Patents by Inventor Damien Joseph CELLIER
Damien Joseph CELLIER 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: 11221020Abstract: A part or an assembly of parts of a splitter stage of a turbofan, including a plurality of obstacles including at least one a blade and at least one arm, and a platform from which the obstacles extend, wherein the arm is defined by a skeleton angle having a trailing value on the trailing edge of between 3° and 15°.Type: GrantFiled: September 2, 2016Date of Patent: January 11, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Ghislain Maxime Romuald Madiot, Jean Bertucchi, Damien Joseph Cellier, Irwin Pierre Robert Kernemp, Aurelien Mazzella
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Patent number: 10753371Abstract: A stage of variable-pitch vanes for a turbine engine includes a plurality of vanes. Each vane has a blade with a first radially internal frusto-conical surface. The cone angle of the first frusto-conical surface is radially flared inwards and is configured to interact with an internal frusto-conical surface of a first frusto-conical bushing. The vane further includes a second radially external frusto-conical surface with cone angle that is radially flared outwards and is configured to interact with an internal frusto-conical surface of a second substantially frusto-conical bushing.Type: GrantFiled: July 11, 2016Date of Patent: August 25, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pierre-Alain Francis Claude Sebrecht, Damien Joseph Cellier, Cédric Michel Claude Chretien
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Patent number: 10352330Abstract: A turbomachine part including at least first and second blades, and a platform from which the blades extend, wherein the platform has a non-axisymmetric surface limited by first and second end planes, and defined by at least three construction curves of class CI each representing the value of a radius of the surface on the basis of a position between the lower surface of the first blade and the upper surface of the second blade according to a plane substantially parallel to the end planes, including a first curve that increases in the vicinity of the second blade; a second curve that decreases in the vicinity of the second blade; a third curve having a minimum at the second blade.Type: GrantFiled: October 10, 2014Date of Patent: July 16, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventor: Damien Joseph Cellier
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Patent number: 10330117Abstract: The main object of the invention is an angular stator sector (10) for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterized in that the inner shroud (S) comprises at least one brush seal (1, 2, 3) forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).Type: GrantFiled: September 5, 2014Date of Patent: June 25, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Damien Joseph Cellier, Mickael Dias Gomes, Antoine Robert Alain Brunet, Daniel Georges Plona
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Patent number: 10301941Abstract: A turbine engine rotor blade including an airfoil defined by plane airfoil sections stacked in a radial direction, each airfoil section being positioned radially at a height H, where height H is expressed as a percentage of the total height of the airfoil, and being identified by its sweep angle ? and its dihedral angle ?, wherein the sweep angle ? varies as a function of height H in such a manner that the sweep angle ? reaches a maximum at a height H?M, the value H?M lying in the range 5% to 40%, and the sweep angle ? increases from 0% to H?M, and wherein the dihedral angle ? varies as a function of H, the dihedral angle ? being a decreasing function of height H for heights H lying in the range 0% to H?1, H?1 lying in the range 10% to 40%.Type: GrantFiled: August 4, 2014Date of Patent: May 28, 2019Assignee: SAFRAN AIRCARFT ENGINESInventors: Damien Joseph Cellier, Alicia Lise Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Vincent Paul Gabriel Perrot, Laurent Christophe Francis Villaines
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Patent number: 10216867Abstract: A method for modeling at least part of a non-axisymmetric surface (5) of one portion (2) of a part (1). The portion (2) is bounded by first and second extremal planes (PS, PR). The method includes processing data from a device (10), by: (a) modeling at least two basic non-axisymmetric surfaces (Sk, SI, SE) making up the surface, each of the basic surfaces (Sk, SI, SE) extending between both extremal planes (PS, PR) of the portion (S); (b) constructing at least one connection curve (CR) tangential to the first and second surfaces; (c) locally modifying the first and second basic surfaces (Sk, SI, SE) to keep to the connection curve (CR) near a discontinuity; and (d) restoring, at least part of the obtained surface (5).Type: GrantFiled: July 7, 2014Date of Patent: February 26, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Damien Joseph Cellier, Vincent Perrot, Matthieu Jean Luc Vollebregt, Nicolas Jean Fernand Pignier
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Publication number: 20180252230Abstract: A part or an assembly of parts of a splitter stage of a turbofan, including a plurality of obstacles including at least one a blade and at least one arm, and a platform from which the obstacles extend, wherein the arm is defined by a skeleton angle having a trailing value on the trailing edge of between 3° and 15°.Type: ApplicationFiled: September 2, 2016Publication date: September 6, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Ghislain Maxime Romuald MADIOT, Jean BERTUCCHI, Damien Joseph CELLIER, Irwin Pierre Robert KERNEMP, Aurelien MAZZELLA
