Patents by Inventor Damien Cellier
Damien 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: 10309419Abstract: A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.Type: GrantFiled: October 11, 2012Date of Patent: June 4, 2019Assignee: SAFRAN AIRCARFT ENGINESInventors: Damien Cellier, Alicia Lise Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Vincent Paul Gabriel Perrot, Jean-Francois Antoine Christian Rios, Laurent Christophe Francis Villaines
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Patent number: 10138897Abstract: The invention relates to a compressor blade, defined at each one of the points of its surface by a sweep angle and a dihedral angle, comprising: a root, a tip, the distance between the root and the tip, measured along an axis referred to as the radial axis, perpendicular to an axis of rotation of the compressor, being referred to as radial height (h), a zone, between the root and the tip, of which a first portion has a strictly positive leading edge dihedral angle, and a second portion has a strictly negative leading edge dihedral angle, the zone of maximum dihedral angle being, along the radial axis, between r=0.25 h and r=0.7 h.Type: GrantFiled: March 18, 2014Date of Patent: November 27, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventor: Damien Cellier
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Patent number: 9556740Abstract: A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.Type: GrantFiled: November 22, 2012Date of Patent: January 31, 2017Assignee: SNECMAInventors: Vincent Paul Gabriel Perrot, Damien Cellier, Alicia Lise Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Jean-Francois Antoine Christian Rios, Laurent Christophe Francis Villaines
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Patent number: 9464526Abstract: An assembly including an airfoil for a bladed wheel together with a platform, the airfoils in association with such platforms forming a bladed wheel. The platform surface presents a circumferential depression between a leading edge of an airfoil at 60% of the airfoil going downstream. A skeleton curve designates a curve plotting variations in a skeleton angle of the airfoil as a function of position along the axis of the wheel; and a linearized skeleton curve designates a curve that provides a straight line connection between points representing the skeleton angle respectively at 10% and at 90% of an axial extent of the airfoil from its leading edge, and, in a vicinity of the platform, a lowered portion of the skeleton curve lying under the linearized skeleton curve extends axially over at least half of an axial extent of the depression.Type: GrantFiled: February 6, 2012Date of Patent: October 11, 2016Assignee: SNECMAInventors: Damien Cellier, Vincent Paul Gabriel Perrot, Jean-Francois Rios
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Patent number: 9458720Abstract: An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of the airfoil, a deepest section of the depression being situated in an upstream half of the airfoil. A skeleton curve designates a curve of variations of a skeleton angle of the airfoil as a function of position along the axis of the wheel, and a linearized skeleton curve designates a curve of variations of an angle as a function of position along the axis of the wheel, the curve being a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge. In a vicinity of the platform, the skeleton curve presents a raised portion that lies above the linearized skeleton curve.Type: GrantFiled: February 6, 2012Date of Patent: October 4, 2016Assignee: SNECMAInventors: Damien Cellier, Vincent Paul Gabriel Perrot, Jean-Francois Rios
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Publication number: 20160061218Abstract: The invention relates to a compressor blade, defined at each one of the points of its surface by a sweep angle and a dihedral angle, comprising: a root, a tip, the distance between the root and the tip, measured along an axis referred to as the radial axis, perpendicular to an axis of rotation of the compressor, being referred to as radial height (h), a zone, between the root and the tip, of which a first portion has a strictly positive leading edge dihedral angle, and a second portion has a strictly negative leading edge dihedral angle, the zone of maximum dihedral angle being, along the radial axis, between r=0.25 h and r=0.7 h.Type: ApplicationFiled: March 18, 2014Publication date: March 3, 2016Inventor: Damien Cellier
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Publication number: 20140341749Abstract: A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.Type: ApplicationFiled: November 22, 2012Publication date: November 20, 2014Applicant: SNECMAInventors: Vincent Paul Gabriel Perrot, Damien Cellier, Alicia Lise, Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Jean-Francois Antoine Christian Rios, Laurent Christophe Francis Villaines
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Publication number: 20140248144Abstract: A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.Type: ApplicationFiled: October 11, 2012Publication date: September 4, 2014Applicant: SNECMAInventors: Damien Cellier, Alicia Lise, Julia Dufresne, Philippe Pierre Marcel, Marie Pelletrau, Vincent Paul, Gabriel Perrot, Jean-Francois Antoine, Christian Rios, Laurent Christophe, Francis Villaines
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Publication number: 20130315739Abstract: An assembly including an airfoil for a bladed wheel together with a platform, the airfoils in association with such platforms forming a bladed wheel. The platform surface presents a circumferential depression between a leading edge of an airfoil at 60% of the airfoil going downstream. A skeleton curve designates a curve plotting variations in a skeleton angle of the airfoil as a function of position along the axis of the wheel; and a linearized skeleton curve designates a curve that provides a straight line connection between points representing the skeleton angle respectively at 10% and at 90% of an axial extent of the airfoil from its leading edge, and, in a vicinity of the platform, a lowered portion of the skeleton curve lying under the linearized skeleton curve extends axially over at least half of an axial extent of the depression.Type: ApplicationFiled: February 6, 2012Publication date: November 28, 2013Applicant: SnecmaInventors: Damien Cellier, Vincent Paul Gabriel Perrot, Jean-Francois Rios
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Publication number: 20130315738Abstract: An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of the airfoil, a deepest section of the depression being situated in an upstream half of the airfoil. A skeleton curve designates a curve of variations of a skeleton angle of the airfoil as a function of position along the axis of the wheel, and a linearized skeleton curve designates a curve of variations of an angle as a function of position along the axis of the wheel, the curve being a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge. In a vicinity of the platform, the skeleton curve presents a raised portion that lies above the linearized skeleton curve.Type: ApplicationFiled: February 6, 2012Publication date: November 28, 2013Applicant: SNECMAInventors: Damien Cellier, Vincent Paul, Gabriel Perrot, Jean-Francois Rios