Patents by Inventor John Carl Jacobson
John Carl Jacobson has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20210404379Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes a liner at least partially defining a combustion chamber and having an inner wall defining an inner opening and an outer wall defining an outer opening. A boss is defined by the inner wall and extends around the inner opening toward the outer wall. A body of a ferrule extends along an axial direction through the outer opening and defines a central bore in fluid communication with the combustion chamber. A radial flange extends from the body along a radial direction and is positioned between the inner wall and the outer wall. The flange defines a flange diameter that is greater than an internal diameter of the outer opening such that the ferrule may slide along the radial direction but is restrained in the axial direction.Type: ApplicationFiled: June 24, 2021Publication date: December 30, 2021Inventors: Massimo Giovanni Giambra, Orin Hall, John Carl Jacobson
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Patent number: 10690345Abstract: A combustor assembly for use in a gas turbine engine includes a combustor liner that defines a combustion chamber and includes an axial combustion portion and a curved transition portion. The combustion liner also includes an inner surface and an outer surface and a first plurality of cooling channels defined between the inner and outer surfaces. The combustor assembly also includes a sleeve substantially circumscribing the combustor liner such that an annular cavity is defined between the combustor liner and the sleeve. The sleeve includes a second plurality of cooling channels defined therethrough that are configured to channel a fluid against the combustor liner outer surface.Type: GrantFiled: July 6, 2016Date of Patent: June 23, 2020Assignee: General Electric CompanyInventors: Joseph Douglas Monty, John Carl Jacobson, Stephen John Howell
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Patent number: 10502424Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly comprises a volute walled enclosure defining a spiral scroll pitch axis disposed at least partially circumferentially around a centerline axis of the gas turbine engine, in which the walled enclosure is defined around the pitch axis, and the walled enclosure defines a combustion chamber therewithin.Type: GrantFiled: August 10, 2017Date of Patent: December 10, 2019Assignee: General Electric CompanyInventors: Joseph Douglas Monty, John Carl Jacobson
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Patent number: 10473332Abstract: A combustor assembly for a gas turbine engine includes an inner liner, an outer liner, and a combustor dome. The inner liner, outer liner, and combustor dome together define at least in part a combustion chamber having an annulus height. Additionally, the combustor assembly includes a fuel-air injector hardware assembly positioned at least partially within an opening of the combustor dome. The fuel-air injector hardware assembly includes a heat shield located at least partially within the combustion chamber, the heat shield defining an outer diameter. A ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield may be at least about 1.5:1.Type: GrantFiled: February 25, 2016Date of Patent: November 12, 2019Assignee: General Electric CompanyInventors: David Andrew Hannwacker, Stephen John Howell, John Carl Jacobson, Joseph Douglas Monty
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Patent number: 10378771Abstract: A combustor assembly for a gas turbine engine includes a combustor dome and a combustion chamber liner attached to or formed integrally with the combustor dome. The combustion chamber liner extends between a forward end and an aft end, and together with the combustor dome at least partially defines a combustion chamber. The combustor assembly additionally includes a mounting assembly attached to the liner proximate the forward end of the liner for supporting the combustor dome and combustion chamber liner within the gas turbine engine relative to a structural component of the gas turbine engine.Type: GrantFiled: February 25, 2016Date of Patent: August 13, 2019Assignee: General Electric CompanyInventors: David Andrew Hannwacker, Stephen John Howell, John Carl Jacobson
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Patent number: 10317085Abstract: A combustor assembly for a gas turbine engine includes a combustor dome having a hot side and a cold side and at least in part defining a combustion chamber. The combustor assembly additionally includes a fuel-air injector hardware assembly having a first member and a second member. The first member is positioned at least partially adjacent to the cold side of the combustor dome and the second member is positioned at least partially adjacent to the hot side of the combustor dome. The first and second members together define an attachment interface joining the first member to the second member and mounting the fuel-air injector hardware assembly to the combustor dome. The attachment interface may be shielded from the combustion chamber to protect the attachment interface from an undesirable amount of thermal expansion and to maintain the materials within desired material operating temperature limits.Type: GrantFiled: February 25, 2016Date of Patent: June 11, 2019Assignee: General Electric CompanyInventors: David Andrew Hannwacker, Stephen John Howell, John Carl Jacobson
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Patent number: 10222065Abstract: A combustor assembly for a gas turbine engine includes a liner and a combustor dome. The combustor dome and liner together at least in part define a combustion chamber. The combustor dome includes a transition portion and a forward wall. The transition portion extends from the forward wall towards the liner. Additionally the transition portion may define an angle relative to the forward wall and/or may define a radius of curvature between the forward wall of the combustor dome and a flat of the transition portion of the combustor dome for increasing an aerodynamic efficiency of the combustor dome.Type: GrantFiled: February 25, 2016Date of Patent: March 5, 2019Assignee: General Electric CompanyInventors: David Andrew Hannwacker, Stephen John Howell, John Carl Jacobson
