Patents by Inventor Eric J. Ward

Eric J. Ward 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: 10900376
    Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.
    Type: Grant
    Filed: January 14, 2020
    Date of Patent: January 26, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Eric J. Ward
  • Publication number: 20200149428
    Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.
    Type: Application
    Filed: January 14, 2020
    Publication date: May 14, 2020
    Inventor: Eric J. Ward
  • Patent number: 10605119
    Abstract: A turbine frame for a gas turbine engine according to an example of the present disclosure includes a turbine case, a bearing support housing that defines a receptacle, and a tie rod preloaded in compression between the turbine case and the bearing support housing.
    Type: Grant
    Filed: September 25, 2017
    Date of Patent: March 31, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Eric J. Ward
  • Patent number: 10570770
    Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.
    Type: Grant
    Filed: December 8, 2014
    Date of Patent: February 25, 2020
    Assignee: United Technologies Corporation
    Inventor: Eric J. Ward
  • Patent number: 10514102
    Abstract: A gas turbine engine includes a first rotor shaft and a second rotor shaft around the first rotor shaft. A knife edge seal is radially between the first rotor shaft and the second rotor shaft, and is connected to one of the first rotor shaft or the second rotor shaft. The knife edge seal is sized radially to form a gap between the knife edge seal and the other of the first rotor shaft or the second rotor shaft. A plurality of blades having a general airfoil shape is between the first rotor shaft and the second rotor shaft proximate the knife edge seal. The plurality of blades is connected to the first rotor shaft or the second rotor shaft, and a second gap is formed radially between the plurality of blades and the other of the first rotor shaft or the second rotor shaft.
    Type: Grant
    Filed: July 14, 2017
    Date of Patent: December 24, 2019
    Assignee: United Technologies Corporation
    Inventor: Eric J. Ward
  • Publication number: 20190093507
    Abstract: A turbine frame for a gas turbine engine according to an example of the present disclosure includes a turbine case, a bearing support housing that defines a receptacle, and a tie rod preloaded in compression between the turbine case and the bearing support housing.
    Type: Application
    Filed: September 25, 2017
    Publication date: March 28, 2019
    Inventor: Eric J. Ward
  • Publication number: 20190017604
    Abstract: A gas turbine engine includes a first rotor shaft and a second rotor shaft around the first rotor shaft. A knife edge seal is radially between the first rotor shaft and the second rotor shaft, and is connected to one of the first rotor shaft or the second rotor shaft. The knife edge seal is sized radially to form a gap between the knife edge seal and the other of the first rotor shaft or the second rotor shaft. A plurality of blades having a general airfoil shape is between the first rotor shaft and the second rotor shaft proximate the knife edge seal. The plurality of blades is connected to the first rotor shaft or the second rotor shaft, and a second gap is formed radially between the plurality of blades and the other of the first rotor shaft or the second rotor shaft.
    Type: Application
    Filed: July 14, 2017
    Publication date: January 17, 2019
    Inventor: Eric J. Ward
  • Publication number: 20160319693
    Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.
    Type: Application
    Filed: December 8, 2014
    Publication date: November 3, 2016
    Inventor: Eric J. Ward
  • Patent number: 9169849
    Abstract: A compressor section for use in a gas turbine engine has a plurality of compressor stages. Each compressor stage is provided with a rotor hub, and each rotor hub mounts a plurality of compressor blades. A rotor drum extends between adjacent rotor hubs. A plurality of stator stages have an outer ring and a radially inner ring. A plurality of vanes extend between the outer and inner rings. An inner surface of the inner ring is spaced by a gap from an outer surface of the rotor drum. The rotor drum is provided with a plurality of blades having a general airfoil shape to resist leakage across the gap.
    Type: Grant
    Filed: May 8, 2012
    Date of Patent: October 27, 2015
    Assignee: United Technologies Corporation
    Inventor: Eric J. Ward
  • Patent number: 8967952
    Abstract: A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first flow apertures extending axially therethrough, and a plurality of roller elements connected to an inner rotor platform. The first flow apertures are arranged circumferentially around the inner rotor platform. The duct blocker stator includes a plurality of second flow apertures extending axially therethrough, and a roller element track located radially within the inner rotor platform and in rolling contact with the roller elements. The second flow apertures are arranged circumferentially around an inner stator platform that is located axially adjacent to the inner rotor platform. The duct blocker rotor rotates relative to the duct blocker stator to regulate fluid flowing between the first flow apertures and the second flow apertures.
    Type: Grant
    Filed: December 22, 2011
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: James Jones, John H. Maurer, Eric J. Ward, Roger W. Bursey, Jr.
  • Patent number: 8616850
    Abstract: A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as windmilling when centrifugal force alone is inadequate to tightly seal the root within the slot.
    Type: Grant
    Filed: June 11, 2010
    Date of Patent: December 31, 2013
    Assignee: United Technologies Corporation
    Inventors: Eric J. Ward, Brian K. Richardson
  • Publication number: 20130302140
    Abstract: A compressor section for use in a gas turbine engine has a plurality of compressor stages. Each compressor stage is provided with a rotor hub, and each rotor hub mounts a plurality of compressor blades. A rotor drum extends between adjacent rotor hubs. A plurality of stator stages have an outer ring and a radially inner ring. A plurality of vanes extend between the outer and inner rings. An inner surface of the inner ring is spaced by a gap from an outer surface of the rotor drum. The rotor drum is provided with a plurality of blades having a general airfoil shape to resist leakage across the gap.
