Patents by Inventor Colin J. Kling
Colin J. Kling 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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Publication number: 20240141794Abstract: A rotor assembly is provided that includes a rotor disk, a rotor blade and a rotor spacer. The rotor disk includes a slot. The rotor blade includes a blade root arranged within the slot. The root spacer is arranged within the slot between the rotor disk and the blade root. The root spacer is configured as or otherwise includes a cellular structure with a plurality of internal cells.Type: ApplicationFiled: October 28, 2022Publication date: May 2, 2024Inventors: Colin J. Kling, Nicholas J. Lawliss
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Patent number: 11519291Abstract: A gas turbine engine component includes a tubular body section including a plurality of fiber wraps encompassed within a matrix composition and one or more integrally-formed stiffeners extending from an outer surface of the body section and in a component circumferential direction around the body section. The stiffener includes one or more fiber wraps extending radially outwardly from the body section over a form and to the body section from the form.Type: GrantFiled: January 11, 2018Date of Patent: December 6, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Colin J. Kling
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Patent number: 11267576Abstract: 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, Colin J. Kling, Grant O. Cook, III, James J. McPhail, Shari L. Bugaj, James F. O'Brien, Majidullah Dehlavi, Scott A. Smith, Matthew R. Rader, Matthew A. Turner, JinQuan Xu
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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: 11236765Abstract: A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.Type: GrantFiled: October 25, 2019Date of Patent: February 1, 2022Assignee: Raytheon Technologies CorporationInventors: Colin J. Kling, Darin S. Lussier, James F. O'Brien
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Patent number: 11156126Abstract: A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture.Type: GrantFiled: March 29, 2019Date of Patent: October 26, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Colin J. Kling, Darin S. Lussier
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Patent number: 11028714Abstract: A fan rotor includes a fan hub and a plurality of fan blades extending radially outwardly from the fan hub. Platforms are positioned intermediate blade sides of adjacent ones of the fan blades. Seals are positioned between the blade sides and platform sides of the platform seals. The seals have an elongated bonding area bonded to one of the platform sides and the fan blade sides. The seal extends radially outwardly from the elongated bonding area to a wedge portion. A gas turbine engine and a seal are also disclosed.Type: GrantFiled: July 16, 2018Date of Patent: June 8, 2021Assignee: Raytheon Technologies CorporationInventor: Colin J. Kling
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Patent number: 10935046Abstract: A gas turbine engine fan case may comprise a plurality of wound layers that form a laminate and have a nominal radial fan case thickness, where the laminate includes a plurality of discrete fan case radial locations comprising a plurality of radially stacked composite plies that form a radial integral build up in comparison to the nominal radial fan case thickness.Type: GrantFiled: April 19, 2018Date of Patent: March 2, 2021Assignee: Raytheon Technologies CorporationInventors: David R. Lyders, Colin J. Kling
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Patent number: 10612400Abstract: A reinforced component in accordance with various embodiments includes a metal lug configured to be attached to a secondary component. The reinforced component further includes a composite material integrally formed around the metal lug and configured to be retained in place relative to the secondary component via an attachment between the metal lug and the secondary component.Type: GrantFiled: November 27, 2017Date of Patent: April 7, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Colin J. Kling, Darin S. Lussier, David R. Lyders
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Publication number: 20200056626Abstract: A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.Type: ApplicationFiled: October 25, 2019Publication date: February 20, 2020Inventors: Colin J. Kling, Darin S. Lussier, James F. O'Brien
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Publication number: 20200025034Abstract: A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture.Type: ApplicationFiled: March 29, 2019Publication date: January 23, 2020Inventors: Colin J. Kling, Darin S. Lussier
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Publication number: 20200018179Abstract: A fan rotor includes a fan hub and a plurality of fan blades extending radially outwardly from the fan hub. Platforms are positioned intermediate blade sides of adjacent ones of the fan blades. Seals are positioned between the blade sides and platform sides of the platform seals. The seals have an elongated bonding area bonded to one of the platform sides and the fan blade sides. The seal extends radially outwardly from the elongated bonding area to a wedge portion. A gas turbine engine and a seal are also disclosed.Type: ApplicationFiled: July 16, 2018Publication date: January 16, 2020Inventor: Colin J. Kling
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Patent number: 10533450Abstract: A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.Type: GrantFiled: October 30, 2017Date of Patent: January 14, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Colin J. Kling, Darin S. Lussier, Mark W. Costa
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Patent number: 10472049Abstract: A fan assembly of a gas turbine engine, a method for fabricating a fan assembly for a gas turbine engine, and a gas turbine engine are disclosed. The fan assembly of the gas turbine engine may include a spinner section, a fan hub section aft of the spinner section, and a joint therebetween. The fan assembly may further include a support ring for internally supporting the spinner, the support ring including a first portion facing the fan hub and a second portion connected to the spinner at the joint, wherein the connection between the second portion and the joint is a bonded connection.Type: GrantFiled: May 23, 2014Date of Patent: November 12, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Colin J. Kling, Scot A. Webb, James J. McPhail
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Patent number: 10472048Abstract: A spinner for a gas turbine engine is disclosed. The spinner may include a body extending between a first and second end comprised of a cured chopped unidirectional fiber pre-impregnated material. The body may have a generally conical shape and may further be plated with a metal or metal alloy.Type: GrantFiled: November 3, 2015Date of Patent: November 12, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Colin J. Kling, Shari L. Bugaj, James T. Roach
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Patent number: 10458433Abstract: A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.Type: GrantFiled: June 17, 2016Date of Patent: October 29, 2019Assignee: United Technologies CorporationInventors: Colin J. Kling, Darin S. Lussier, James F. O'Brien
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Publication number: 20190323520Abstract: A gas turbine engine fan case may comprise a plurality of wound layers that form a laminate and have a nominal radial fan case thickness, where the laminate includes a plurality of discrete fan case radial locations comprising a plurality of radially stacked composite plies that form a radial integral build up in comparison to the nominal radial fan case thickness.Type: ApplicationFiled: April 19, 2018Publication date: October 24, 2019Inventors: David R. Lyders, Colin J. Kling
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Patent number: 10392949Abstract: A spinner for a gas turbine engine comprises an outer shell for defining an airflow path when mounted in a gas turbine engine. An inner surface is provided with a plurality of webs. A gas turbine engine and a fan section for a gas turbine engine are also disclosed.Type: GrantFiled: January 9, 2015Date of Patent: August 27, 2019Assignee: United Technologies CorporationInventors: James T. Roach, Grant O. Cook, III, Colin J. Kling, James F. O'Brien, Shari L. Bugaj
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Patent number: 10352236Abstract: The present disclosure relates generally to a nosecap for a gas turbine engine. The nosecap may be injection molded in an embodiment. The nosecap may have bolt holes surrounded by bolt pockets that are asymmetric about a plane passing through a geometric center of the nosecap and passing through and dividing the bolt hole in an embodiment.Type: GrantFiled: October 15, 2014Date of Patent: July 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Colin J. Kling, Charles W. Brown
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Publication number: 20190211705Abstract: A gas turbine engine component includes a tubular body section including a plurality of fiber wraps encompassed within a matrix composition and one or more integrally-formed stiffeners extending from an outer surface of the body section and in a component circumferential direction around the body section. The stiffener includes one or more fiber wraps extending radially outwardly from the body section over a form and to the body section from the form.Type: ApplicationFiled: January 11, 2018Publication date: July 11, 2019Inventor: Colin J. Kling