Patents by Inventor Jean-Claude Marcel Auguste Hanny
Jean-Claude Marcel Auguste Hanny 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: 10926444Abstract: An assembly for manufacturing a wax moulding of a turbine engine blade has a wax injection mould in which a core is able to be mounted in a predetermined moulding position, the core including a main element and at least a first secondary element each including at least one functional part and a non-functional part, wherein the non-functional part of the first secondary element includes a rod portion extending in a longitudinal direction of the blade and housed in a first slot of the non-functional part of the main member, the mould including a first internal boss clamping said rod portion at the bottom of the first slot.Type: GrantFiled: April 26, 2018Date of Patent: February 23, 2021Assignees: Safran, Safran Aircraft EnginesInventors: Jean-Claude Marcel Auguste Hanny, Pascal Francis Patrick Gomez, Daniel Quach, Adrien Bernard Vincent Rollinger, Joseph Toussaint Tami Lizuzu, Matthieu Jean Luc Vollebregt
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Patent number: 10576535Abstract: A ceramic material mold for use in molding a turbine engine blade from a molten metal, the blade including a root, an inner platform, an airfoil, and an outer platform, and the mold including a cavity having the shape of the blade, and an auxiliary grain duct including a first segment and a second segment that is an extension of the first segment, the first segment opening out at one end into a first portion of the cavity forming the root of the blade, and at another end into a second portion of the cavity forming a lip of the inner platform of the blade, the second segment opening out at one end into the second portion of the cavity, and at another end into a third portion of the cavity forming a lip of the outer platform of the blade.Type: GrantFiled: June 1, 2017Date of Patent: March 3, 2020Assignees: SAFRAN, SAFRAN AIRCRAFT ENGINESInventors: Ngadia Taha Niane, Saïd Boukerma, Serge Dillenseger, Julien Gelebart, David Grange, Jean-Claude Marcel Auguste Hanny, Philippe Metron
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Patent number: 10533426Abstract: A method for manufacturing a turbine engine blade (25) comprising a pressure side and a suction side separated from one another by an inner space for the circulation of cooling air, the blade (25) comprising a tip (S) with a closing wall (29) joining the pressure side and suction side walls in the region of this tip (S) in order to define a well shape, the closing wall including through-holes. The closing wall (29) obtained by moulding has a considerable nominal thickness with pits (36, 37) locally reducing this thickness at each through-hole in order to facilitate the removal by chemical etching of alumina rods defining the holes. Since the closing wall (29) thus has a large nominal thickness, it can then be machined in order to form raised patterns or complex shapes inside the well.Type: GrantFiled: December 15, 2015Date of Patent: January 14, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Dominique Coyez, Christian Bariaud, Sami Benichou, Jean-Claude Marcel Auguste Hanny
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Patent number: 10486226Abstract: A core used in the manufacture, by lost-wax casting, of a turbomachine blade, includes a main element and at least one first secondary element, each including a functional part and a non-functional part. The non-functional part of the main element and the non-functional part of the at least one first secondary element are assembled and shaped so as to cooperate with each other by sliding in a longitudinal direction extending between the base and the top of a blade and by rotating around the longitudinal direction.Type: GrantFiled: April 26, 2018Date of Patent: November 26, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Daniel Quach, Pascal Francis Patrick Gomez, Coralie Cinthia Guerard, Jean-Claude Marcel Auguste Hanny, Patrick Emilien Paul Emile Huchin, Joseph Toussaint Tami Lizuzu, Matthieu Jean Luc Vollebregt, Vincent Marc Herb, Laetitia Person
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Publication number: 20190337048Abstract: A ceramic material mold for use in molding a turbine engine blade from a molten metal, the blade including a root, an inner platform, an airfoil, and an outer platform, and the mold including a cavity having the shape of the blade, and an auxiliary grain duct including a first segment and a second segment extending the first segment, the first segment opening out at one end into a first portion of the cavity forming the root of the blade, and at another end into a second portion of the cavity forming a lip of the inner platform of the blade, the second segment opening out at one end into the second portion of the cavity, and at another end into a third portion of the cavity forming a lip of the outer platform of the blade.Type: ApplicationFiled: June 1, 2017Publication date: November 7, 2019Inventors: Ngadia Taha NIANE, Saïd BOUKERMA, Serge DILLENSEGER, Julien GELEBART, David GRANGE, Jean-Claude Marcel Auguste HANNY, Philippe METRON
