Patents by Inventor Daniel Lecuyer
Daniel Lecuyer 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: 11867081Abstract: 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: January 26, 2023Date of Patent: January 9, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Abdulhalim Twahir, Panagiota Tsifourdaris, Daniel Lecuyer, Masoud Roshan Fekr, Stephane Bigras
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Patent number: 11603763Abstract: 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 12, 2021Date of Patent: March 14, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Abdulhalim Twahir, Panagiota Tsifourdaris, Niloofar Moradi, Daniel Lecuyer, Jocelyn Menard
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Patent number: 11578607Abstract: An airfoil for a gas turbine engine, which has an airfoil body extending in a spanwise direction and in a chordwise direction, a platform located at an inner end and/or an outer end of the airfoil body, and a fillet at a junction between the airfoil body and the platform. The fillet has a radius distribution at a given chordwise location, the radius distribution varying from the platform to the airfoil body in the spanwise direction. The radius distribution defines a local minimum, the radius of the fillet at the given chordwise location increasing from the local minimum along the spanwise direction toward both of the airfoil and the platform. A local maximum of the radius distribution is offset from the local minimum along the spanwise direction, the radius decreasing from the local maximum along the spanwise direction toward both of the airfoil and the platform.Type: GrantFiled: December 15, 2020Date of Patent: February 14, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Daniel Lecuyer, Michael Paolucci, Francis Gemme
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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: 11536141Abstract: A turbine vane 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. The 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: February 4, 2022Date of Patent: December 27, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Mohammed Ennacer, Panagiota Tsifourdaris, Remo Marini, Niloofar Moradi, Daniel Lecuyer, Patricia Phutthavong, Farzad Ashrafi
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Patent number: 11371359Abstract: A turbine blade for a gas turbine engine has: an airfoil extending along a span from a base to a tip and along a chord from a leading edge to a trailing edge, the airfoil having a pressure side and a suction side, a tip pocket at the tip of the airfoil, the tip pocket at least partially surrounded by a peripheral tip wall defining a portion of the pressure and suction sides; at least one internal cooling passage in the airfoil and having at least one outlet communicating with the tip pocket; and a reinforcing bump located on the pressure side of the airfoil and protruding from a baseline surface of the peripheral tip wall to a bump end located into the tip pocket, the reinforcing bump overlapping a location where a curvature of a concave portion of the pressure side of the airfoil is maximal.Type: GrantFiled: November 26, 2020Date of Patent: June 28, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Daniel Lecuyer, Othmane Leghzaouni
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Publication number: 20220186622Abstract: An airfoil for a gas turbine engine, which has an airfoil body extending in a spanwise direction and in a chordwise direction, a platform located at an inner end and/or an outer end of the airfoil body, and a fillet at a junction between the airfoil body and the platform. The fillet has a radius distribution at a given chordwise location, the radius distribution varying from the platform to the airfoil body in the spanwise direction. The radius distribution defines a local minimum, the radius of the fillet at the given chordwise location increasing from the local minimum along the spanwise direction toward both of the airfoil and the platform. A local maximum of the radius distribution is offset from the local minimum along the spanwise direction, the radius decreasing from the local maximum along the spanwise direction toward both of the airfoil and the platform.Type: ApplicationFiled: December 15, 2020Publication date: June 16, 2022Inventors: Daniel LECUYER, Michael PAOLUCCI, Francis GEMME
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Publication number: 20220162948Abstract: A turbine blade for a gas turbine engine has: an airfoil extending along a span from a base to a tip and along a chord from a leading edge to a trailing edge, the airfoil having a pressure side and a suction side, a tip pocket at the tip of the airfoil, the tip pocket at least partially surrounded by a peripheral tip wall defining a portion of the pressure and suction sides; at least one internal cooling passage in the airfoil and having at least one outlet communicating with the tip pocket; and a reinforcing bump located on the pressure side of the airfoil and protruding from a baseline surface of the peripheral tip wall to a bump end located into the tip pocket, the reinforcing bump overlapping a location where a curvature of a concave portion of the pressure side of the airfoil is maximal.Type: ApplicationFiled: November 26, 2020Publication date: May 26, 2022Inventors: Daniel LECUYER, Othmane LEGHZAOUNI
