Patents by Inventor Othmane Leghzaouni
Othmane Leghzaouni 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: 11913356Abstract: A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.Type: GrantFiled: December 8, 2021Date of Patent: February 27, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Chao Zhang, Robert Huszar, Othmane Leghzaouni
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Patent number: 11578599Abstract: A rotor assembly comprises a rotor having annular flange including a plurality of protrusions axisymmetrically disposed about the annular flange, each protrusion having a mounting aperture for selectively receiving a balancing feature, and a plurality of slots axisymmetrically disposed about the circumference of the annular flange between adjacent protrusions. Each slot has a pair of converging flat portions extending axially inwardly from an adjacent protrusion end, an inner flat portion at an inner end of each slot, and a pair of curved portions respectively joining each converging flat portion to the inner flat portion in each slot. Each slot has a depth at least as great as an adjacent mounting aperture depth extending normally from the adjacent protrusion end to a far end of the corresponding mounting aperture.Type: GrantFiled: February 2, 2021Date of Patent: February 14, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Franco Di Paola, Othmane Leghzaouni, Thierry Stocco
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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: 11572789Abstract: 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: Constantinos Ravanis, Vincent Paradis, Eduardo Hawie, Michael Papple, Marc-Antoine Mailloux-Labrousse, Othmane Leghzaouni, Philippe Boyer, Jasrobin Grewal
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Patent number: 11512595Abstract: 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: February 4, 2022Date of Patent: November 29, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Fariba Ajalli, Panagiota Tsifourdaris, Michael Paolucci, Othmane Leghzaouni, Stephane Bigras
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Publication number: 20220243593Abstract: A rotor assembly comprises a rotor having annular flange including a plurality of protrusions axisymmetrically disposed about the annular flange, each protrusion having a mounting aperture for selectively receiving a balancing feature, and a plurality of slots axisymmetrically disposed about the circumference of the annular flange between adjacent protrusions. Each slot has a pair of converging flat portions extending axially inwardly from an adjacent protrusion end, an inner flat portion at an inner end of each slot, and a pair of curved portions respectively joining each converging flat portion to the inner flat portion in each slot. Each slot has a depth at least as great as an adjacent mounting aperture depth extending normally from the adjacent protrusion end to a far end of the corresponding mounting aperture.Type: ApplicationFiled: February 2, 2021Publication date: August 4, 2022Inventors: Franco DI PAOLA, Othmane LEGHZAOUNI, Thierry STOCCO
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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: 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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Publication number: 20220098990Abstract: A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.Type: ApplicationFiled: December 8, 2021Publication date: March 31, 2022Inventors: Chao ZHANG, Robert HUSZAR, Othmane LEGHZAOUNI
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Patent number: 11220919Abstract: A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.Type: GrantFiled: July 18, 2019Date of Patent: January 11, 2022Assignee: PRATT & WHTNEY CANADA CORP.Inventors: Chao Zhang, Robert Huszar, Othmane Leghzaouni
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Patent number: 11118462Abstract: A turbine blade for a gas turbine engine, the turbine blade having a peripheral blade tip wall surrounding a radially recessed tip pocket, the peripheral blade tip wall having: a wall height; a leading edge; a trailing edge; a pressure side wall; and a suction side wall; and a rib extending between the pressure side wall and the suction side wall defining a leading portion and a trailing portion of the radially recessed tip pocket, the rib having a rib height less than the wall height.Type: GrantFiled: January 24, 2019Date of Patent: September 14, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Vincent Paradis, Othmane Leghzaouni, Masoud Roshan Fekr, Marc-Antoine Mailloux-Labrousse
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Patent number: 11021975Abstract: The gas turbine engine can have a first and second rotary components structurally joined to one another via a connector, a first spigot fit between the connector and the first rotary component, the first spigot fit forming an interference fit at a first operating condition and forming a gap at a second operating condition, a second spigot fit between the connector and the first rotary component, the second spigot fit forming an interference fit at the second operating condition and forming a gap at the first operating condition, the gas turbine engine being further configured to form a radial interference fit between the connector and the second rotary component in both the first and second operating conditions.Type: GrantFiled: February 12, 2019Date of Patent: June 1, 2021Assignee: PRATT & WHITNEY CANADA CORPInventors: Marc-Antoine Mailloux-Labrousse, Othmane Leghzaouni, Yves Roussel, Max Bergeron-Fillion
