Patents by Inventor Bryan William Olver
Bryan William Olver 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: 11466622Abstract: An aerospace component, for example, used in a gas turbine engine, includes the following structurally-integrated layers: a metallic layer and a composite layer having reinforcing fibers embedded in a matrix material. The aerospace component can also include an insulating layer disposed between the metallic layer and the composite layer where the insulating layer has a thermal conductivity that is lower than a thermal conductivity of the composite layer.Type: GrantFiled: November 2, 2018Date of Patent: October 11, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Kin-Leung Cheung, Bryan William Olver, Stephen Caulfeild
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Patent number: 11274602Abstract: A turbofan engine comprising an outer bypass duct, an annular bypass flow path between the outer bypass duct and a core engine, an engine component forming an airflow obstruction adjacent the outer bypass duct, an air cooler having a tube, the tube having at least a sinuous portion extending in the annular bypass flow path, the sinuous portion extending along the outer bypass duct, downstream of the airflow obstruction, the sinuous portion configured for exchanging heat between a fluid circulating in the tube and air circulating in the bypass flow path during operation of the turbofan engine.Type: GrantFiled: May 24, 2019Date of Patent: March 15, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bryan William Olver, Daniel Alecu, Jason Fish, Zoran Markovic
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Patent number: 11111856Abstract: The turbofan engine can have a core engine, a bypass duct surrounding the core engine, an annular bypass flow path between the bypass duct and the core engine, and a plurality of core links extending across the bypass path and supporting the core engine relative to the bypass duct, and a fluid passage having a heat exchange portion in a given one of the core links, the heat exchange portion being configured for heat exchange with the bypass flow path, an inlet leading into the given core link and to the heat exchange portion, and an outlet extending from the heat exchange portion and out of the given core link.Type: GrantFiled: March 4, 2019Date of Patent: September 7, 2021Assignee: PRATT & WHITNEY CANADA CORPInventor: Bryan William Olver
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Publication number: 20200370476Abstract: A turbofan engine comprising an outer bypass duct, an annular bypass flow path between the outer bypass duct and a core engine, an engine component forming an airflow obstruction adjacent the outer bypass duct, an air cooler having a tube, the tube having at least a sinuous portion extending in the annular bypass flow path, the sinuous portion extending along the outer bypass duct, downstream of the airflow obstruction, the sinuous portion configured for exchanging heat between a fluid circulating in the tube and air circulating in the bypass flow path during operation of the turbofan engine.Type: ApplicationFiled: May 24, 2019Publication date: November 26, 2020Inventors: Bryan William OLVER, Daniel ALECU, Jason FISH, Zoran MARKOVIC
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Publication number: 20200284198Abstract: The turbofan engine can have a core engine, a bypass duct surrounding the core engine, an annular bypass flow path between the bypass duct and the core engine, and a plurality of core links extending across the bypass path and supporting the core engine relative to the bypass duct, and a fluid passage having a heat exchange portion in a given one of the core links, the heat exchange portion being configured for heat exchange with the bypass flow path, an inlet leading into the given core link and to the heat exchange portion, and an outlet extending from the heat exchange portion and out of the given core link.Type: ApplicationFiled: March 4, 2019Publication date: September 10, 2020Inventor: Bryan William OLVER
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Patent number: 10711625Abstract: A gaspath traversing component of a gas turbine engine comprises a wall having an outer edge surface and a thickness relative to the gaspath, the wall having a plurality of layers of composite materials forming the thickness. A wear indication layer is embedded within the plurality of layers of composite material, the wear indication layer being visually contrasting with the composite material. The wear indication layer is positioned interiorly of at least one layer of said plurality of layers of composite material relative to the outer edge surface. A method for attending to a gas traversing component of a gas turbine engine is also provided.Type: GrantFiled: December 20, 2013Date of Patent: July 14, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Stephen Caulfeild, Kin-Leung Cheung, Mathieu Poulin, Bryan William Olver
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Publication number: 20200095938Abstract: An aerospace component, for example, used in a gas turbine engine, includes the following structurally-integrated layers: a metallic layer and a composite layer having reinforcing fibers embedded in a matrix material. The aerospace component can also include an insulating layer disposed between the metallic layer and the composite layer where the insulating layer has a thermal conductivity that is lower than a thermal conductivity of the composite layer.Type: ApplicationFiled: November 2, 2018Publication date: March 26, 2020Inventors: Kin-Leung CHEUNG, Bryan William OLVER, Stephen CAULFEILD
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Patent number: 9784132Abstract: A gas turbine engine including a composite case having a conductive path therein, and a conductive case connected to the composite case. The conductive case is made of a conductive material. A fastener connects the composite case to the conductive case. The fastener is conductively connected to the conductive material of the conductive case and not directly conductively connected to the conductive path. At least one voltage discharge channeling assembly is connected to the fastener and to the conductive case. The at least one voltage discharge channeling assembly has a portion conductively connected to the conductive path. The at least one voltage discharge channeling assembly is conductively connected to the fastener. A method of assembling an engine casing in a gas turbine engine is also provided.Type: GrantFiled: April 20, 2015Date of Patent: October 10, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bryan William Olver, Suresh Sivavarman, Brant Duke
