Patents by Inventor Richard Christopher Uskert
Richard Christopher Uskert 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: 9920634Abstract: One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil. Yet another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooled gas turbine engine components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: GrantFiled: June 27, 2014Date of Patent: March 20, 2018Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.Inventors: Richard Christopher Uskert, Ted Joseph Freeman, David John Thomas, Jay E. Lane, Adam Lee Chamberlain, John Alan Weaver
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Patent number: 9631916Abstract: An apparatus including a first component having an exterior surface formed of a ceramic material and including a primary surface region and a plurality of secondary surface regions protruding from the primary surface region, and a second component positioned in contact with at least one of the secondary surface regions and spaced from the primary surface region to define a determinant load path between the first and second components. A method of forming the apparatus is also provided.Type: GrantFiled: December 27, 2013Date of Patent: April 25, 2017Assignee: Rolls Royce CorporationInventors: David John Thomas, Richard Christopher Uskert
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Publication number: 20160348586Abstract: An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and a CMC foam layer bonded to the first CMC sheet. The CMC foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the CMC foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.Type: ApplicationFiled: August 11, 2016Publication date: December 1, 2016Inventors: Richard Christopher Uskert, Ted Joseph Freeman, David John Thomas, Jay Lane
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Patent number: 9421733Abstract: An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and an open-cell foam layer bonded to the first CMC sheet. The open-cell foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the open-cell foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.Type: GrantFiled: December 24, 2011Date of Patent: August 23, 2016Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Richard Christopher Uskert, Ted Joseph Freeman, David John Thomas, Jay Lane
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Patent number: 9310079Abstract: The disclosure is directed to a gas turbine engine combustion liner and a gas turbine engine. The gas turbine engine combustion liner may include a thermally cooled wall section, an acoustically damped wall section, or a thermally cooled and acoustically damped wall section. Open cell foam or honeycomb may be disposed between inner and outer combustion liner walls. The walls, open cell foam, or honeycomb may be made of a composite material.Type: GrantFiled: June 16, 2011Date of Patent: April 12, 2016Assignee: Rolls-Royce North American Technologies, Inc.Inventor: Richard Christopher Uskert
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Publication number: 20150354936Abstract: An apparatus including a first component having an exterior surface formed of a ceramic material and including a primary surface region and a plurality of secondary surface regions protruding from the primary surface region, and a second component positioned in contact with at least one of the secondary surface regions and spaced from the primary surface region to define a determinant load path between the first and second components. A method of forming the apparatus is also provided.Type: ApplicationFiled: December 27, 2013Publication date: December 10, 2015Applicant: Rolls-Royce CorporationInventors: David John Thomas, Richard Christopher Uskert
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Publication number: 20150345501Abstract: The invention comprises an electromagnetic propulsive motor having a rotor capable of rotation around a shaft and having a plurality of radially disposed blades including blade tip portions for compressing a working fluid. The invention further comprises a stator having a case frame, and a plurality of radially disposed vanes extending generally between said case frame and said shaft for directing the working fluid. A plurality of electromagnetic elements disposed within said rotor blades proximate the tip portions thereof interact electromagnetically with a plurality of electromagnetic elements disposed in said stator case frame to drive said rotor.Type: ApplicationFiled: August 13, 2015Publication date: December 3, 2015Inventor: Richard Christopher Uskert
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Patent number: 9151166Abstract: A gas turbine engine component is disclosed having a composite construction. In one embodiment the gas turbine engine component is a blade that includes a shroud. A fiber ply of the composite construction extends from an airfoil part of the blade to the shroud. The shroud can include multiple plies that can be stitched together. In one form a sealing knife is formed and coupled to the shroud. The sealing knife can be coupled to the shroud by stitching. Filler material can be used in the composite construction of the gas turbine engine component.Type: GrantFiled: June 7, 2010Date of Patent: October 6, 2015Assignee: Rolls-Royce North American Technologies, Inc.Inventor: Richard Christopher Uskert