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Patent number: 11199096Abstract: A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.75-2.20 inches. A chord length at 50% span is 1.05-1.35 inches. At least two of: a first mode resonance frequency is 2400±10% Hz; a second mode resonance frequency is 4950±10% Hz; a third mode resonance frequency is 7800±10% Hz; a fourth mode resonance frequency is 8700±10% Hz; and a fifth mode resonance frequency is 12500±10% Hz.Type: GrantFiled: January 15, 2018Date of Patent: December 14, 2021Assignee: Raytheon Technologies CorporationInventors: Michael Leslie Clyde Papple, David A. Niezelski, Daniel Lecuyer, XingYun Haggard, Domenico Di Florio, Francois Caron, John R. Battye, Panagiota Tsifourdaris, Ghislain Plante, Timothy J. Jennings, Rene Paquet
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Publication number: 20210199017Abstract: A blade for mounting on a rotor disc of a gas turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.Type: ApplicationFiled: March 15, 2021Publication date: July 1, 2021Inventors: Daniel LECUYER, Robert HUSZAR
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Patent number: 10975714Abstract: The gas turbine engine rotor assembly includes a rotor disc with a plurality of sealing tabs projecting radially out from a peripheral surface of the rotor disc in the rear end portion thereof. A said sealing tab is disposed at a tip portion of a fixing member of the disc, formed between pairs of blade root slots, adjacent a trailing edge of the rotor disc. The sealing tabs help to reduce the leakage of secondary air out the back of a blade pocket defined between adjacent blades mounted on the rotor disc.Type: GrantFiled: November 22, 2018Date of Patent: April 13, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Daniel Lecuyer, Robert Huszar
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Patent number: 10876429Abstract: An annular shroud assembly for a gas turbine engine is provided. The annular shroud assembly includes a plurality of first shroud segments having a same first arcuate length within a tolerance, at least one second shroud segment having a second arcuate length different than the first arcuate length and outside the tolerance, a plurality of first intersegment gaps between adjacent first segments, the first intersegment gaps having a circumferential dimension within a desired controlled range of dimensions, and at least two second intersegment gaps between opposed ends of the second segment and adjacent first segment. The first and second intersegment gaps are within the desired controlled range. Methods for controlling intersegment gaps between a plurality of shroud segments forming an annular shroud assembly and for forming such annular shroud assembly are also provided.Type: GrantFiled: March 21, 2019Date of Patent: December 29, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Guy Lefebvre, Daniel Lecuyer
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Publication number: 20200300124Abstract: An annular shroud assembly for a gas turbine engine is provided. The annular shroud assembly includes a plurality of first shroud segments having a same first arcuate length within a tolerance, at least one second shroud segment having a second arcuate length different than the first arcuate length and outside the tolerance, a plurality of first intersegment gaps between adjacent first segments, the first intersegment gaps having a circumferential dimension within a desired controlled range of dimensions, and at least two second intersegment gaps between opposed ends of the second segment and adjacent first segment. The first and second intersegment gaps are within the desired controlled range. Methods for controlling intersegment gaps between a plurality of shroud segments forming an annular shroud assembly and for forming such annular shroud assembly are also provided.Type: ApplicationFiled: March 21, 2019Publication date: September 24, 2020Inventors: Guy LEFEBVRE, Daniel LECUYER
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Publication number: 20200165926Abstract: The gas turbine engine rotor assembly includes a rotor disc with a plurality of sealing tabs projecting radially out from a peripheral surface of the rotor disc in the rear end portion thereof. A said sealing tab is disposed at a tip portion of a fixing member of the disc, formed between pairs of blade root slots, adjacent a trailing edge of the rotor disc. The sealing tabs help to reduce the leakage of secondary air out the back of a blade pocket defined between adjacent blades mounted on the rotor disc.Type: ApplicationFiled: November 22, 2018Publication date: May 28, 2020Inventors: Daniel LECUYER, Robert HUSZAR
