Patents by Inventor Jason Smoke
Jason Smoke 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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Patent number: 9068469Abstract: A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.Type: GrantFiled: September 1, 2011Date of Patent: June 30, 2015Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Bradley Reed Tucker, Jason Smoke, Mark C. Morris
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Patent number: 9033670Abstract: Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.Type: GrantFiled: April 11, 2012Date of Patent: May 19, 2015Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Don Mittendorf, David K. Jan, Jason Smoke, Amandine Miner
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Publication number: 20150075178Abstract: A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform. The platform has a leading edge, a trailing edge, a suction side edge, and a pressure side edge. The pressure side edge includes a first concave portion.Type: ApplicationFiled: September 17, 2013Publication date: March 19, 2015Inventors: Steve Halfmann, Mark C. Morris, Jason Smoke, Brandan Wakefield, Bob Mitlin
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Patent number: 8668442Abstract: A turbine nozzle is provided and includes a first ring having a first microstructure, a vane extending from the first ring, a first porous zone between the first ring and the vane that is more porous than the first microstructure to attenuate thermo-mechanical fatigue cracking between the vane and the first ring. Methods of manufacturing the turbine nozzle are also provided.Type: GrantFiled: June 30, 2010Date of Patent: March 11, 2014Assignee: Honeywell International Inc.Inventors: Mark C. Morris, Daniel Ryan, Donald G. Godfrey, Jason Smoke
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Patent number: 8616832Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.Type: GrantFiled: November 30, 2009Date of Patent: December 31, 2013Assignee: Honeywell International Inc.Inventors: Jason Smoke, Bradley Reed Tucker, Bob Mitlin, Dan Crites, Rajiv Rana, Alexander MirzaMoghadam
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Publication number: 20130272882Abstract: Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.Type: ApplicationFiled: April 11, 2012Publication date: October 17, 2013Applicant: Honeywell International Inc.Inventors: Don Mittendorf, David K. Jan, Jason Smoke, Amandine Miner
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Patent number: 8534076Abstract: A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.Type: GrantFiled: June 9, 2009Date of Patent: September 17, 2013Assignee: Honeywell Internationl Inc.Inventors: Gregory O. Woodcock, Bradley Reed Tucker, Jason Smoke, Stony Kujala, Terrel Kuhn
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Patent number: 8408446Abstract: Embodiments of a method for manufacturing a turbine engine component are provided, as are embodiments of a thermal growth constraint tool for the manufacture of turbine engine components. In one embodiment, the method includes the steps of obtaining a plurality of arched pieces, arranging the plurality of arched pieces in a ring formation, and bonding the plurality of arched pieces together to produce a monolithic ring by heating the ring formation to a predetermined bonding temperature while constraining the outward radial growth thereof.Type: GrantFiled: February 13, 2012Date of Patent: April 2, 2013Assignee: Honeywell International Inc.Inventors: Jason Smoke, David K. Jan, Don Mittendorf
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Patent number: 8393858Abstract: A coupling assembly for a turbine shroud is provided. The coupling assembly comprises a rotatable positioning block having a first surface, and a biasing spring having a second surface, the second surface generally facing the first surface, and the biasing spring adapted to exert a force toward the positioning block when compressed.Type: GrantFiled: March 13, 2009Date of Patent: March 12, 2013Assignee: Honeywell International Inc.Inventors: Jason Smoke, Michael Kahrs
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Publication number: 20130058768Abstract: A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.Type: ApplicationFiled: September 1, 2011Publication date: March 7, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Bradley Reed Tucker, Jason Smoke, Mark C. Morris
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Patent number: 8388307Abstract: Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE.Type: GrantFiled: July 21, 2009Date of Patent: March 5, 2013Assignee: Honeywell International Inc.Inventors: Jason Smoke, Stony Kujala, Gregory O. Woodcock, Bradley Reed Tucker