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Publication number: 20190049114Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly comprises a volute walled enclosure defining a spiral scroll pitch axis disposed at least partially circumferentially around a centerline axis of the gas turbine engine, in which the walled enclosure is defined around the pitch axis, and the walled enclosure defines a combustion chamber therewithin.Type: ApplicationFiled: August 10, 2017Publication date: February 14, 2019Inventors: Joseph Douglas Monty, John Carl Jacobson
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Publication number: 20180010796Abstract: A combustor assembly for use in a gas turbine engine includes a combustor liner that defines a combustion chamber and includes an axial combustion portion and a curved transition portion. The combustion liner also includes an inner surface and an outer surface and a first plurality of cooling channels defined between the inner and outer surfaces. The combustor assembly also includes a sleeve substantially circumscribing the combustor liner such that an annular cavity is defined between the combustor liner and the sleeve. The sleeve includes a second plurality of cooling channels defined therethrough that are configured to channel a fluid against the combustor liner outer surface.Type: ApplicationFiled: July 6, 2016Publication date: January 11, 2018Inventors: Joseph Douglas Monty, John Carl Jacobson, Stephen John Howell
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Publication number: 20170248314Abstract: A combustor assembly for a gas turbine engine includes a liner and a combustor dome. The combustor dome and liner together at least in part define a combustion chamber. The combustor dome includes a transition portion and a forward wall. The transition portion extends from the forward wall towards the liner. Additionally the transition portion may define an angle relative to the forward wall and/or may define a radius of curvature between the forward wall of the combustor dome and a flat of the transition portion of the combustor dome for increasing an aerodynamic efficiency of the combustor dome.Type: ApplicationFiled: February 25, 2016Publication date: August 31, 2017Inventors: David Andrew Hannwacker, Stephen John Howell, John Carl Jacobson
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Publication number: 20170248316Abstract: A combustor assembly for a gas turbine engine includes a combustor dome and a combustion chamber liner attached to or formed integrally with the combustor dome. The combustion chamber liner extends between a forward end and an aft end, and together with the combustor dome at least partially defines a combustion chamber. The combustor assembly additionally includes a mounting assembly attached to the liner proximate the forward end of the liner for supporting the combustor dome and combustion chamber liner within the gas turbine engine relative to a structural component of the gas turbine engine.Type: ApplicationFiled: February 25, 2016Publication date: August 31, 2017Inventors: David Andrew Hannwacker, Stephen John Howell, John Carl Jacobson
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Publication number: 20170248320Abstract: A combustor assembly for a gas turbine engine includes a combustor dome having a hot side and a cold side and at least in part defining a combustion chamber. The combustor assembly additionally includes a fuel-air injector hardware assembly having a first member and a second member. The first member is positioned at least partially adjacent to the cold side of the combustor dome and the second member is positioned at least partially adjacent to the hot side of the combustor dome. The first and second members together define an attachment interface joining the first member to the second member and mounting the fuel-air injector hardware assembly to the combustor dome. The attachment interface may be shielded from the combustion chamber to protect the attachment interface from an undesirable amount of thermal expansion and to maintain the materials within desired material operating temperature limits.Type: ApplicationFiled: February 25, 2016Publication date: August 31, 2017Inventors: David Andrew Hannwacker, Stephen John Howell, John Carl Jacobson
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Publication number: 20170248317Abstract: A combustor assembly for a gas turbine engine includes an inner liner, an outer liner, and a combustor dome. The inner liner, outer liner, and combustor dome together define at least in part a combustion chamber having an annulus height. Additionally, the combustor assembly includes a fuel-air injector hardware assembly positioned at least partially within an opening of the combustor dome. The fuel-air injector hardware assembly includes a heat shield located at least partially within the combustion chamber, the heat shield defining an outer diameter. A ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield may be at least about 1.5:1.Type: ApplicationFiled: February 25, 2016Publication date: August 31, 2017Inventors: David Andrew Hannwacker, Stephen John Howell, John Carl Jacobson, Joseph Douglas Monty
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Patent number: 7721437Abstract: A method facilitates assembling a combustor for a gas turbine engine, wherein the combustor includes a swirler assembly. The method comprises machining material to form a domeplate, positioning a sealplate including an overhanging portion against the domeplate, securing the sealplate in position relative to the domeplate with a welding process, and welding the swirler assembly to the domeplate.Type: GrantFiled: December 6, 2007Date of Patent: May 25, 2010Assignee: General Electric CompanyInventors: Stephen John Howell, John Carl Jacobson, Timothy P. McCaffrey, Barry Francis Barnes
