Patents by Inventor Bryan W. Olver
Bryan W. 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: 11530710Abstract: An aircraft pneumatic system including a pneumatic actuator arranged to operate at a pressure value at least equal to a pressure threshold, a line fluidly connected between a pneumatic source and the pneumatic actuator, and a venturi disposed upstream of the line and downstream of the pneumatic source. The venturi is configured to receive a source flow from the source at a mass flow rate, the mass flow rate being between a lower, nominal flow rate value and a higher, graded flow rate value. The venturi is sized such that when the mass flow rate is at the nominal flow rate value, a line pressure inside the line corresponds to a source pressure upstream of the venturi, and when the mass flow rate to the venturi is at the graded flow rate value, the line pressure is less than the source pressure.Type: GrantFiled: January 28, 2020Date of Patent: December 20, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bryan W. Olver, Daniel Alecu, Nick Stina
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Publication number: 20210231050Abstract: An aircraft pneumatic system including a pneumatic actuator arranged to operate at a pressure value at least equal to a pressure threshold, a line fluidly connected between a pneumatic source and the pneumatic actuator, and a venturi disposed upstream of the line and downstream of the pneumatic source. The venturi is configured to receive a source flow from the source at a mass flow rate, the mass flow rate being between a lower, nominal flow rate value and a higher, graded flow rate value. The venturi is sized such that when the mass flow rate is at the nominal flow rate value, a line pressure inside the line corresponds to a source pressure upstream of the venturi, and when the mass flow rate to the venturi is at the graded flow rate value, the line pressure is less than the source pressure.Type: ApplicationFiled: January 28, 2020Publication date: July 29, 2021Inventors: Bryan W. OLVER, Daniel ALECU, Nick STINA
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Patent number: 11002148Abstract: A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.Type: GrantFiled: June 14, 2019Date of Patent: May 11, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bryan W. Olver, Stephen Caulfeild
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Patent number: 10753229Abstract: A mounting arrangement for mounting a fluid cooler to an engine case of a gas turbine engine, the mounting arrangement comprises at least one fixture adapted to be mounted to the engine case and defining a circumferentially extending channel for receiving at least one circumferentially extending flange of a cooler body of the fluid cooler. The at least one flange being free to slide in the channel of the at least one fixture in a circumferential direction of the engine case. The fixture may further comprise a clamping arrangement to hold the fluid cooler while allowing the same to thermally grow.Type: GrantFiled: December 20, 2016Date of Patent: August 25, 2020Assignee: PRATT & WHITNEY CANADA CORPInventor: Bryan W. Olver
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Publication number: 20190292939Abstract: A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.Type: ApplicationFiled: June 14, 2019Publication date: September 26, 2019Inventors: Bryan W. OLVER, Stephen CAULFEILD
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Patent number: 10364700Abstract: A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.Type: GrantFiled: June 28, 2016Date of Patent: July 30, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bryan W. Olver, Stephen Caulfeild
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Publication number: 20170370246Abstract: A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.Type: ApplicationFiled: June 28, 2016Publication date: December 28, 2017Inventors: Bryan W. Olver, Stephen Caulfeild
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Publication number: 20170298763Abstract: A mounting arrangement for mounting a fluid cooler to an engine case of a gas turbine engine, the mounting arrangement comprises at least one fixture adapted to be mounted to the engine case and defining a circumferentially extending channel for receiving at least one circumferentially extending flange of a cooler body of the fluid cooler. The at least one flange being free to slide in the channel of the at least one fixture in a circumferential direction of the engine case. The fixture may further comprise a clamping arrangement to hold the fluid cooler while allowing the same to thermally grow.Type: ApplicationFiled: December 20, 2016Publication date: October 19, 2017Applicant: PRATT & WHITNEY CANADA CORP.Inventor: Bryan W. OLVER
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Patent number: 9267435Abstract: A cam-type apparatus is included in a support link between outer and inner cases of gas turbine engines for centering the cases one to another. The cam-type apparatus is lockable to allow locking an adjusted position of the cam-type apparatus.Type: GrantFiled: September 25, 2013Date of Patent: February 23, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jeffrey Bernard Heyerman, Bryan W. Olver
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Publication number: 20160003154Abstract: A cam-type apparatus is included in a support link between outer and inner cases of gas turbine engines for centering the cases one to another. The cam-type apparatus is lockable to allow locking an adjusted position of the cam-type apparatus.Type: ApplicationFiled: September 25, 2013Publication date: January 7, 2016Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Jeffrey Bernard HEYERMAN, Bryan W. OLVER
