Patents by Inventor Nicolas Grivas
Nicolas Grivas 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: 11572790Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.Type: GrantFiled: November 11, 2021Date of Patent: February 7, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Remo Marini, Panagiota Tsifourdaris, Nicolas Grivas, Daniel Lecuyer, Michael Papple, Robert Huszar, Othmane Leghzaouni, Jonathan Dorai, Jasrobin Grewal
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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: 10443451Abstract: A shroud mounting arrangement comprises a shroud housing and a shroud mounted to the shroud housing. The shroud is configured to surround a stage of rotor blades of a gas turbine engine. A circumferentially segmented vane ring is disposed axially adjacent to the stage of rotor blades. The circumferentially segmented vane ring comprises a plurality of vane segments. The vane segments jointly support the shroud housing.Type: GrantFiled: July 18, 2016Date of Patent: October 15, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Guy Lefebvre, Nicolas Grivas, Vincent Paradis
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Publication number: 20180016943Abstract: A shroud mounting arrangement comprises a shroud housing and a shroud mounted to the shroud housing. The shroud is configured to surround a stage of rotor blades of a gas turbine engine. A circumferentially segmented vane ring is disposed axially adjacent to the stage of rotor blades. The circumferentially segmented vane ring comprises a plurality of vane segments. The vane segments jointly support the shroud housing.Type: ApplicationFiled: July 18, 2016Publication date: January 18, 2018Inventors: GUY LEFEBVRE, NICOLAS GRIVAS, VINCENT PARADIS
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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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Patent number: 8876463Abstract: A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil.Type: GrantFiled: July 16, 2013Date of Patent: November 4, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Eric Durocher, Nicolas Grivas
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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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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: 20140133962Abstract: A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil.Type: ApplicationFiled: July 16, 2013Publication date: May 15, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Eric DUROCHER, Nicolas GRIVAS
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Patent number: 8578584Abstract: A method for centering an engine structure such as a bearing housing is provided which may be used, for example, during assembly of a mid turbine frame or other engine case structure. In one aspect, the method includes using spacers with respective radial spokes which connect inner and outer portions of the case. In another aspect, centering may be provided by machining selected contacting surfaces of selected components.Type: GrantFiled: October 19, 2012Date of Patent: November 12, 2013Assignee: Pratt & Whitney Canada Corp.Inventors: Eric Durocher, John Pietrobon, Nicolas Grivas
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Patent number: 8511969Abstract: A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil.Type: GrantFiled: October 1, 2009Date of Patent: August 20, 2013Assignee: Pratt & Whitney Canada Corp.Inventors: Eric Durocher, Nicolas Grivas
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Patent number: 8316523Abstract: A method for centering an engine structure such as a bearing housing is provided which may be used, for example, during assembly of a mid turbine frame or other engine case structure. In one aspect, the method includes using spacers with respective radial spokes which connect inner and outer portions of the case. In another aspect, centring may be provided by machining selected contacting surfaces of selected components.Type: GrantFiled: October 1, 2009Date of Patent: November 27, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Eric Durocher, John Pietrobon, Nicolas Grivas
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Patent number: 8166767Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.Type: GrantFiled: October 15, 2010Date of Patent: May 1, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Nicolas Grivas, Bhawan B. Patel, Oleg Morenko, Eric Durocher
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Publication number: 20110081228Abstract: A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil.Type: ApplicationFiled: October 1, 2009Publication date: April 7, 2011Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Eric DUROCHER, Nicolas GRIVAS
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Publication number: 20110078902Abstract: A method for centering an engine structure such as a bearing housing is provided which may be used, for example, during assembly of a mid turbine frame or other engine case structure. In one aspect, the method includes using spacers with respective radial spokes which connect inner and outer portions of the case. In another aspect, centring may be provided by machining selected contacting surfaces of selected components.Type: ApplicationFiled: October 1, 2009Publication date: April 7, 2011Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Eric DUROCHER, John PIETROBON, Nicolas GRIVAS
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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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Publication number: 20110023499Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.Type: ApplicationFiled: October 15, 2010Publication date: February 3, 2011Inventors: Nicolas GRIVAS, Bhawan B. Patel, Oleg Morenko, Eric Durocher
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Patent number: 7836702Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.Type: GrantFiled: September 15, 2006Date of Patent: November 23, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Nicolas Grivas, Bhawan B. Patel, Oleg Morenko, Eric Durocher
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Publication number: 20100236257Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.Type: ApplicationFiled: September 15, 2006Publication date: September 23, 2010Inventors: Nicolas GRIVAS, Bhawan B. Patel, Oleg Morenko, Eric Durocher