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Publication number: 20180311876Abstract: An assembly for manufacturing a wax moulding of a turbine engine blade has a wax injection mould in which a core is able to be mounted in a predetermined moulding position, the core including a main element and at least a first secondary element each including at least one functional part and a non-functional part, wherein the non-functional part of the first secondary element includes a rod portion extending in a longitudinal direction of the blade and housed in a first slot of the non-functional part of the main member, the mould including a first internal boss clamping said rod portion at the bottom of the first slot.Type: ApplicationFiled: April 26, 2018Publication date: November 1, 2018Applicants: Safran Aircraft Engines, SafranInventors: Jean-Claude Marcel Auguste Hanny, Pascal Francis Patrick Gomez, Daniel Quach, Adrien Bernard Vincent Rollinger, Joseph Toussaint Tami Lizuzu, Matthieu Jean Luc Vollebregt
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Publication number: 20180311722Abstract: A core used in the manufacture, by lost-wax casting, of a turbomachine blade, includes a main element and at least one first secondary element, each including a functional part and a non-functional part. The non-functional part of the main element and the non-functional part of the at least one first secondary element are assembled and shaped so as to cooperate with each other by sliding in a longitudinal direction extending between the base and the top of a blade and by rotating around the longitudinal direction.Type: ApplicationFiled: April 26, 2018Publication date: November 1, 2018Applicant: Safran Aircraft EnginesInventors: Daniel Quach, Pascal Francis Patrick Gomez, Coralie Cinthia Guerard, Jean-Claude Marcel Auguste Hanny, Patrick Emilien Paul Emile Huchin, Joseph Toussaint Tami Lizuzu, Matthieu Jean Luc Vollebregt, Vincent Marc Herb, Laetitia Person
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Publication number: 20170328222Abstract: A method for manufacturing a turbine engine blade (25) comprising a pressure side and a suction side separated from one another by an inner space for the circulation of cooling air, the blade (25) comprising a tip (S) with a closing wall (29) joining the pressure side and suction side walls in the region of this tip (S) in order to define a well shape, the closing wall including through-holes. The closing wall (29) obtained by moulding has a considerable nominal thickness with pits (36, 37) locally reducing this thickness at each through-hole in order to facilitate the removal by chemical etching of alumina rods defining the holes. Since the closing wall (29) thus has a large nominal thickness, it can then be machined in order to form raised patterns or complex shapes inside the well.Type: ApplicationFiled: December 15, 2015Publication date: November 16, 2017Applicant: Safran Aircraft EnginesInventors: Dominique Coyez, Christian Bariaud, Sami Benichou, Jean-Claude Marcel, Auguste Hanny
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Patent number: 8128375Abstract: The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, is disclosed. The blade includes an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ; and a connection zone between the airfoil and the airfoil end face. The connection zone forms a fattening of the airfoil. The connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil upstream of the suction face neck and a point P3 situated on the pressure face of the airfoil upstream of the pressure face neck.Type: GrantFiled: December 12, 2008Date of Patent: March 6, 2012Assignee: SNECMAInventors: Patrick Joseph Marie Girard, Jean-Claude Marcel Auguste Hanny, Renaud Martet, Olivier Charles Henri Massy, Philippe Jean-Pierre Pabion, Stephanie Dominique Roger
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Publication number: 20090155085Abstract: The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, comprising: an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element, an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ and a connection zone between the airfoil and said airfoil end face, said connection zone forming a fattening of the airfoil, is characterized in that said connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil upstream of the suction face neck and a point P3 situated on the pressure face of the airfoil upstream of the pressure face neck.Type: ApplicationFiled: December 12, 2008Publication date: June 18, 2009Applicant: SNECMAInventors: Patrick Joseph Marie GIRARD, Jean-Claude Marcel Auguste Hanny, Renaud Martet, Olivier Charles Hanri Massy, Philippe Jean-pierre Pabion, Stephanie Dominique Roger