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Patent number: 8757540Abstract: A nacelle inlet lip has a simplified geometry. The nacelle inlet lip has a constant cross-section all along a circumference thereof and is wholly concentric relative to the engine centerline, thereby allowing for the use of simple and economical manufacturing processes.Type: GrantFiled: June 30, 2008Date of Patent: June 24, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Bryan W. Olver, Ljubisa Vrljes
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Patent number: 8567202Abstract: A cam-type apparatus is included in a support link between outer and inner cases of gas turbine engines for centering the cases one to another. The cam-type apparatus is lockable to allow locking an adjusted position of the cam-type apparatus.Type: GrantFiled: May 15, 2009Date of Patent: October 29, 2013Assignee: Pratt & Whitney Canada Corp.Inventors: Jeffrey Bernard Heyerman, Bryan W. Olver
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Patent number: 8313293Abstract: A gas turbine engine has a rear mounting assembly incorporating a mounting apparatus attached to a bypass duct wall with a link device for transferring core portion related inertia-induced loads, from an MTF of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall.Type: GrantFiled: May 15, 2009Date of Patent: November 20, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Jeffrey Bernard Heyerman, Bryan W. Olver, Bruce Fielding, Carl Smythe
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Patent number: 8231142Abstract: A fluid conduit coupling for a turbofan engine wherein the engine has a gas path defined by inner and outer duct walls and the exterior surface of the outer duct wall is readily accessible for visual inspection. In one example, a first fluid line extends across the gas path between the inner and outer duct walls and a second fluid line is connected to the first fluid line at the level of the outer duct wall. The first fluid line may include a female coupling member and the second fluid member may include a mating male coupling member. An annular sealing member is associated with the first and second couplings and a leak path is defined between the annular sealing member and the exterior surface of the outer duct wall, whereby fluid may be detected by visual inspection of the outer duct wall if a leak should occur at the annular sealing member.Type: GrantFiled: February 17, 2009Date of Patent: July 31, 2012Assignee: Pratt & Whitney Canada Corp.Inventor: Bryan W. Olver
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Patent number: 7862293Abstract: A bleed air cooler assembly of a gas turbine engine comprises a cooler body defining a fluid passage therein and a connector detachably affixed with the cooler body installed in an annular bypass air passage.Type: GrantFiled: May 3, 2007Date of Patent: January 4, 2011Assignee: Pratt & Whitney Canada Corp.Inventor: Bryan W. Olver
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Publication number: 20100287950Abstract: A cam-type apparatus is included in a support link between outer and inner cases of gas turbine engines for centering the cases one to another. The cam-type apparatus is lockable to allow locking an adjusted position of the cam-type apparatus.Type: ApplicationFiled: May 15, 2009Publication date: November 18, 2010Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Jeffrey Bernard HEYERMAN, Bryan W. OLVER
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Publication number: 20100290903Abstract: A gas turbine engine has a rear mounting assembly incorporating a mounting apparatus attached to a bypass duct wall with a link device for transferring core portion related inertia-induced loads, from an MTF of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall.Type: ApplicationFiled: May 15, 2009Publication date: November 18, 2010Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Jeffrey Bernard HEYERMAN, Bryan W. OLVER, Bruce FIELDING, Carl SMYTHE
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Publication number: 20100207379Abstract: A fluid conduit coupling for a turbofan engine wherein the engine has a gas path defined by inner and outer duct walls and the exterior surface of the outer duct wall is readily accessible for visual inspection. In one example, a first fluid line extends across the gas path between the inner and outer duct walls and a second fluid line is connected to the first fluid line at the level of the outer duct wall. The first fluid line may include a female coupling member and the second fluid member may include a mating male coupling member. An annular sealing member is associated with the first and second couplings and a leak path is defined between the annular sealing member and the exterior surface of the outer duct wall, whereby fluid may be detected by visual inspection of the outer duct wall if a leak should occur at the annular sealing member.Type: ApplicationFiled: February 17, 2009Publication date: August 19, 2010Inventor: Bryan W. Olver
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Publication number: 20090321585Abstract: A nacelle inlet lip has a simplified geometry. The nacelle inlet lip has a constant cross-section all along a circumference thereof and is wholly concentric relative to the engine centerline, thereby allowing for the use of simple and economical manufacturing processes.Type: ApplicationFiled: June 30, 2008Publication date: December 31, 2009Inventors: Bryan W. Olver, Ljubisa Vrljes
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Publication number: 20080271433Abstract: A bleed air cooler assembly of a gas turbine engine comprises a cooler body defining a fluid passage therein and a connector detachably affixed with the cooler body installed in an annular bypass air passage.Type: ApplicationFiled: May 3, 2007Publication date: November 6, 2008Applicant: PRATT & WHITNEY CANADA CORP.Inventor: Bryan W. OLVER