Patents by Inventor Paul Aitchison
Paul Aitchison 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: 20230392503Abstract: A rotor of an aircraft engine has a plurality of blades extending radially from a disc. At least one of the blades has an airfoil, a root and a tip. The airfoil has a crack-mitigating rib extending chordwise along the airfoil. The crack-mitigating rib is disposed radially closer to the root than to the tip.Type: ApplicationFiled: June 2, 2022Publication date: December 7, 2023Inventors: Paul Aitchison, Paul Stone, Dikran Mangardich
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Patent number: 11454127Abstract: A vane configured to be disposed in a gas path defined in part by an inner surface of a case of a gas turbine engine is provided. The vane comprises a vane body configured to extend through an aperture in the case and a vane head disposed at an end of the vane body. The vane head has an abutting surface configured to contact an outer surface of the case when the vane body extends through the aperture, and a groove configured to receive a sealing member. The groove opens to the abutting surface and is outwardly open relative to an inner region surrounded by the groove. The groove has an inner seating surface that hinders movement of the sealing member toward the abutting surface and can facilitate installation of the vane in the engine.Type: GrantFiled: November 22, 2019Date of Patent: September 27, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Tammy Yam, Tibor Urac, Paul Aitchison
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Publication number: 20210156272Abstract: A vane configured to be disposed in a gas path defined in part by an inner surface of a case of a gas turbine engine is provided. The vane comprises a vane body configured to extend through an aperture in the case and a vane head disposed at an end of the vane body. The vane head has an abutting surface configured to contact an outer surface of the case when the vane body extends through the aperture, and a groove configured to receive a sealing member. The groove opens to the abutting surface and is outwardly open relative to an inner region surrounded by the groove. The groove has an inner seating surface that hinders movement of the sealing member toward the abutting surface and can facilitate installation of the vane in the engine.Type: ApplicationFiled: November 22, 2019Publication date: May 27, 2021Inventors: Tammy YAM, Tibor URAC, Paul AITCHISON
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Patent number: 11002293Abstract: A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.Type: GrantFiled: September 15, 2017Date of Patent: May 11, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Karan Anand, Farid Abrari, Ernest Adique, Paul Aitchison, Daniel Fudge, Kari Heikurinen, Paul Stone, Tibor Urac, Thomas Veitch
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Patent number: 10689987Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.Type: GrantFiled: September 6, 2019Date of Patent: June 23, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Thomas Veitch, Farid Abrari, Ernest Adique, Paul Aitchison, Daniel Fudge, Kari Heikurinen, Paul Stone, Tibor Urac
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Publication number: 20200018176Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.Type: ApplicationFiled: September 6, 2019Publication date: January 16, 2020Inventors: Thomas VEITCH, Farid ABRARI, Ernest ADIQUE, Paul AITCHISON, Daniel FUDGE, Kari HEIKURINEN, Paul STONE, Tibor URAC
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Patent number: 10443411Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.Type: GrantFiled: September 18, 2017Date of Patent: October 15, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Thomas Veitch, Farid Abrari, Ernest Adique, Paul Aitchison, Daniel Fudge, Kari Heikurinen, Paul Stone, Tibor Urac
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Publication number: 20190085868Abstract: A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.Type: ApplicationFiled: September 15, 2017Publication date: March 21, 2019Inventors: Karan ANAND, Farid ABRARI, Ernest ADIQUE, Paul AITCHISON, Daniel FUDGE, Kari HEIKURINEN, Paul STONE, Tibor URAC, Thomas VEITCH
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Publication number: 20190085708Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.Type: ApplicationFiled: September 18, 2017Publication date: March 21, 2019Inventors: Thomas VEITCH, Farid ABRARI, Ernest ADIQUE, Paul AITCHISON, Daniel FUDGE, Kari HEIKURINEN, Paul STONE, Tibor URAC
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Patent number: 9376935Abstract: A casing for an aircraft engine includes an outer ring and an inner hub defining an airflow passage therebetween, the outer ring having an axis defining an axial direction; a plurality of struts arranged in a circumferential array and extending radially from the inner hub to the outer ring to mount the inner hub to the outer ring; wherein the outer ring is defined by a double skin including an axially-extending annular outer skin of sheet metal concentrically surrounding and radially-spaced from an annular inner skin of sheet metal, the outer and inner skins generally parallel to one another, an annular front end ring and an annular rear end ring welded or brazed to the outer and inner skins adjacent respective front and rear edges of the skins to define an annular cavity between them, and the outer ring further comprising a plurality of circumferentially spaced axially-extending ribs interconnecting the outer and inner skins to reinforce the double skins.Type: GrantFiled: December 18, 2012Date of Patent: June 28, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Andreas Eleftheriou, Denis Leclair, David Denis, David Menheere, Paul Aitchison
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Publication number: 20140165533Abstract: A casing for an aircraft engine includes an outer ring and an inner hub defining an airflow passage therebetween, the outer ring having an axis defining an axial direction; a plurality of struts arranged in a circumferential array and extending radially from the inner hub to the outer ring to mount the inner hub to the outer ring; wherein the outer ring is defined by a double skin including an axially-extending annular outer skin of sheet metal concentrically surrounding and radially-spaced from an annular inner skin of sheet metal, the outer and inner skins generally parallel to one another, an annular front end ring and an annular rear end ring welded or brazed to the outer and inner skins adjacent respective front and rear edges of the skins to define an annular cavity between them, and the outer ring further comprising a plurality of circumferentially spaced axially-extending ribs interconnecting the outer and inner skins to reinforce the double skins.Type: ApplicationFiled: December 18, 2012Publication date: June 19, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Andreas ELEFTHERIOU, Denis LECLAIR, David DENIS, David MENHEERE, Paul AITCHISON
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Patent number: 8490409Abstract: A fluid-conveying device including an inner tubular member with a circumferential end portion, a non-elastomeric ring received in a depression of the end portion, and an outer tubular member. The ring has a peripheral surface with a rounded contour defined along a longitudinal direction configured to remain out of the depression to engage the outer tubular member and facilitate sealing thereof.Type: GrantFiled: October 1, 2009Date of Patent: July 23, 2013Assignee: Pratt & Whitney Canada Corp.Inventors: Tania Pucovsky, Paul Aitchison, Brian Healey
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Publication number: 20110079018Abstract: A fluid-conveying device including an inner tubular member with a circumferential end portion, a non-elastomeric ring received in a depression of the end portion, and an outer tubular member. The ring has a peripheral surface with a rounded contour defined along a longitudinal direction configured to remain out of the depression to engage the outer tubular member and facilitate sealing thereof.Type: ApplicationFiled: October 1, 2009Publication date: April 7, 2011Inventors: TANIA PUCOVSKY, Paul Aitchison, Brian Healey
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Publication number: 20050116114Abstract: A fluid flow actuated valve for controlling the fluid flow in a conduit comprises a support structure adapted to be mounted within the conduit and at least one flap member pivotally mounted to the support structure. The at least one flap member is pivotable between an first position for a minimum fluid flow and a second position for a maximum fluid flow. A torsion spring is attached to the at least one flap member to urge the same to pivot against a fluid pressure differential, from the first position to the second position when the fluid pressure differential is smaller than a predetermined level.Type: ApplicationFiled: December 17, 2004Publication date: June 2, 2005Applicant: Pratt & Whitney Canada Corp.Inventors: Paul Aitchison, Patrick Germain, Henry Smith