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Patent number: 7448216Abstract: A method facilitates assembling a gas turbine engine. The method comprises coupling a combustor including a dome assembly and a combustor liner that extends downstream from the dome assembly to a combustor casing that is positioned radially outwardly from the combustor, coupling a ring support that includes a first radial flange, a second radial flange, and a plurality of beams that extend therebetween to the combustor casing, and coupling a primer nozzle including an injection tip to the combustor such that the primer nozzle extends axially through the dome assembly such that fuel may be discharged from the primer nozzle into the combustor during engine start-up operating conditions.Type: GrantFiled: July 5, 2006Date of Patent: November 11, 2008Assignee: General Electric CompanyInventors: Timothy P. McCaffrey, Stephen John Howell, John Carl Jacobson, Barry Francis Barnes
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Publication number: 20080209728Abstract: A method facilitates assembling a combustor for a gas turbine engine, wherein the combustor includes a swirler assembly. The method comprises machining material to form a domeplate, positioning a sealplate including an overhanging portion against the domeplate, securing the sealplate in position relative to the domeplate with a welding process, and welding the swirler assembly to the domeplate.Type: ApplicationFiled: December 6, 2007Publication date: September 4, 2008Inventors: Stephen John Howell, John Carl Jacobson, Timothy P. McCaffrey, Barry Francis Barnes
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Patent number: 7325403Abstract: A method for fabricating a dome assembly for a gas turbine engine combustor includes forming an annular dome plate including a plurality of substantially circular eyelets circumferentially spaced thereon, coupling a seal plate to the dome plate at each eyelet such that an opening defined in each seal plate is aligned substantially concentrically with respect to a respective eyelet, coupling a baffle to each seal plate such that an opening defined in each baffle is aligned substantially concentrically with respect to a respective eyelet, and coupling a swirler assembly having an integrally formed swirler and flare cone to each seal plate such that the flare cone extends at least partially through the baffle opening, and such that cooling air may be directed towards the flare cone through openings formed in the assembly.Type: GrantFiled: March 26, 2007Date of Patent: February 5, 2008Assignee: General Electric CompanyInventors: Aureen Cyr Currin, Kamil Bazyli Kaczorowski, John Carl Jacobson, Joseph Douglas Monty
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Patent number: 7310952Abstract: A method facilitates assembling a combustor for a gas turbine engine, wherein the combustor includes a swirler assembly. The method comprises machining material to form a domeplate, positioning a sealplate including an overhanging portion against the domeplate, securing the sealplate in position relative to the domeplate with a welding process, and welding the swirler assembly to the domeplate.Type: GrantFiled: October 17, 2003Date of Patent: December 25, 2007Assignee: General Electric CompanyInventors: Stephen John Howell, John Carl Jacobson, Timothy P. McCaffrey, Barry Francis Barnes
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Patent number: 7246494Abstract: A method for fabricating a dome assembly for a gas turbine engine combustor includes forming an annular dome plate including a plurality of substantially circular eyelets circumferentially spaced thereon, coupling a seal plate to the dome plate at each eyelet such that an opening defined in each seal plate is aligned substantially concentrically with respect to a respective eyelet, coupling a baffle to each seal plate such that an opening defined in each baffle is aligned substantially concentrically with respect to a respective eyelet, and coupling a swirler assembly having an integrally formed swirler and flare cone to each seal plate such that the flare cone extends at least partially through the baffle opening, and such that cooling air may be directed towards the flare cone through openings formed in the assembly.Type: GrantFiled: September 29, 2004Date of Patent: July 24, 2007Assignee: General Electric CompanyInventors: Aureen Cyr Currin, Kamil Bazyli Kaczorowski, John Carl Jacobson, Joseph Douglas Monty
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Patent number: 7216488Abstract: An ignition device assembly for a gas turbine engine combustor includes a body and a shroud. The body extends from an inlet end to an outlet end, and the shroud extends circumferentially around at least a portion of the body, and axially from a first end to a tip end. The shroud includes a tip portion and a body portion. The body portion includes a plurality of metering openings and a plurality of first outlet openings. The plurality of metering openings are for channeling cooling air to the ignition device body, and the plurality of first outlet openings are for channeling spent cooling air from the ignition device body. The tip portion includes a plurality of discharge openings extending therethrough for channeling cooling from the ignition device body. The plurality of first outlet openings are between the shroud tip portion and the plurality of shroud metering openings.Type: GrantFiled: July 20, 2004Date of Patent: May 15, 2007Assignee: General Electric CompanyInventors: Stephen John Howell, John Carl Jacobson, Barry Francis Barnes, Ramy Michael Souri