    Type: Application
    Filed: May 8, 2012
    Publication date: November 14, 2013
    Inventor: Eric J. Ward
  • Publication number: 20130164118
    Abstract: A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first flow apertures extending axially therethrough, and a plurality of roller elements connected to an inner rotor platform. The first flow apertures are arranged circumferentially around the inner rotor platform. The duct blocker stator includes a plurality of second flow apertures that extending axially therethrough, and a roller element track located radially within the inner rotor platform and in rolling contact with the roller elements. The second flow apertures are arranged circumferentially around an inner stator platform that is located axially adjacent to the inner rotor platform. The duct blocker rotor rotates relative to the duct blocker stator to regulate fluid flowing between the first flow apertures and the second flow apertures.
    Type: Application
    Filed: December 22, 2011
    Publication date: June 27, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: James Jones, John H. Maurer, Eric J. Ward, Roger W. Bursey, JR.
  • Publication number: 20110305576
    Abstract: A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as windmilling when centrifugal force alone is inadequate to tightly seal the root within the slot.
    Type: Application
    Filed: June 11, 2010
    Publication date: December 15, 2011
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Eric J. Ward, Brian K. Richardson
  • Patent number: 6694723
    Abstract: A valve assembly for supplying cooling air to a nozzle of a gas turbine engine. The nozzle can move between a first configuration and a second configuration. The valve assembly includes a first member having openings that receive cooling air. The valve assembly also includes a second member having openings. The second member resides adjacent the first member to receive the cooling air from the first member. Finally, the valve assembly includes actuator for moving the first member from a first position, which allows a first flow rate of cooling air to pass through the openings, to a second position, which allows a second flow rate of cooling air to pass through the openings. The second flow rate is less than the first flow rate.
    Type: Grant
    Filed: March 27, 2002
    Date of Patent: February 24, 2004
    Assignee: United Technologies Corporation
    Inventor: Eric J. Ward
  • Publication number: 20030205043
    Abstract: A valve assembly for supplying cooling air to a nozzle of a gas turbine engine. The nozzle can move between a first configuration and a second configuration. The valve assembly includes a first member having openings that receive cooling air. The valve assembly also includes a second member having openings. The second member resides adjacent the first member to receive the cooling air from the first member. Finally, the valve assembly includes actuator for moving the first member from a first position, which allows a first flow rate of cooling air to pass through the openings, to a second position, which allows a second flow rate of cooling air to pass through the openings. The second flow rate is less than the first flow rate.
    Type: Application
    Filed: March 27, 2002
    Publication date: November 6, 2003
    Inventor: Eric J. Ward
  • Patent number: 5797544
    Abstract: The flaps of the C/D exhaust nozzle for a gas turbine engine are arranged to obtain synchronous movement relative to each other and the interconnecting fulcrum links are attached to a coaxially mounted combined piston/sync ring by an H-shaped link. One link from one convergent flap is connected to one of the fulcrum links and the adjacent convergent flap is connected to the same fulcrum link. The redundant synchronization provided by the H-shaped links and flap connections provide damping of the flap train. The fulcrum links are judiciously mounted between adjacent convergent flaps.
    Type: Grant
    Filed: September 27, 1996
    Date of Patent: August 25, 1998
    Assignee: United Technologies Corporation
    Inventor: Eric J. Ward
  • Patent number: 5323965
    Abstract: A gap seal for convergent/divergent flap hinge ends to spaced disc and wall surfaces in a 2-D nozzle of a gas turbine engine is provided. The seal employs at least two cups resiliently mounted to the hinge ends, which cups independently translate axially and resiliently to contact the spaced surfaces at different or varying gaps to seal same. The translating cup seals of the invention thus maintain a constant seal in the gaps between the hinge ends and such surfaces at varying C/D hinge positions and varying operating conditions in the 2-D nozzle. That is, the cups independently maintain their seals across gaps as they expand or contract due to thermal changes as well as across gaps of different sizes.
    Type: Grant
    Filed: May 26, 1993
    Date of Patent: June 28, 1994
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventors: Kenneth W. Froemming, Eric J. Ward
  • Patent number: 5102049
    Abstract: A thrust reverser in a two dimensional jet engine exhaust nozzle employs a plurality of reverser apparati that maintain a constant flow throat area, for example, in the reverse throat mode. A single reverser apparatus includes an actuator that operates through a lever upon linkage and a coupler to drive a set of parallel vanes and at least one independent vane. The parallel vanes are connected by a parallelogram of links to the coupler. The independent vanes move in a manner as defined by a cam having a preselected path therein that causes the independent vanes to move in a desired manner to provide the constant throat area.
    Type: Grant
    Filed: November 24, 1987
    Date of Patent: April 7, 1992
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventor: Eric J. Ward
  • Patent number: 5031836
    Abstract: A flexible fairing 13 is provided which includes an aerodynamic surface 20 composed of a plurality of closely spaced, telescopic fairing members 14 and a moveable fairing panel 18. One end 15 of each fairing member 14 is pivotably secured to a divergent flap 11 of a thrust vectoring nozzle, and the other end 17 of the fairing member is pivotably secured to the fairing panel 18 which is slideably mounted to the static structure of a nozzle 19 of a gas turbine engine. The flexible fairing 13 adjusts to accommodate both translational and rotational movement of the divergent flap relative to an airframe fairing 10, thereby maintaining an aerodynamic surface 20 between the airframe fairing 10 and the divergent flap 11 of the nozzle.
    Type: Grant
    Filed: July 10, 1990
    Date of Patent: July 16, 1991
    Assignee: United Technologies Corporation
    Inventor: Eric J. Ward