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Patent number: 9143023Abstract: The invention provides an electromagnetic propulsive motor having a rotor capable of rotation around a shaft and having a plurality of radially disposed blades including blade tip portions for compressing a working fluid. The invention further provides a stator having a case frame, and a plurality of radially disposed vanes extending generally between said case frame and said shaft for directing the working fluid. A plurality of electromagnetic elements disposed within said rotor blades proximate the tip portions thereof interact electromagnetically with a plurality of electromagnetic elements disposed in said stator case frame to drive said rotor.Type: GrantFiled: May 17, 2011Date of Patent: September 22, 2015Inventor: Richard Christopher Uskert
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Publication number: 20140311163Abstract: One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil. Yet another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooled gas turbine engine components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: ApplicationFiled: June 27, 2014Publication date: October 23, 2014Inventors: Richard Christopher Uskert, Ted Joseph Freeman, David John Thomas, Jay E. Lane, Adam Lee Chamberlain, John Alan Weaver
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Patent number: 8753090Abstract: A bladed disk assembly includes a disk, a blade, and a retaining clip. The disk is centered on an axis. The disk has at least one groove extending along the axis. The blade is received in the groove. The retaining clip contacts the blade and limits movement of the blade along the axis. The retaining clip is engaged with the disk through a snap-fit.Type: GrantFiled: November 24, 2010Date of Patent: June 17, 2014Assignee: Rolls-Royce CorporationInventors: Matthew Peter Basiletti, Richard Christopher Uskert, Michelle Lynn Tucker
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Patent number: 8439635Abstract: An apparatus and method for locking a composite component such as blade or vane of a turbine engine is disclosed herein. The disclosed lock can also be used generally to fix the position of composite structures. The lock includes a first locking member including a first structure operable to at least partially fix the first locking member along an axis of a slot for receiving a blade or a vane. The lock also includes a second locking member including a second structure operable to engage the blade or vane. The first and second locking members are slidably engaged with one another along mating ramped surfaces.Type: GrantFiled: May 11, 2009Date of Patent: May 14, 2013Assignee: Rolls-Royce CorporationInventors: Richard Christopher Uskert, Darrell Curtis Harris
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Publication number: 20120266603Abstract: An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and an open-cell foam layer bonded to the first CMC sheet. The open-cell foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the open-cell foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.Type: ApplicationFiled: December 24, 2011Publication date: October 25, 2012Inventors: Richard Christopher Uskert, Ted Joseph Freeman, David John Thomas, Jay Lane
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Publication number: 20120167574Abstract: One embodiment of the present invention is a unique gas turbine engine combustion liner. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine combustion liners. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: ApplicationFiled: June 16, 2011Publication date: July 5, 2012Inventor: Richard Christopher Uskert
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Publication number: 20120128498Abstract: A bladed disk assembly is disclosed herein. The bladed disk assembly includes a disk centered on an axis. The disk has at least one groove extending along the axis. The bladed disk assembly also includes a blade received in the groove. The bladed disk assembly also includes a retaining clip contacting the blade and limiting movement of the blade along the axis. The retaining clip is engaged with the disk through a snap-fit.Type: ApplicationFiled: November 24, 2010Publication date: May 24, 2012Inventors: Matthew Peter Basiletti, Richard Christopher Uskert, Michelle Lynn Tucker
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Publication number: 20110299976Abstract: A gas turbine engine component is disclosed having a composite construction. In one embodiment the gas turbine engine component is a blade that includes a shroud. A fiber ply of the composite construction extends from an airfoil part of the blade to the shroud. The shroud can include multiple plies that can be stitched together. In one form a sealing knife is formed and coupled to the shroud. The sealing knife can be coupled to the shroud by stitching. Filler material can be used in the composite construction of the gas turbine engine component.Type: ApplicationFiled: June 7, 2010Publication date: December 8, 2011Inventor: Richard Christopher Uskert
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Publication number: 20100284805Abstract: An apparatus and method for locking a composite component such as blade or vane of a turbine engine is disclosed herein. The disclosed lock can also be used generally to fix the position of composite structures. The lock includes a first locking member including a first structure operable to at least partially fix the first locking member along an axis of a slot for receiving a blade or a vane. The lock also includes a second locking member including a second structure operable to engage the blade or vane. The first and second locking members are slidably engaged with one another along mating ramped surfaces.Type: ApplicationFiled: May 11, 2009Publication date: November 11, 2010Inventors: Richard Christopher Uskert, Darrell Curtis Harris