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).

  • Publication number: 20200182471
    Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.
    Type: Application
    Filed: January 7, 2020
    Publication date: June 11, 2020
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, David K. Jan, Mark Matwey
  • Patent number: 10677084
    Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.
    Type: Grant
    Filed: February 20, 2018
    Date of Patent: June 9, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, Kent L. Kime, Blake Petersen, Luke Zurmehly
  • Patent number: 10669862
    Abstract: An airfoil includes a leading edge and an opposing trailing edge. The airfoil includes a pressure sidewall and an opposing suction sidewall. A leading edge cavity is defined between the pressure sidewall and the suction sidewall. The leading edge cavity has a first end opposite the leading edge and a second end defined at a rib. The airfoil includes at least one pin structure defined in the leading edge cavity between the first end and the second end. The at least one pin structure includes a main body and a first branch. The main body is coupled to the second end and extends toward the first end. The first branch extends from the main body toward the first end.
    Type: Grant
    Filed: July 13, 2018
    Date of Patent: June 2, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Luis Tapia, Jason Smoke
  • Patent number: 10669617
    Abstract: Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (TDISK_PROCESS_MIN) for the hub disk and a maximum critical temperature for the rotor blades (TBLADE_MAX) is established such that TBLADE_MAX is less than TDIsK_PROCESS_MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than TDISK_PROCESS_MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below TBLADE_MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.
    Type: Grant
    Filed: August 1, 2019
    Date of Patent: June 2, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Christopher David Gatto, Jude Miller, Benjamin Dosland Kamrath, Don Mittendorf, Jason Smoke, Mark C. Morris
  • Patent number: 10655859
    Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.
    Type: Grant
    Filed: January 11, 2017
    Date of Patent: May 19, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, David K. Jan, Mark Matwey
  • Publication number: 20200140983
    Abstract: Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (TDISK_PROCESS_MIN) for the hub disk and a maximum critical temperature for the rotor blades (TBLADE_MAX) is established such that TBLADE_MAX is less than TDISK_PROCESS_MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than TDISK_PROCESS_MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below TBLADE_MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.
    Type: Application
    Filed: August 1, 2019
    Publication date: May 7, 2020
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Christopher David Gatto, Jude Miller, Benjamin Dosland Kamrath, Don Mittendorf, Jason Smoke, Mark C. Morris
  • Publication number: 20200116037
    Abstract: A turbine shroud assembly includes a shroud support and a shroud segment. The shroud support structure includes a forward support rail and an aft support rail. The forward support rail includes forward first engagement structures and the aft support rail includes aft first engagement structures. The shroud segment includes a forward segment rail and an aft segment rail. The forward segment rail includes forward second engagement structures positioned on a forward segment rail periphery and the aft segment rail includes second engagement structures positioned on an aft segment rail periphery. The forward first engagement structures radially and circumferentially engage with the forward second engagement structures and the aft first engagement structures radially and circumferentially engage with the aft second engagement structures to radially and circumferentially interlock the shroud segment to the shroud support structure.
    Type: Application
    Filed: October 16, 2018
    Publication date: April 16, 2020
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Luke Zurmehly, Jason Smoke, Kent L. Kime, Blake Petersen
  • Patent number: 10563520
    Abstract: A turbine component with shaped cooling pins is provided. The turbine component includes at least one cooling circuit defined within the turbine component, the at least one cooling circuit in fluid communication with a source of a cooling fluid. The turbine component includes at least one shaped cooling pin disposed in the at least one cooling circuit. The at least one shaped cooling pin has a first end and a second end extending along an axis. The first end has a first curved surface defined by a minor diameter and the second end has a second curved surface defined by a major diameter. The first curved surface is upstream in the cooling fluid and the minor diameter is less than the major diameter.
    Type: Grant
    Filed: March 31, 2017
    Date of Patent: February 18, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Benjamin Dosland Kamrath, Jason Smoke, Daniel C. Crites
  • Publication number: 20200018172
    Abstract: An airfoil includes a leading edge and an opposing trailing edge. The airfoil includes a pressure sidewall and an opposing suction sidewall. A leading edge cavity is defined between the pressure sidewall and the suction sidewall. The leading edge cavity has a first end opposite the leading edge and a second end defined at a rib. The airfoil includes at least one pin structure defined in the leading edge cavity between the first end and the second end. The at least one pin structure includes a main body and a first branch. The main body is coupled to the second end and extends toward the first end. The first branch extends from the main body toward the first end.
    Type: Application
    Filed: July 13, 2018
    Publication date: January 16, 2020
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Luis Tapia, Jason Smoke
  • Publication number: 20200003059
    Abstract: A cooling circuit to receive a cooling fluid includes at least one shaped cooling pin disposed in the cooling circuit. The at least one shaped cooling pin has a first end and a second end extending along an axis. The first end has a first curved surface defined by a minor diameter and the second end has a second curved surface defined by a major diameter. The first curved surface is to be upstream in the cooling fluid and the minor diameter is less than the major diameter.
    Type: Application
    Filed: August 20, 2019
    Publication date: January 2, 2020
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Benjamin Dosland Kamrath, Jason Smoke, Daniel C. Crites
  • Patent number: 10399176
    Abstract: Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step.