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Patent number: 10934874Abstract: An assembly comprising a blade including a blade portion, a root portion and a platform portion between the blade portion and the root portion, the platform portion defining at least one cavity opened laterally. An abutment projects from a wall portion of the cavity at a trailing end of the blade. A seal is received in the cavity and positioned along a periphery of the cavity, the seal having a trailing edge abutting against the abutment.Type: GrantFiled: February 6, 2019Date of Patent: March 2, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Lorenzo Sanzari, Othmane Leghzaouni
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Publication number: 20210017865Abstract: A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.Type: ApplicationFiled: July 18, 2019Publication date: January 21, 2021Inventors: Chao ZHANG, Robert HUSZAR, Othmane LEGHZAOUNI
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Publication number: 20200256203Abstract: The gas turbine engine can have a first and second rotary components structurally joined to one another via a connector, a first spigot fit between the connector and the first rotary component, the first spigot fit forming an interference fit at a first operating condition and forming a gap at a second operating condition, a second spigot fit between the connector and the first rotary component, the second spigot fit forming an interference fit at the second operating condition and forming a gap at the first operating condition, the gas turbine engine being further configured to form a radial interference fit between the connector and the second rotary component in both the first and second operating conditions.Type: ApplicationFiled: February 12, 2019Publication date: August 13, 2020Inventors: Marc-Antoine MAILLOUX-LABROUSSE, Othmane LEGHZAOUNI, Yves ROUSSEL, Max BERGERON-FILLION
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Publication number: 20200248576Abstract: An assembly comprising a blade including a blade portion, a root portion and a platform portion between the blade portion and the root portion, the platform portion defining at least one cavity opened laterally. An abutment projects from a wall portion of the cavity at a trailing end of the blade. A seal is received in the cavity and positioned along a periphery of the cavity, the seal having a trailing edge abutting against the abutment.Type: ApplicationFiled: February 6, 2019Publication date: August 6, 2020Inventors: Lorenzo SANZARI, Othmane LEGHZAOUNI
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Publication number: 20200240274Abstract: A turbine blade for a gas turbine engine, the turbine blade having a peripheral blade tip wall surrounding a radially recessed tip pocket, the peripheral blade tip wall having: a wall height; a leading edge; a trailing edge; a pressure side wall; and a suction side wall; and a rib extending between the pressure side wall and the suction side wall defining a leading portion and a trailing portion of the radially recessed tip pocket, the rib having a rib height less than the wall height.Type: ApplicationFiled: January 24, 2019Publication date: July 30, 2020Inventors: Vincent PARADIS, Othmane LEGHZAOUNI, Masoud ROSHAN FEKR, Marc-Antoine MAILLOUX-LABROUSSE
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Patent number: 7357623Abstract: A rotor blade of a gas turbine engine includes a blade root defining a cooling airflow entry cavity therein, in fluid communication with internal cooling air passages through the blade. The cavity includes opposed side walls and at least one divider wall extending therebetween. At least one end portion of the divider walls adjoins one of the side walls in an angled direction relative to a perpendicular direction of the side walls.Type: GrantFiled: May 23, 2005Date of Patent: April 15, 2008Assignee: Pratt & Whitney Canada Corp.Inventors: Othmane Leghzaouni, Ghislain Plante
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Publication number: 20080050238Abstract: A turbine rotor disc includes a plurality of attachment slots for receiving firtree-profiled blade roots. Each attachment slot is formed in an undulating profile having substantially smoothly curved and laterally, alternately recessed and projecting portions. At least one pair of substantially smoothly curved projecting portions being truncated at a tip thereof, respectively.Type: ApplicationFiled: August 24, 2006Publication date: February 28, 2008Inventors: Eric Durocher, Minh Loc Tran, Othmane Leghzaouni
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Publication number: 20060263218Abstract: A rotor blade of a gas turbine engine includes a blade root defining a cooling airflow entry cavity therein, in fluid communication with internal cooling air passages through the blade. The cavity includes opposed side walls and at least one divider wall extending therebetween. At least one end portion of the divider walls adjoins one of the side walls in an angled direction relative to a perpendicular direction of the side walls.Type: ApplicationFiled: May 23, 2005Publication date: November 23, 2006Inventors: Othmane Leghzaouni, Ghislain Plante