Patents by Inventor Olivier Kueny
Olivier Kueny 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: 9518467Abstract: A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil, the blade configured, together with other identical blades, to form a ring around a ring axis, with the adjacent blade platforms joining in pairs so as to form an inter-airfoil surface linking the pressure surface of one airfoil to the suction surface of the neighboring airfoil. In this blade, the inter-airfoil surface includes, in an upstream half of the airfoil, a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the suction surface.Type: GrantFiled: January 7, 2015Date of Patent: December 13, 2016Assignee: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
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Publication number: 20150147179Abstract: A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil, the blade configured, together with other identical blades, to form a ring around a ring axis, with the adjacent blade platforms joining in pairs so as to form an inter-airfoil surface linking the pressure surface of one airfoil to the suction surface of the neighboring airfoil. In this blade, the inter-airfoil surface includes, in an upstream half of the airfoil, a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the suction surface.Type: ApplicationFiled: January 7, 2015Publication date: May 28, 2015Applicant: SNECMAInventors: Jean-Michel GUIMBARD, Olivier KUENY, Ludovic PINTAT
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Patent number: 9004865Abstract: A blade for a turbomachine impeller including an airfoil and at least one platform at one end of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring, the platform surface having a suction surface profile and a pressure surface profile respectively along the suction surface and the pressure surface. In the blade, the pressure surface profile including a pressure surface recessed part is located axially in an upstream half of the airfoil. Due to this configuration, efficiency of the blade is improved.Type: GrantFiled: February 27, 2009Date of Patent: April 14, 2015Assignee: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
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Patent number: 8757983Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: GrantFiled: June 29, 2011Date of Patent: June 24, 2014Assignee: SNECMAInventors: Patrick Girard, Olivier Kueny, Pierre Marche, Ludovic Pintat
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Patent number: 8734113Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: GrantFiled: June 29, 2011Date of Patent: May 27, 2014Assignee: SnecmaInventors: Patrick Girard, Olivier Kueny, Renaud Martet, Renaud Royan
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Patent number: 8647069Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: GrantFiled: June 29, 2011Date of Patent: February 11, 2014Assignee: SnecmaInventors: Patrick Girard, Olivier Kueny, Ludovic Pintat, Pascal Routier
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Patent number: 8647066Abstract: A blade for a turbomachine impeller including an airfoil, and at least one platform at one of the ends of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring around a ring axis. In the blade, a suction surface profile at the surface of the platform and along the suction surface has a first recessed part located axially in an upstream half of the airfoil and a first boss-like part located axially downstream of the first recessed part. Due to this configuration, efficiency of the blade is improved.Type: GrantFiled: February 27, 2009Date of Patent: February 11, 2014Assignee: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
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Publication number: 20120070298Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: ApplicationFiled: June 29, 2011Publication date: March 22, 2012Applicant: SNECMAInventors: Patrick GIRARD, Olivier Kueny, Pierre Marche, Ludovic Pintat
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Publication number: 20120051932Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: ApplicationFiled: June 29, 2011Publication date: March 1, 2012Applicant: SNECMAInventors: Patrick GIRARD, Olivier Kueny, Ludovic Pintat, Pascal Routier
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Publication number: 20120020806Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane PO situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: ApplicationFiled: June 29, 2011Publication date: January 26, 2012Applicant: SNECMAInventors: Patrick GIRARD, Olivier Kueny, Renaud Martet, Renaud Royan
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Patent number: 8083476Abstract: A method of designing a multistage turbine for a turbomachine in which each turbine stage comprises a stator row and a rotor row each made up of an annular row of airfoils, wherein, for all of the stator or rotor rows, it consists in simultaneously modifying the shapes of the airfoils of said rows to straighten out the wakes from the trailing edges of said airfoils, then in angularly positioning the rows in such a manner that the wakes from the airfoils of the stator (or rotor) airfoils impact against the leading edges of the stator (or rotor, respectively) airfoils of the rows situated downstream, in order to achieve multistage aerodynamic coupling simultaneously over the turbine as a whole.Type: GrantFiled: December 5, 2008Date of Patent: December 27, 2011Assignee: SNECMAInventors: Jean-Michel Bernard Guimbard, Olivier Kueny, Eric Schwartz
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Publication number: 20110189023Abstract: A blade for a turbomachine impeller including an airfoil, and at least one platform at one of the ends of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring around a ring axis. In the blade, a suction surface profile at the surface of the platform and along the suction surface has a first recessed part located axially in an upstream half of the airfoil and a first boss-like part located axially downstream of the first recessed part. Due to this configuration, efficiency of the blade is improved.Type: ApplicationFiled: February 27, 2009Publication date: August 4, 2011Applicant: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
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Publication number: 20110110788Abstract: A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil, the blade configured, together with other identical blades, to form a ring around a ring axis, with the adjacent blade platforms joining in pairs so as to form an inter-airfoil surface linking the pressure surface of one airfoil to the suction surface of the neighboring airfoil. In this blade, the inter-airfoil surface includes, in an upstream half of the airfoil, a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the suction surface.Type: ApplicationFiled: February 27, 2009Publication date: May 12, 2011Applicant: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
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Publication number: 20110014056Abstract: A blade for a turbomachine impeller including an airfoil and at least one platform at one end of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring, the platform surface having a suction surface profile and a pressure surface profile respectively along the suction surface and the pressure surface. In the blade, the pressure surface profile including a pressure surface recessed part is located axially in an upstream half of the airfoil. Due to this configuration, efficiency of the blade is improved.Type: ApplicationFiled: February 27, 2009Publication date: January 20, 2011Applicant: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
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Publication number: 20090155062Abstract: A method of designing a multistage turbine for a turbomachine in which each turbine stage comprises a stator row and a rotor row each made up of an annular row of airfoils, wherein, for all of the stator or rotor rows, it consists in simultaneously modifying the shapes of the airfoils of said rows to straighten out the wakes from the trailing edges of said airfoils, then in angularly positioning the rows in such a manner that the wakes from the airfoils of the stator (or rotor) airfoils impact against the leading edges of the stator (or rotor, respectively) airfoils of the rows situated downstream, in order to achieve multistage aerodynamic coupling simultaneously over the turbine as a whole.Type: ApplicationFiled: December 5, 2008Publication date: June 18, 2009Applicant: SNECMAInventors: Jean-Michel Bernard GUIMBARD, Olivier Kueny, Eric Schwartz