf_load_stackoverflow) 1970-10-20
NO132165C (enrdf_load_stackoverflow) 1975-09-24
GB1302217A (enrdf_load_stackoverflow) 1973-01-04
FR2043412A5 (enrdf_load_stackoverflow) 1971-02-12
IL34172A (en) 1973-03-30
BE748911A (fr) 1970-09-16
DK130661B (da) 1975-03-17
NO132165B (enrdf_load_stackoverflow) 1975-06-16
CH526043A (de) 1972-07-31
DE2018485A1 (de) 1971-01-14

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