Patents by Inventor Jeff Howe

Jeff Howe 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: 20210003019
    Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.
    Type: Application
    Filed: September 14, 2020
    Publication date: January 7, 2021
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Jeff Howe, Luis Tapia
  • Patent number: 10830052
    Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.
    Type: Grant
    Filed: September 15, 2016
    Date of Patent: November 10, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jeff Howe, Luis Tapia
  • Patent number: 10577954
    Abstract: Vane impingement tubes having blockage deterrent features are provided, as turbine nozzles containing blockage-resistant vane impingement tubes. In an embodiment, the turbine nozzle includes inner and outer annular endwalls, and turbine nozzle vanes arranged in an annular array between the outer and inner annular endwalls. Vane impingement tubes are inserted into the turbine nozzle vanes. The vane impingement tubes each includes a tube body, an impingement outlet formed in the tube body and configured to discharge airflow for impingement against one of the turbine nozzle vanes, a first flow-turning feature located in the tube body, and an inlet formed in the tube body and configured receive cooling airflow in a substantially radial direction. The first flow-turning feature is shaped and positioned to turn the airflow received through the inlet in a substantially axial direction, which is perpendicular to the radial direction, prior to discharge through the impingement outlet.
    Type: Grant
    Filed: March 27, 2017
    Date of Patent: March 3, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Harry Lester Kington, Daniel C. Crites, Jeff Howe
  • Publication number: 20200011186
    Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.
    Type: Application
    Filed: August 29, 2019
    Publication date: January 9, 2020
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Jeff Howe, Luis Tapia
  • Publication number: 20180274377
    Abstract: Vane impingement tubes having blockage deterrent features are provided, as turbine nozzles containing blockage-resistant vane impingement tubes. In an embodiment, the turbine nozzle includes inner and outer annular endwalls, and turbine nozzle vanes arranged in an annular array between the outer and inner annular endwalls. Vane impingement tubes are inserted into the turbine nozzle vanes. The vane impingement tubes each includes a tube body, an impingement outlet formed in the tube body and configured to discharge airflow for impingement against one of the turbine nozzle vanes, a first flow-turning feature located in the tube body, and an inlet formed in the tube body and configured receive cooling airflow in a substantially radial direction. The first flow-turning feature is shaped and positioned to turn the airflow received through the inlet in a substantially axial direction, which is perpendicular to the radial direction, prior to discharge through the impingement outlet.
    Type: Application
    Filed: March 27, 2017
    Publication date: September 27, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Harry Lester Kington, Daniel C. Crites, Jeff Howe
  • Publication number: 20180073368
    Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.
    Type: Application
    Filed: September 15, 2016
    Publication date: March 15, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Jeff Howe, Luis Tapia
  • Patent number: 9638103
    Abstract: An inlet particle separator system for an engine includes a hub section, a shroud section, a splitter, and a plasma flow control actuator. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The plasma flow control actuator is coupled to the hub section and is disposed between the air inlet and the splitter.
    Type: Grant
    Filed: July 26, 2013
    Date of Patent: May 2, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jeff Howe, Nick Nolcheff, Harry Lester Kington
  • Patent number: 9631554
    Abstract: An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity.
    Type: Grant
    Filed: January 14, 2014
    Date of Patent: April 25, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jeff Howe, Harry Lester Kington, Nick Nolcheff
  • Patent number: 9596240
    Abstract: A subscriber login server is used for managing a subscriber login session. The login server is associated with a DHCP server for configuring a premise equipment device and operator-managed device. A subscriber login client at the premise equipment device securely communicates login username and password identifiers to the subscriber login server without using PPP technology. The login server retrieves matching identifiers from a RADIUS server and authorizes service with messages to the DHCP server and the CMTS. The login client can emulate a PPP login client so that a user's interface is similar to a PPPoE client. However, a layer-3 CMTS can be used instead of a layer-2 CMTS. In addition, subscriber authentication and accounting using RADIUS are preserved, positive network access control at the CMTS is maintained, and native IP traffic is routed or switched for maximum performance and QoS treatment.
    Type: Grant
    Filed: December 29, 2009
    Date of Patent: March 14, 2017
    Assignee: ARRIS Enterprises, Inc.
    Inventors: Erich Arnold, Thomas J Cloonan, Jeff Howe
  • Patent number: 9546603
    Abstract: A cooling arrangement is provided for a gas turbine engine with a turbine section. The cooling arrangement includes a first conduit to receive cooling air that includes particles; a separator system coupled to the first conduit to receive the cooling air and configured to remove at least a portion of the particles to result in relatively clean cooling air and scavenge air including the portion of the particles; and a second conduit coupled to the separator system and configured to direct the relatively clean cooling air to the turbine section.
    Type: Grant
    Filed: April 3, 2014
    Date of Patent: January 17, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: John Meier, Daniel C. Crites, Yogendra Yogi Sheoran, Mark C. Morris, Jeff Howe, Ardeshir Riahi
  • Patent number: 9479352
    Abstract: A packet data flow processor applies a first level of Data Over Cable Service Interface Specification (DOCSIS) processing to packet flows that are not from trusted sources, and applies a second level of DOCSIS processing, simpler than the first level, to packet flows from the trusted sources.