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Patent number: 10174626Abstract: A partially coated blade for a gas turbine engine, including a fillet surface surrounding the airfoil section and connecting it to the platform section. A radially outermost portion of the pressure side and leading edge is covered by a thermal barrier coating. This portion extends radially from a first limit to the blade tip. The first limit is located at a radial distance from the platform of at most 21% of the maximum span. The fillet surface is free or substantially free of the thermal barrier coating. In another embodiment, a second portion of the pressure side and of the leading edge is free or substantially free of the thermal barrier coating, extending radially from the platform section to a second limit located a radial distance from the platform section corresponding to at least 5% of the maximum span. A method of applying a thermal barrier coating is also discussed.Type: GrantFiled: October 15, 2014Date of Patent: January 8, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael Papple, Daniel Lecuyer
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Patent number: 9581029Abstract: A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one set of holes selected from the group consisting of a first set, a second set, a third set, a fourth set, a fifth set and a sixth set, wherein the first, second, third, fourth, fifth and sixth sets of holes respectively include the holes numbered A1 to A8, B1 to B10, C1 to C9, D1 to D6, E1 to E7 and F1 to F6 each located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.Type: GrantFiled: September 24, 2014Date of Patent: February 28, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael Papple, Daniel LeCuyer
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Patent number: 9328621Abstract: A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring. The resilient fingers are configured each to radially abut a blade seal, damper or other engine component against radially inner facing surfaces of platforms of the respective blades when the blades are being seated onto the disc during an assembly procedure.Type: GrantFiled: January 21, 2014Date of Patent: May 3, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Joseph Daniel Lecuyer, Bruno Chatelois
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Publication number: 20160108742Abstract: A partially coated blade for a gas turbine engine, including a fillet surface surrounding the airfoil section and connecting it to the platform section. A radially outermost portion of the pressure side and leading edge is covered by a thermal barrier coating. This portion extends radially from a first limit to the blade tip. The first limit is located at a radial distance from the platform of at most 21% of the maximum span. The fillet surface is free or substantially free of the thermal barrier coating. In another embodiment, a second portion of the pressure side and of the leading edge is free or substantially free of the thermal barrier coating, extending radially from the platform section to a second limit located a radial distance from the platform section corresponding to at least 5% of the maximum span. A method of applying a thermal barrier coating is also discussed.Type: ApplicationFiled: October 15, 2014Publication date: April 21, 2016Inventors: Michael PAPPLE, Daniel LECUYER
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Publication number: 20160084091Abstract: A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one set of holes selected from the group consisting of a first set, a second set, a third set, a fourth set, a fifth set and a sixth set, wherein the first, second, third, fourth, fifth and sixth sets of holes respectively include the holes numbered A1 to A8, B1 to B10, C1 to C9, D1 to D6, E1 to E7 and F1 to F6 each located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.Type: ApplicationFiled: September 24, 2014Publication date: March 24, 2016Inventors: Michael PAPPLE, Daniel LECUYER
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Patent number: 9127556Abstract: A rotor disc, such as one made of a damage intolerant material or other material sensitive to stress concentrations, has at least one balancing assembly which includes a plurality of circumferentially spaced-apart sacrificial protrusions projecting between adjacent stress-relieving slots. Selective material removal is permitted from the rotor disc, while managing stress concentrations in the rotor disc created by such material removal, such that the rotor disc may be balanced without detrimentally affecting its service life.Type: GrantFiled: November 30, 2012Date of Patent: September 8, 2015Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Christian Pronovost, Joseph Daniel Lecuyer