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).
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Patent number: 10900376Abstract: 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: GrantFiled: January 14, 2020Date of Patent: January 26, 2021Assignee: Raytheon Technologies CorporationInventor: Eric J. Ward
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Publication number: 20200149428Abstract: 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: ApplicationFiled: January 14, 2020Publication date: May 14, 2020Inventor: Eric J. Ward
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Patent number: 10605119Abstract: 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: GrantFiled: September 25, 2017Date of Patent: March 31, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Eric J. Ward
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Patent number: 10570770Abstract: 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: GrantFiled: December 8, 2014Date of Patent: February 25, 2020Assignee: United Technologies CorporationInventor: Eric J. Ward
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Patent number: 10514102Abstract: 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: GrantFiled: July 14, 2017Date of Patent: December 24, 2019Assignee: United Technologies CorporationInventor: Eric J. Ward
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Publication number: 20190093507Abstract: 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: ApplicationFiled: September 25, 2017Publication date: March 28, 2019Inventor: Eric J. Ward
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Publication number: 20190017604Abstract: 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: ApplicationFiled: July 14, 2017Publication date: January 17, 2019Inventor: Eric J. Ward
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Publication number: 20160319693Abstract: 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: ApplicationFiled: December 8, 2014Publication date: November 3, 2016Inventor: Eric J. Ward
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Patent number: 9169849Abstract: 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: GrantFiled: May 8, 2012Date of Patent: October 27, 2015Assignee: United Technologies CorporationInventor: Eric J. Ward
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Patent number: 8967952Abstract: 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: GrantFiled: December 22, 2011Date of Patent: March 3, 2015Assignee: United Technologies CorporationInventors: James Jones, John H. Maurer, Eric J. Ward, Roger W. Bursey, Jr.
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Patent number: 8616850Abstract: 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: GrantFiled: June 11, 2010Date of Patent: December 31, 2013Assignee: United Technologies CorporationInventors: Eric J. Ward, Brian K. Richardson
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Publication number: 20130302140Abstract: 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: ApplicationFiled: May 8, 2012Publication date: November 14, 2013Inventor: Eric J. Ward
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Publication number: 20130164118Abstract: 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: ApplicationFiled: December 22, 2011Publication date: June 27, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: James Jones, John H. Maurer, Eric J. Ward, Roger W. Bursey, JR.
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Publication number: 20110305576Abstract: 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: ApplicationFiled: June 11, 2010Publication date: December 15, 2011Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Eric J. Ward, Brian K. Richardson
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Patent number: 6694723Abstract: 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: GrantFiled: March 27, 2002Date of Patent: February 24, 2004Assignee: United Technologies CorporationInventor: Eric J. Ward
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Publication number: 20030205043Abstract: 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: ApplicationFiled: March 27, 2002Publication date: November 6, 2003Inventor: Eric J. Ward
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Patent number: 5797544Abstract: 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: GrantFiled: September 27, 1996Date of Patent: August 25, 1998Assignee: United Technologies CorporationInventor: Eric J. Ward
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Patent number: 5323965Abstract: 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: GrantFiled: May 26, 1993Date of Patent: June 28, 1994Assignee: The United States of America as represented by the Secretary of the Air ForceInventors: Kenneth W. Froemming, Eric J. Ward
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Patent number: 5102049Abstract: 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: GrantFiled: November 24, 1987Date of Patent: April 7, 1992Assignee: The United States of America as represented by the Secretary of the Air ForceInventor: Eric J. Ward
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Patent number: 5031836Abstract: 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: GrantFiled: July 10, 1990Date of Patent: July 16, 1991Assignee: United Technologies CorporationInventor: Eric J. Ward