Patents by Inventor Steven Clarkson
Steven Clarkson 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: 11268526Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.Type: GrantFiled: July 9, 2014Date of Patent: March 8, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: James T. Roach, Barry Barnett, Grant O. Cook, III, Charles R. Watson, Shari L. Bugaj, Glenn LeVasseur, Wendell V. Twelves, Jr., Christopher J. Hertel, Colin J. Kling, Matthew A. Turner, JinQuan Xu, Steven Clarkson, Michael Caulfield
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Patent number: 10837313Abstract: A case for a gas turbine engine includes a case body defining an axially extending core flow path, a radially extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A lubricant conduit is connected to the case body and is in thermal communication with the structure-supporting member.Type: GrantFiled: December 15, 2015Date of Patent: November 17, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Steven Clarkson, Daniel K. Van Ness, II, Paul Thomas Rembish
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Patent number: 10731511Abstract: A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.Type: GrantFiled: February 22, 2013Date of Patent: August 4, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Sreenivasa R. Voleti, Mark W. Costa, Steven Clarkson
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Patent number: 10526919Abstract: A fan case includes a composite fan case body including an outer surface and at least one attachment tool attached to the outer surface of the fan case body. The attachment tool includes a boss that has at least one fastener opening with a threaded insert. A channel extends from at least one interior cavity of the attachment tool through an outer wall of the attachment tool.Type: GrantFiled: July 17, 2015Date of Patent: January 7, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas Joseph Robertson, Jr., Steven Clarkson
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Patent number: 10487693Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.Type: GrantFiled: February 5, 2018Date of Patent: November 26, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Mark W. Costa, Steven Clarkson
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Patent number: 10294960Abstract: An ice liner assembly for a fan containment case for a turbofan gas turbine engine is disclosed. The disclosed ice liner assembly includes a plurality of arcuate panels arranged end to end to form a cylindrical liner that is disposed within the fan containment case and aft of the fan and abradable strip liner that circumscribes the fan. Because the plurality of arcuate panels are arranged end to end fashion, the ice liner assembly includes a plurality of splice joints, or a joint between two abutting ends of two arcuate panels. The splice joints are reinforced with molded polymeric splice support cores that are substantially lighter and less expensive than currently employed high density aluminum honeycomb core materials.Type: GrantFiled: May 23, 2014Date of Patent: May 21, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Steven Clarkson
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Patent number: 10208667Abstract: A nose cone may have a spinner including a main portion and an axially extending stepped portion. The nose cone may also have an annular aft support ring radially secured to the axially extending stepped portion. The nose cone may further include a fairing, which may be secured to the stepped portion.Type: GrantFiled: May 23, 2014Date of Patent: February 19, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Colin J. Kling, Steven Clarkson
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Publication number: 20180171826Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.Type: ApplicationFiled: February 5, 2018Publication date: June 21, 2018Inventors: Thomas J. Robertson, JR., Mark W. Costa, Steven Clarkson
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Patent number: 9982605Abstract: A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.Type: GrantFiled: September 13, 2013Date of Patent: May 29, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Steven Clarkson, Mark w. Costa
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Patent number: 9915168Abstract: A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a containment case and a cartridge liner carried therein. A ballistic liner encircles at least a portion of the cartridge liner and is attached thereto.Type: GrantFiled: June 2, 2015Date of Patent: March 13, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Steven Clarkson
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Patent number: 9909458Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.Type: GrantFiled: February 4, 2015Date of Patent: March 6, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Mark W. Costa, Steven Clarkson
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Patent number: 9896964Abstract: A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.Type: GrantFiled: December 15, 2015Date of Patent: February 20, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Steven Clarkson, Daniel K. Van Ness, II, Paul Thomas Rembish
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Patent number: 9822665Abstract: A core for a fan containment includes an intermediate core segment and a plenum for fluid passage defined through the intermediate core segment. The intermediate core segment has an axial inlet side, an axial outlet side opposed to the axial inlet side, a radially inner side, and a radially outer side opposed to the radially inner side. The radially outer side is configured to be operatively connected to a cylindrical outer case and the radially inner side is configured to be operatively connected to at least one arcuate panel to form a liner assembly. The plenum extends through the intermediate core segment proximate the radially outer side for fluid passage between the axial inlet side and the axial outlet side.Type: GrantFiled: December 4, 2014Date of Patent: November 21, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Steven Clarkson
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Patent number: 9644493Abstract: A method of manufacturing a fan case with a liner includes the steps of providing a preform having a circular cross-section with a cut and a first diameter, flexing the preform to reduce the first diameter to a second diameter, and adhering the preform to an inner surface of a fan case. A fan case for a gas turbine engine includes a fan case body having an inner surface. A preform is adhered to the inner surface and has a cut providing a gap.Type: GrantFiled: September 7, 2012Date of Patent: May 9, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Steven Clarkson
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Publication number: 20170083950Abstract: A method and apparatus are provided for pairing a player to an athlete for developing the player. The method for pairing a user to an athlete includes receiving, from a client device, a request to match a user to an athlete. The request identifies a user profile associated with the user. The method also includes retrieving a plurality of athlete profiles and the user profile based on the identification of the user profile associated with the user. The method also includes matching an athlete profile to the user profile. The method also includes, responsive to matching the athlete profile to the user, updating the user profile with data from the matched athlete profile by offering one or more products to the user, wherein the one or more products is based on the data from the matched athlete. The method also includes transmitting the updated user profile to the client device.Type: ApplicationFiled: September 19, 2016Publication date: March 23, 2017Inventors: Michael Grant Fitts, Steven Clarkson
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Publication number: 20160273550Abstract: A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment. A radially interior layer, defining a relatively substantially uninterrupted flowpath over at least a portion of the impact resistant layer and the aft segment, extends against and radially interior of both the impact resistant layer and the honeycomb aft segment.Type: ApplicationFiled: December 8, 2014Publication date: September 22, 2016Inventors: Steven Clarkson, Richard B. Bergethon
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Publication number: 20160258445Abstract: An ice liner assembly for a fan containment case for a turbofan gas turbine engine is disclosed. The disclosed ice liner assembly includes a plurality of arcuate panels arranged end to end to form a cylindrical liner that is disposed within the fan containment case and aft of the fan and abradable strip liner that circumscribes the fan. Because the plurality of arcuate panels are arranged end to end fashion, the ice liner assembly includes a plurality of splice joints, or a joint between two abutting ends of two arcuate panels.Type: ApplicationFiled: May 23, 2014Publication date: September 8, 2016Inventors: Thomas J. Robertson, JR., Steven Clarkson
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Publication number: 20160245175Abstract: An ice panel for a fan case of a gas turbine engine is disclosed. The ice panel may comprise a facesheet located on an inner surface of the fan case and it may comprise a chopped prepreg tape that is cured. The chopped prepreg tape may comprise randomly oriented chips of fibers impregnated with a resin matrix.Type: ApplicationFiled: May 23, 2014Publication date: August 25, 2016Inventors: Steven CLARKSON, Thomas J. ROBERTSON
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Publication number: 20160237897Abstract: A nose cone may have a spinner including a main portion and an axially extending stepped portion. The nose cone may also have an annular aft support ring radially secured to the axially extending stepped portion. The nose cone may further include a fairing, which may be secured to the stepped portion.Type: ApplicationFiled: May 23, 2014Publication date: August 18, 2016Inventors: Colin J. Kling, Steven Clarkson
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Publication number: 20160177840Abstract: A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.Type: ApplicationFiled: September 13, 2013Publication date: June 23, 2016Inventors: Thomas J. Robertson, Steven Clarkson, Mark W. Costa