Patents by Inventor James W. Norris

James W. Norris 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).

  • Patent number: 10760483
    Abstract: A non-metallic tailcone in a tip turbine engine includes a tapered wall structure disposed about a central axis. The non-metallic tailcone is fastened to a structural frame in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.
    Type: Grant
    Filed: October 16, 2017
    Date of Patent: September 1, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Brian Merry, Gabriel L. Suciu, James W. Norris
  • Patent number: 10760423
    Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.
    Type: Grant
    Filed: April 6, 2018
    Date of Patent: September 1, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Gabriel L. Suciu, Stephen P. Muron, Ioannis Alvanos, Christopher M. Dye, Brian D. Merry, Arthur M. Salve, Jr., James W. Norris
  • Patent number: 10181132
    Abstract: A media player is provided. The media player comprises a communications interface, a memory store containing a plurality of personalized advertisements, and a media playback component. The targeted advertisements are refreshed by receiving updates from the communications interface during some of the intervals when the media player is connected to a network. The targeted advertisements are indexed by a plurality of characteristics, the first characteristic being a creation date of the targeted advertisements. The media playback component is configured to play a media content, wherein the media content is stored separately from the targeted advertisements, and to play one of the targeted advertisements in the memory store selected based on the characteristics of the one of the targeted advertisements.
    Type: Grant
    Filed: November 11, 2013
    Date of Patent: January 15, 2019
    Assignee: Sprint Communications Company L.P.
    Inventors: Jason R. Delker, John M. Everson, Michael A. Gailloux, Jarrod A. Nichols, James W. Norris
  • Patent number: 10091553
    Abstract: A video content distribution method is provided that comprises transmitting, by a video content distribution server, an initial portion of a scalable video file associated with a video to a mobile communication device via a first communication channel, transmitting an additional portion of the scalable video file to the mobile communication device via a second communication channel, and reconstructing, by the mobile communication device, at least some of the scalable video file based on reconstruction data using the initial portion and the additional portion of the scalable video file. The method also comprises playing, by the mobile communication device, at least a portion of the video at an initial resolution and frame rate based on the initial portion of the scalable video file and at least a portion of the video at an improved resolution and frame rate based on the reconstructed at least some of the scalable video file.
    Type: Grant
    Filed: January 10, 2014
    Date of Patent: October 2, 2018
    Assignee: Sprint Communications Company L.P.
    Inventors: Lyle T. Bertz, James W. Norris, Daniel J. Sershen
  • Publication number: 20180223668
    Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.
    Type: Application
    Filed: April 6, 2018
    Publication date: August 9, 2018
    Inventors: Gabriel L. Suciu, Stephen P. Muron, Ioannis Alvanos, Christopher M. Dye, Brian D. Merry, Arthur M. Salve, JR., James W. Norris
  • Publication number: 20180106194
    Abstract: A non-metallic tailcone in a tip turbine engine includes a tapered wall structure disposed about a central axis. The non-metallic tailcone is fastened to a structural frame in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.
    Type: Application
    Filed: October 16, 2017
    Publication date: April 19, 2018
    Inventors: Brian Merry, Gabriel L. Suciu, James W. Norris
  • Patent number: 9948452
    Abstract: A method and system are provided for converting an enhanced Long Range Navigational (eLORAN) signal to a Precision Time Protocol (PTP) signal. Network devices can be located within buildings and not have access to a GPS signal directly from a GPS satellite. Network devices may also be located in a line of sight of a GPS satellite but may lose the GPS signal. An adapter is provided that takes an eLORAN signal, when a GPS signal is lost or not available, and converts the signal into a PTP and other signals to act as timing, synchronization, and syntonization inputs into the network devices. In some cases, the network devices can have a PTP client to receive the PTP signal, one pulse per second signal, and a ten (10) megahertz frequency signal. In other cases, the network devices do not have a PTP client, but can receive a time of day message, one pulse per second signal, and the 10 megahertz frequency signal.
    Type: Grant
    Filed: October 23, 2013
    Date of Patent: April 17, 2018
    Assignee: Sprint Communications Company, L.P.
    Inventors: Timothy Hugh Pearson, James W. Norris, Steven Kenneth Guthrie
  • Patent number: 9938831
    Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.
    Type: Grant
    Filed: October 28, 2011
    Date of Patent: April 10, 2018
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Stephen P. Muron, Ioannis Alvanos, Christopher M. Dye, Brian D. Merry, Arthur M. Salve, James W. Norris
  • Patent number: 9879543
    Abstract: A cooling system for cooling a fluid reaction apparatus of a gas turbine engine includes a vapor cooling subsystem and a film cooling subsystem. The vapor cooling subsystem has a vaporization section and a condenser section for cooling a portion of the fluid reaction apparatus. The condenser section is cooled by a fluid. The film cooling subsystem is configured for cooling a portion of the fluid reaction apparatus by discharging fluid out of openings defined in the fluid reaction apparatus. At least a portion of the fluid used to cool the condenser section of the vapor cooling subsystem is discharged out of the openings of the film cooling subsystem.
    Type: Grant
    Filed: July 14, 2009
    Date of Patent: January 30, 2018
    Assignee: United Technologies Corporation
    Inventors: James W. Norris, James D. Hill
  • Patent number: 9845727
    Abstract: A non-metallic tailcone (202) in a tip turbine engine includes a tapered wall structure disposed (208) about a central axis. The non-metallic tailcone is fastened to a structural frame (44) in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.