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Patent number: 8381533Abstract: An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cooling air. The self-supporting seal plate comprises a plurality of shaped cooling holes in fluid communication with the flow of cooling air emanating from the TOBI. The rotating disk includes a plurality of turbine blade slots formed therein. The plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to the plurality of turbine blades. The plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment and optimized to minimize radial and hoop stresses.Type: GrantFiled: April 30, 2009Date of Patent: February 26, 2013Assignee: Honeywell International Inc.Inventors: Jason Smoke, Bob Mitlin, Alexander MirzaMoghadam
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Publication number: 20120228803Abstract: Embodiments of a method are provided for fabricating a high temperature castable article, such as a casting mold or a core. In one embodiment, the method includes the steps of providing a suspension containing a plurality of ceramic particles and a photo-curable monomer; photo-curing selected portions of the suspension to produce a green body coated, at least partially, with uncured suspension; and removing the uncured suspension from the green body under process conditions at which the viscosity of the uncured suspension is reduced. The process conditions include exposing the green body to one of the group consisting of: (i) microwave energy sufficient to excite a dipole moment of the uncured suspension and (ii) sonic energy sufficient to induce shear-thinning of the uncured suspension. The green body is then heat treated to produce the high temperature castable article.Type: ApplicationFiled: March 8, 2011Publication date: September 13, 2012Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Wil Baker, Dennis Wolski
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Patent number: 8262342Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.Type: GrantFiled: July 10, 2008Date of Patent: September 11, 2012Assignee: Honeywell International Inc.Inventors: Mark C. Morris, Jeff Howe, Greg Heitland, Jason Smoke
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Patent number: 8147197Abstract: A turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent the turbine blade and a lower surface comprising a first rib, the cavity extending into the first rib, the first rib coupled to the lower surface, tapering as it extends away from the turbine blade, and comprising a first port extending from the cavity to the upper surface.Type: GrantFiled: March 10, 2009Date of Patent: April 3, 2012Assignee: Honeywell International, Inc.Inventors: Mark C. Morris, Jason Smoke, Jeff Howe, Bob Mitlin
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Publication number: 20120003086Abstract: A turbine nozzle is provided and includes a first ring having a first microstructure, a vane extending from the first ring, a first porous zone between the first ring and the vane that is more porous than the first microstructure to attenuate thermo-mechanical fatigue cracking between the vane and the first ring. Methods of manufacturing the turbine nozzle are also provided.Type: ApplicationFiled: June 30, 2010Publication date: January 5, 2012Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Mark C. Morris, Daniel Ryan, Donald G. Godfrey, Jason Smoke
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Patent number: 8047771Abstract: Turbine nozzles and methods of manufacturing the turbine nozzles are provided. In an embodiment, by way of example only, a turbine nozzle includes a first ring, a vane, and a first joint. The first ring comprises a single unitary component and having a first opening and including a first metal alloy. The vane includes a first end disposed in the first opening and includes a second metal alloy. The first joint is formed in the first opening between the first ring and the vane and includes a first braze layer and an oxide layer. The first braze layer is disposed adjacent to the oxide layer, and the first braze layer and the oxide layer are disposed between the first ring and the vane.Type: GrantFiled: November 17, 2008Date of Patent: November 1, 2011Assignee: Honeywell International Inc.Inventors: Bradley Reed Tucker, Mark C. Morris, Jason Smoke, Daniel Ryan
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Publication number: 20110129342Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.Type: ApplicationFiled: November 30, 2009Publication date: June 2, 2011Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Bradley Reed Tucker, Bob Mitlin, Dan Crites, Rajiv Rana, Alexander MirzaMoghadam
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Publication number: 20110020118Abstract: Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE.Type: ApplicationFiled: July 21, 2009Publication date: January 27, 2011Applicant: Honeywell International Inc.Inventors: Jason Smoke, Stony Kujala, Gregory O. Woodcock, Bradley Reed Tucker
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Publication number: 20100307166Abstract: A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.Type: ApplicationFiled: June 9, 2009Publication date: December 9, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Gregory O. Woodcock, Bradley Reed Tucker, Jason Smoke, Stony Kujala, Terrel Kuhn