Patents by Inventor Denis Leclair
Denis Leclair 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: 10760527Abstract: An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.Type: GrantFiled: February 9, 2016Date of Patent: September 1, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Guy Lefebvre, Nicolas Grivas, Richard Bouchard, Denis Leclair, Eric Durocher
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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: 20160153398Abstract: An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.Type: ApplicationFiled: February 9, 2016Publication date: June 2, 2016Inventors: Guy Lefebvre, Nicolas Grivas, Richard Bouchard, Denis Leclair, Eric Durocher
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Patent number: 9284915Abstract: An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.Type: GrantFiled: April 28, 2014Date of Patent: March 15, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Guy Lefebvre, Nicolas Grivas, Richard Bouchard, Denis Leclair, Eric Durocher
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Publication number: 20140230404Abstract: An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.Type: ApplicationFiled: April 28, 2014Publication date: August 21, 2014Applicant: Pratt & Whitney Canada Corp.Inventors: Guy LEFEBVRE, Nicolas GRIVAS, Richard BOUCHARD, Denis LECLAIR, Eric DUROCHER
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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: 8739513Abstract: An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.Type: GrantFiled: August 17, 2010Date of Patent: June 3, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Guy Lefebvre, Nicolas Grivas, Richard Bouchard, Denis Leclair, Eric Durocher
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Publication number: 20110036068Abstract: An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.Type: ApplicationFiled: August 17, 2010Publication date: February 17, 2011Inventors: Guy LEFEBVRE, Nicolas GRIVAS, Richard BOUCHARD, Denis LECLAIR, Eric DUROCHER
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Patent number: 7797922Abstract: A casing for an aircraft turbine bypass engine comprises a splitter having slots to receive and be welded to a plurality of struts extending between an outer ring and an inner hub of the casing.Type: GrantFiled: June 4, 2007Date of Patent: September 21, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Andreas Eleftheriou, David Denis, Denis Leclair, Yves Roussel
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Patent number: 7658545Abstract: A foil-fluid bearing assembly adapted for supporting a shaft within an outer bearing housing and is adapted for accommodating angular misalignment of the rotating shaft relative to the housing.Type: GrantFiled: April 2, 2004Date of Patent: February 9, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Jean Dubreuil, Denis Leclair
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Publication number: 20090185766Abstract: A foil-fluid bearing assembly adapted for supporting a shaft within an outer bearing housing and is adapted for accommodating angular misalignment of the rotating shaft relative to the housing.Type: ApplicationFiled: April 2, 2004Publication date: July 23, 2009Inventors: Jean Dubreuil, Denis Leclair
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Publication number: 20080292229Abstract: A foil-fluid bearing assembly adapted for supporting a shaft within an outer bearing housing and is adapted for accommodating angular misalignment of the rotating shaft relative to the housing.Type: ApplicationFiled: April 2, 2004Publication date: November 27, 2008Inventors: Jean Dubreuil, Denis Leclair
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Publication number: 20080073154Abstract: An oil feed assembly suitable for use in a gas turbine engine having a bearing housing, an outer ring surrounding the bearing housing and a monocase extending therebetween. The assembly provides an oil supply tube for extension within the monocase and between the outer ring and the bearing housing. An oil nozzle support means is employed for selective releasable engagement with one end of the oil supply tube. This is also supported by an oil supply tube support means for selective releasable engagement with a second end of the oil supply tube. A coupling means for coupling said oil supply tube support means and the outer ring completes the assembly.Type: ApplicationFiled: September 27, 2006Publication date: March 27, 2008Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Andreas ELEFTHERIOU, David DENIS, Denis LECLAIR, Julien GARON, Jean FOURNIER
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Publication number: 20070280819Abstract: A casing for an aircraft turbine bypass engine comprises a splitter having slots to receive and be welded to a plurality of struts extending between an outer ring and an inner hub of the casing.Type: ApplicationFiled: June 4, 2007Publication date: December 6, 2007Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Andreas ELEFTHERIOU, David DENIS, Denis LECLAIR, Yves ROUSSEL
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Patent number: 6786642Abstract: A foil-fluid bearing assembly adapted for supporting a shaft within an outer bearing housing. The foil-fluid bearing assembly comprises a bearing sleeve having an outer surface and an inner circumferential surface diametrically sized to receive the shaft therewithin such that an annular clearance gap, radially defined between an outer surface of the shaft and the inner circumferential surface, is adapted for accommodating fluid therein and axially extends along a substantial portion of a length of the bearing sleeve, and has a foil element disposed therewithin. Compliant bearing supports between the outer surface of the bearing sleeve and the outer bearing housing, comprises at least two independent compliant support elements respectively having a first and a second modulus of elasticity, wherein the first modulus of elasticity is less than the second modulus of elasticity. Angular misalignment capability for the foil-fluid bearing is provided by the compliant support elements.Type: GrantFiled: August 30, 2002Date of Patent: September 7, 2004Assignee: Pratt & Whitney Canada Corp.Inventors: Jean Dubreuil, Denis Leclair
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Publication number: 20040042693Abstract: A foil-fluid bearing assembly adapted for supporting a shaft within an outer bearing housing. The foil-fluid bearing assembly comprises a bearing sleeve having an outer surface and an inner circumferential surface diametrically sized to receive the shaft therewithin such that an annular clearance gap, radially defined between an outer surface of the shaft and the inner circumferential surface, is adapted for accommodating fluid therein and axially extends along a substantial portion of a length of the bearing sleeve, and has a foil element disposed therewithin. Compliant bearing supports between the outer surface of the bearing sleeve and the outer bearing housing, comprises at least two independent compliant support elements respectively having a first and a second modulus of elasticity, wherein the first modulus of elasticity is less than the second modulus of elasticity. Angular misalignment capability for the foil-fluid bearing is provided by the compliant support elements.Type: ApplicationFiled: August 30, 2002Publication date: March 4, 2004Inventors: Jean Dubreuil, Denis Leclair
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Patent number: 6155056Abstract: The invention provides in a gas turbine engine combustion chamber, an array of elongate louver strips between fuel nozzles of a combustion chamber dome wall, to cool the dome wall and contain combustion gases in the area between nozzles. The elongate louver strips are each disposed symmetrically along the median line on the inner surface dome wall and extend between each nozzle cup of the annular array. Each strip includes an elongate flange extending into the combustion chamber from the inner dome wall. The flange has an inner surface, and lateral side walls, with the inner surface generally parallel to the inner surface of the dome wall. Compressed air outlets are disposed along each flange lateral side wall, for directing a compressed air film along the inner surface of the dome wall in a direction away from the median line. A compressed air inlet extends from the outer surface of the dome wall to the outlets.Type: GrantFiled: June 4, 1998Date of Patent: December 5, 2000Assignee: Pratt & Whitney Canada Corp.Inventors: Parthasarathy Sampath, Andre Chevrefils, Denis Leclair, Robert Desroches