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Publication number: 20160305330Abstract: A gas turbine engine including a composite case having a conductive path therein, and a conductive case connected to the composite case. The conductive case is made of a conductive material. A fastener connects the composite case to the conductive case. The fastener is conductively connected to the conductive material of the conductive case and not directly conductively connected to the conductive path. At least one voltage discharge channeling assembly is connected to the fastener and to the conductive case. The at least one voltage discharge channeling assembly has a portion conductively connected to the conductive path. The at least one voltage discharge channeling assembly is conductively connected to the fastener. A method of assembling an engine casing in a gas turbine engine is also provided.Type: ApplicationFiled: April 20, 2015Publication date: October 20, 2016Inventors: Bryan William OLVER, Suresh SIVAVARMAN, Brant DUKE
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Publication number: 20150176425Abstract: A gaspath traversing component of a gas turbine engine comprises a wall having an outer edge surface and a thickness relative to the gaspath, the wall having a plurality of layers of composite materials forming the thickness. A wear indication layer is embedded within the plurality of layers of composite material, the wear indication layer being visually contrasting with the composite material. The wear indication layer is positioned interiorly of at least one layer of said plurality of layers of composite material relative to the outer edge surface. A method for attending to a gas traversing component of a gas turbine engine is also provided.Type: ApplicationFiled: December 20, 2013Publication date: June 25, 2015Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Stephen CAULFEILD, Kin-Leung CHEUNG, Mathieu POULIN, Bryan William OLVER
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Patent number: 8621839Abstract: A gas turbine engine oil system has an air-oil separator for removing air from an air/oil mixture. A breather tube is connected to an exhaust of the air-oil separator for receiving hot air removed from the air/oil mixture in the air-oil separator. The gas turbine engine oil separator exhaust is directed in a cooled oil collector to cause the oil mist remaining in the air at the exit from the engine air-oil separator to condensate. The oil condensate is returned back into the engine oil system.Type: GrantFiled: September 28, 2009Date of Patent: January 7, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Daniel T. Alecu, Bryan William Olver
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Patent number: 8222165Abstract: A fire-critical aircraft or other component within a fire-risk zone includes a protective fire shield directly exposed to the fire-risk zone and separating the fire-critical component therefrom. The fire shield has an entirely composite construction composed of fiber cloth impregnated with a sacrificial resin which has a melting point that is below that of the fiber cloth. When exposed to fire, the fiber cloth remains substantially intact for at least the minimum period of time while the sacrificial resin is allowed to be at least partially consumed by the fire, such that the protective fire shield is partially sacrificed.Type: GrantFiled: October 27, 2008Date of Patent: July 17, 2012Assignee: Pratt & Whitney Canada Corp.Inventor: Bryan William Olver
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Publication number: 20120060508Abstract: A gas turbine engine oil system has an air-oil separator for removing air from an air/oil mixture. A breather tube is connected to an exhaust of the air-oil separator for receiving hot air removed from the air/oil mixture in the air-oil separator. The gas turbine engine oil separator exhaust is directed in a cooled oil collector to cause the oil mist remaining in the air at the exit from the engine air-oil separator to condensate. The oil condensate is returned back into the engine oil system.Type: ApplicationFiled: September 28, 2009Publication date: March 15, 2012Inventors: Daniel T. Alecu, Bryan William Olver
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Patent number: 7861981Abstract: A method and apparatus for providing a mounting system for an elongated item such as a cable, tube or wire, or an assembly of multiple cables, tube and/or wires. The mounting system includes an apparatus for mounting to a supporting structure, and an apparatus for receiving the elongated item. Also included is an apparatus for receiving a tying member such as a cable tie. Also included is an apparatus for permitting the tying member to be cut to release the elongate item from the mount without damage to the elongate item.Type: GrantFiled: October 22, 2008Date of Patent: January 4, 2011Assignee: Pratt & Whitney Canada Corp.Inventor: Bryan William Olver
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Patent number: 7854120Abstract: A fuel conveying member of a gas turbine engine fuel system conducting pressurized fluid flow is provided. The fuel conveying member comprises a body defining an L-shaped fuel flow passage therein, the L-shaped passage including an elbow. The elbow portion provides a substantially smooth fluid-dynamic transition between portions of the passage upstream and downstream thereof.Type: GrantFiled: March 3, 2006Date of Patent: December 21, 2010Assignee: Pratt & Whitney Canada Corp.Inventor: Bryan William Olver
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Publication number: 20100105266Abstract: A fire-critical aircraft or other component within a fire-risk zone includes a protective fire shield directly exposed to the fire-risk zone and separating the fire-critical component therefrom. The fire shield has an entirely composite construction composed of fibre cloth impregnated with a sacrificial resin which has a melting point that is below that of the fibre cloth. When exposed to fire, the fibre cloth remains substantially intact for at least the minimum period of time while the sacrificial resin is allowed to be at least partially consumed by the fire, such that the protective fire shield is partially sacrificed.Type: ApplicationFiled: October 27, 2008Publication date: April 29, 2010Inventor: Bryan William OLVER
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Publication number: 20100096511Abstract: A method and apparatus for providing a mounting system for an elongated item such as a cable, tube or wire, or an assembly of multiple cables, tube and/or wires. The mounting system includes an apparatus for mounting to a supporting structure, and an apparatus for receiving the elongated item. Also included is an apparatus for receiving a tying member such as a cable tie. Also included is an apparatus for permitting the tying member to be cut to release the elongate item from the mount without damage to the elongate item.Type: ApplicationFiled: October 22, 2008Publication date: April 22, 2010Inventor: Bryan William OLVER