    Type: Grant
    Filed: December 1, 2004
    Date of Patent: December 19, 2017
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, James W. Norris, Brian Merry
  • Patent number: 9790859
    Abstract: A gas turbine engine radial impeller includes first and second impeller portions that are secured to one another along a neutral bending plane of the radial impeller. A vapor cooling cavity is provided between the first and second impeller portions. The neutral bending plane is arranged in the vapor cooling cavity.
    Type: Grant
    Filed: October 27, 2014
    Date of Patent: October 17, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: James W. Norris
  • Patent number: 9541092
    Abstract: A tip turbine engine provides increased efficiency while eliminating or reducing the number of axial compressor stages by moving the core airflow inlet aft of the fan. As a result, the core airflow entering the core airflow inlet is the fan exhaust, which is already at an increased pressure. A portion of the fan exhaust is guided radially inward, then axially forward and then radially outward through compressor chambers in the hollow fan blades for further, centrifugal compression.
    Type: Grant
    Filed: December 22, 2011
    Date of Patent: January 10, 2017
    Assignee: United Technologies Corporation
    Inventors: James W. Norris, Craig A. Nordeen
  • Patent number: 9273563
    Abstract: An integrally bladed rotor has an outer rim with a plurality of blades extending radially outwardly of the outer rim. A plurality of channels are formed radially inwardly of the outer rim. A discontinuity formed at a radially outer surface of the outer rim includes a first thin slot at a radially outer face of the outer rim with an enlarged seal holding area. A second thin slot is positioned radially inwardly of the seal holding. The first and second thin slots are thinner circumferentially than the enlarged seal holding area. A seal is inserted into the seal holding area. The seal does not extend into the first and second thin slots, nor into the channels.
    Type: Grant
    Filed: August 14, 2012
    Date of Patent: March 1, 2016
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, James W. Norris
  • Publication number: 20150308342
    Abstract: A gas turbine engine radial impeller includes first and second impeller portions that are secured to one another along a neutral bending plane of the radial impeller. A vapor cooling cavity is provided between the first and second impeller portions. The neutral bending plane is arranged in the vapor cooling cavity.
    Type: Application
    Filed: October 27, 2014
    Publication date: October 29, 2015
    Inventor: James W. Norris
  • Patent number: 9133720
    Abstract: An integrally bladed rotor for a gas turbine engine includes at least one discontinuity formed in an outer face of an outer rim. The discontinuity reduces hoop stress in the outer rim.
    Type: Grant
    Filed: December 28, 2007
    Date of Patent: September 15, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, James W. Norris
  • Patent number: 9109537
    Abstract: A tip turbine engine assembly (8) includes a fan (32) rotatable in a fan plane (22) about an engine centerline (112). The fan (32) includes a fan blade (34) that defines a core airflow passage therethrough. An engine case (10) surrounds and supports the fan and engine. A plurality of engine mounts (20) for mounting the engine to an aircraft are positioned circumferentially about the outside of the engine case in a single mounting plane (22) that is perpendicular to the engine centerline.
    Type: Grant
    Filed: December 4, 2004
    Date of Patent: August 18, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, James W. Norris, Brian Merry
  • Patent number: 9003768
    Abstract: A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.
    Type: Grant
    Filed: February 8, 2011
    Date of Patent: April 14, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian Merry, James W. Norris, Steven J. Sirica
  • Patent number: 8992168
    Abstract: An inner diameter vane seal for a gas turbine engine comprises an annular, ring-like body having inner and outer diameter rims, forward and aft faces and an air passage. The outer diameter rim extends circumferentially for engaging inner diameter ends of stator vanes. The inner diameter rim extends circumferentially and is spaced radially from the inner outer diameter rim. The forward and aft faces extend radially between the outer diameter rim and the inner diameter rim. The air passage extends from the forward face to the aft face between the inner and outer diameter rims.
    Type: Grant
    Filed: October 28, 2011
    Date of Patent: March 31, 2015
    Assignee: United Technologies Corporation
    Inventors: James W. Norris, Joseph W. Bridges, Jr.
  • Patent number: 8976750
    Abstract: Systems, methods, and computer-readable media for precision time protocol (PTP) frequency and phase synchronization to unanchored sites over non on-path supported networks are provided. In embodiments, the method includes continuously measuring one-way delay (OWD) and delay offset from a host site to an anchored site to determine a dynamic corrective offset (DCO). One of a plurality of unanchored sites is identified. In embodiments, the DCO is applied to PTP sync or PTP follow-up messages communicated from the host site to the identified unanchored site. The clocks associated with the unanchored sites are synchronized to the host clock.
    Type: Grant
    Filed: January 16, 2013
    Date of Patent: March 10, 2015
    Assignee: Sprint Communications Company L.P.
    Inventors: Timothy Hugh Pearson, James W. Norris, Christian Erik Seagren, Steven Kenneth Guthrie
  • Patent number: 8967945
    Abstract: A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide vane. In one embodiment, the inlet guide vanes each include a pivotably mounted flap that is variable independently of the flaps of at least some of the other inlet guide vanes. In another embodiment, the inlet guide vanes each include at least one fluid outlet or nozzle directing pressurized air, as controlled by the associated actuator, to control inlet distortion.
    Type: Grant
    Filed: December 23, 2013
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Craig A. Nordeen, James W. Norris