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Patent number: 10002209Abstract: The present invention relates to a method for modelling a part (1), the method being characterized in that it comprises implementing, using data processing means (11) of a piece of equipment (10), steps of: (a) parameterizing a curve of class C1 representing the value of a physical quantity characterizing said part (1) as a function of a position along at least one portion of the part (1), the curve being defined by: a. two end points (PCU0, PCUK) defining the extent of said portion of the part (1); b. at least one intermediate point PCUi, i?[[1,K?1]]) located between the two end points (PCU0, PCUK); c. at least two Bezier curves connected to said intermediate point; the parameterization being carried out using one or more parameters defining said intermediate point; (b) determining optimized values for said parameters of said curve; and (c) returning the determined values to an interface (13) of said piece of equipment (10).Type: GrantFiled: April 16, 2014Date of Patent: June 19, 2018Assignee: SNECMAInventors: Damien Joseph Cellier, Vincent Paul Gabriel Perrot
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Publication number: 20160245299Abstract: A turbomachine part including at least first and second blades, and a platform from which the blades extend, wherein the platform has a non-axisymmetric surface limited by first and second end planes, and defined by at least three construction curves of class CI each representing the value of a radius of the surface on the basis of a position between the lower surface of the first blade and the upper surface of the second blade according to a plane substantially parallel to the end planes, including a first curve that increases in the vicinity of the second blade; a second curve that decreases in the vicinity of the second blade; a third curve having a minimum at the second blade.Type: ApplicationFiled: October 10, 2014Publication date: August 25, 2016Applicant: SNECMAInventor: Damien Joseph CELLIER
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Publication number: 20160195104Abstract: A turbine engine rotor blade including an airfoil defined by plane airfoil sections stacked in a radial direction, each airfoil section being positioned radially at a height H, where height H is expressed as a percentage of the total height of the airfoil, and being identified by its sweep angle ? and its dihedral angle ?, wherein the sweep angle ? varies as a function of height H in such a manner that the sweep angle ? reaches a maximum at a height H?M, the value H?M lying in the range 5% to 40%, and the sweep angle ? increases from 0% to H?M, and wherein the dihedral angle ? varies as a function of H, the dihedral angle ? being a decreasing function of height H for heights H lying in the range 0% to H?1, H?1 lying in the range 10% to 40%.Type: ApplicationFiled: August 4, 2014Publication date: July 7, 2016Applicant: SNECMAInventors: Damien Joseph CELLIER, Alicia Lise Julia DUFRESNE, Philippe Pierre Marcel Marie PELLETRAU, Vincent Paul Gabriel PERROT, Laurent Christophe Francis VILLAINES
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Publication number: 20160154901Abstract: The present invention relates to a method for modeling at least part of a non-axisymmetric surface (S) of one portion (2) of a part (1), the portion (2) being bounded by a first and a second extremal planes (PS, PR).Type: ApplicationFiled: July 7, 2014Publication date: June 2, 2016Inventors: Damien Joseph Cellier, Vincent Perrot, Matthieu Jean Luc Vollebregt, Nicolas Jean Fernand Pignier
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Publication number: 20160063139Abstract: The present invention relates to a method for modelling a part (1), the method being characterised in that it comprises implementing, using data processing means (11) of a piece of equipment (10), steps of: (a) parameterising a curve of class C1 representing the value of a physical quantity characterising said part (1) as a function of a position along at least one portion of the part (1), the curve being defined by: a. two end points (PCU0, PCUK) defining the extent of said portion of the part (1); b. at least one intermediate point PCUi, i?[1,K?1]) located between the two end points (PCU0, PCUK); c. at least two Bezier curves connected to said intermediate point; the parameterization being carried out using one or more parameters defining said intermediate point; (b) determining optimised values for said parameters of said curve; and (c) returning the determined values to an interface (13) of said piece of equipment (10).Type: ApplicationFiled: April 16, 2014Publication date: March 3, 2016Inventors: Damien Joseph Cellier, Vincent Paul Gabriel Perrot
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Publication number: 20150071770Abstract: The main object of the invention is an angular stator sector (10) for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterised in that the inner shroud (S) comprises at least one brush seal (1, 2, 3) forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).Type: ApplicationFiled: September 5, 2014Publication date: March 12, 2015Applicant: SnecmaInventors: Damien Joseph CELLIER, Mickael DIAS GOMES, Antoine Robert Alain BRUNET, Daniel Georges PLONA