    Type: Grant
    Filed: July 13, 2017
    Date of Patent: September 3, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Amandine Miner, David K. Jan, Don Mittendorf, Jason Smoke
  • Patent number: 10385433
    Abstract: Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (TDISK_PROCESS_MIN) for the hub disk and a maximum critical temperature for the rotor blades (TBLADE_MAX) is established such that TBLADE_MAX is less than TDISK_PROCESS_MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than TDISK_PROCESS_MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below TBLADE_MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: August 20, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Christopher David Gatto, Jude Miller, Benjamin Dosland Kamrath, Don Mittendorf, Jason Smoke, Mark C. Morris
  • Patent number: 10294804
    Abstract: Dual alloy Gas Turbine Engine (GTE) rotors and method for producing GTE rotors are provided. In one embodiment, the method include includes arranging bladed pieces in an annular grouping or ring formation such that shank-to-shank junctions are formed between circumferentially-adjacent bladed pieces. A first or bonding alloy is deposited along the shank-to-shank junctions utilizing a localized fusion deposition process to produce a plurality of alloy-filled joints, which join the bladed pieces in a bonded blade ring. The bonding alloy is preferably selected to have a ductility higher than and a melt point lower than the alloy from which the bladed pieces are produced. After deposition of the first alloy and formation of the alloy-filled joints, a hub disk is inserted into the central opening of the bonded blade ring. The hub disk and blade ring are then bonded utilizing, for example, a Hot Isostatic Pressing process.
    Type: Grant
    Filed: August 11, 2015
    Date of Patent: May 21, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, Eric Blumer, David K. Jan, Robbie Joseph Adams, Harry Lester Kington
  • Patent number: 10260355
    Abstract: A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.
    Type: Grant
    Filed: March 7, 2016
    Date of Patent: April 16, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, David K Jan, Amandine Miner, Deanna Pinar Chase, Michael Kahrs, Lorenzo Crosatti
  • Publication number: 20190022781
    Abstract: Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.
    Type: Application
    Filed: November 14, 2017
    Publication date: January 24, 2019
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Bradley Reed Tucker, Ardeshir Riahi, Jason Smoke, Ed Zurmehly
  • Publication number: 20190001448
    Abstract: Turbine wheels, turbine engines, and methods of fabricating the turbine wheels are provided. An exemplary method includes fabricating a turbine wheel that includes a rotor disk and a plurality of turbine blades operatively connected to the rotor disk through a blade mount. The method includes locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration. A rotor disk bonding surface geometry and a blade mount bonding surface geometry are designed based upon a stress analysis of the turbine wheel and locations of the cooling passage and cooling inlet. A rotor disk production configuration and a blade mount production configuration are generated based upon the preliminary configurations. A blade mount and a rotor disk are formed based upon the production configurations. A blade ring including a plurality of blade mounts is formed and bonded to the rotor disk.
    Type: Application
    Filed: June 30, 2017
    Publication date: January 3, 2019
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Michael Kahrs, Daniel C. Crites, Jude Miller, Steve Halfmann, Jason Smoke, Ardeshir Riahi, David K. Jan
  • Publication number: 20180363486
    Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.
    Type: Application
    Filed: February 20, 2018
    Publication date: December 20, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, Kent L. Kime, Blake Petersen, Luke Zurmehly
  • Publication number: 20180363499
    Abstract: A shroud assembly for a gas turbine engine includes a shroud support and a plurality of shroud segments that are attached to the shroud support. The shroud segment includes an internal cooling passage.
    Type: Application
    Filed: February 20, 2018
    Publication date: December 20, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, Kent L. Kime, Blake Petersen, Luke Zurmehly
  • Publication number: 20180283182
    Abstract: A turbine component with shaped cooling pins is provided. The turbine component includes at least one cooling circuit defined within the turbine component, the at least one cooling circuit in fluid communication with a source of a cooling fluid. The turbine component includes at least one shaped cooling pin disposed in the at least one cooling circuit. The at least one shaped cooling pin has a first end and a second end extending along an axis. The first end has a first curved surface defined by a minor diameter and the second end has a second curved surface defined by a major diameter. The first curved surface is upstream in the cooling fluid and the minor diameter is less than the major diameter.
    Type: Application
    Filed: March 31, 2017
    Publication date: October 4, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Benjamin Dosland Kamrath, Jason Smoke, Daniel C. Crites
  • Patent number: 10036254
    Abstract: Dual alloy bladed rotors are provided, as are methods for manufacturing dual alloy bladed rotors. In one embodiment, the method includes arranging bladed pieces in a ring formation such that contiguous bladed pieces contact along shank-to-shank bonding interfaces. The ring formation is positioned around a hub disk, which is contacted by the bladed pieces along a shank-to-hub bonding interface. A metallic sealing material is deposited between contiguous bladed pieces utilizing, for example, a laser welding process to produce an annular seal around the ring formation. A hermetic cavity is then formed, which is circumferentially bounded by the annular seal and which encloses the shank-to-shank and shank-to-hub bonding interface. Afterwards, a Hot Isostatic Pressing process is performed during which the ring formation and the hub disk are exposed to elevated pressures external to the hermetic cavity sufficient to diffusion bond the shank-to-shank and shank-to-hub bonding interface.
    Type: Grant
    Filed: November 12, 2015
    Date of Patent: July 31, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, David K. Jan, Don Mittendorf, Brent Ludwig, Amandine Miner, Deanna Pinar Chase