    Type: Grant
    Filed: June 25, 2009
    Date of Patent: October 25, 2016
    Assignee: ARRIS Enterprises, Inc.
    Inventors: Thomas J. Cloonan, Jeff Howe, Carol Ansley, Mark Bugajski, Charles Cheevers, Ian Wheelock
  • Publication number: 20150354461
    Abstract: A cooling arrangement is provided for a gas turbine engine with a turbine section. The cooling arrangement includes a first conduit to receive cooling air that includes particles; a separator system coupled to the first conduit to receive the cooling air and configured to remove at least a portion of the particles to result in relatively clean cooling air and scavenge air including the portion of the particles; and a second conduit coupled to the separator system and configured to direct the relatively clean cooling air to the turbine section.
    Type: Application
    Filed: April 3, 2014
    Publication date: December 10, 2015
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: John Meier, Daniel C. Crites, Yogendra Yogi Sheoran, Mark C. Morris, Jeff Howe, Ardeshir Riahi
  • Publication number: 20150198090
    Abstract: An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity.
    Type: Application
    Filed: January 14, 2014
    Publication date: July 16, 2015
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Jeff Howe, Harry Lester Kington, Nick Nolcheff
  • Publication number: 20150030435
    Abstract: An inlet particle separator system for an engine includes a hub section, a shroud section, a splitter, and a plasma flow control actuator. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The plasma flow control actuator is coupled to the hub section and is disposed between the air inlet and the splitter.
    Type: Application
    Filed: July 26, 2013
    Publication date: January 29, 2015
    Inventors: Jeff Howe, Nick Nolcheff, Harry Lester Kington
  • Patent number: 8801364
    Abstract: An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.
    Type: Grant
    Filed: June 4, 2010
    Date of Patent: August 12, 2014
    Assignee: Honeywell International Inc.
    Inventors: Mark C. Morris, Alexander MirzaMoghadam, Khosro Molla Hosseini, Kin Poon, Jeff Howe, Alan G. Tiltman
  • Patent number: 8780709
    Abstract: Bandwidth is assigned to subscribers of a data network by applying logic of one or more network devices to sample bits of information communicated over a network communication medium to identify if there is a network congestion condition or an extremely lightly loaded condition. The maximum bandwidth assigned to a subscriber is below a normative maximum bandwidth assigned to the subscriber if the network is congested and the logic of the one or more network devices identifies the subscriber as a heavy bandwidth user. The maximum bandwidth assigned to a subscriber is above the normative maximum bandwidth if the network is extremely lightly loaded and the subscriber is a heavy bandwidth user.
    Type: Grant
    Filed: April 20, 2009
    Date of Patent: July 15, 2014
    Assignee: ARRIS Enterprises, Inc.
    Inventors: Ayham Al-Banna, Carol Ansley, Thomas J. Cloonan, Jeff Howe
  • Publication number: 20130051974
    Abstract: Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction.
    Type: Application
    Filed: August 25, 2011
    Publication date: February 28, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Kin Poon, Jeff Howe, Michael T. Todd Barton, Frank Mignano, Mahmoud Mansour, Nick Nolcheff, Scott Taylor, Steve Trzcinski, Ardeshir Riahi, Jeff Guymon, Alan Hemmingson, Alex Mirzamoghadam
  • Patent number: 8300640
    Abstract: A data communication system includes multiple Media Access Control (MAC) units, multiple physical layer (PHY) interface units, and logic to communicate between the MAC units and the PHY units using a single tunneling protocol over Internet Protocol (IP).
    Type: Grant
    Filed: April 20, 2009
    Date of Patent: October 30, 2012
    Assignee: ARRIS Group, Inc.
    Inventors: Ayham Al-Banna, Erich Arnold, Thomas J. Cloonan, Jeff Howe
  • Patent number: 8262342
    Abstract: 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: Grant
    Filed: July 10, 2008
    Date of Patent: September 11, 2012
    Assignee: Honeywell International Inc.
    Inventors: Mark C. Morris, Jeff Howe, Greg Heitland, Jason Smoke
  • Patent number: 8206080
    Abstract: A gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for receiving hot gas ingested from the hot gas flow path through the annular space and for recirculating the ingested hot gas back through the annular space to the hot gas flow path. The contoured shroud includes a base wall extending radially inwardly from the duct wall, an inboard wall extending from the base wall in an axial direction toward the rotor, and an end wall extending from the inboard wall in a radially outward direction. The end wall terminates in a circumferentially extending free edge disposed in proximity to the annular space. The end wall defines an opening.
    Type: Grant
    Filed: June 12, 2008
    Date of Patent: June 26, 2012
    Assignee: Honeywell International Inc.
    Inventors: Jeff Howe, Mark C. Morris, Khosro Molla Hosseini