Patents by Inventor Renaud Martet
Renaud Martet 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: 9631495Abstract: A turbomachine assembly in which a foil is configured to cover mainly one of bulbs of a disc and to be held, radially with respect to the disc, by the bulb of the disc and a pocket for a blade that can collaborate therewith, when these two are effectively collaborating, and the bulb of the disc includes at least one longitudinal cavity configured to form, with the foil, when the foil is covering the bulb of the disc, a secondary passage through which a secondary cooling air flow can pass.Type: GrantFiled: October 10, 2012Date of Patent: April 25, 2017Assignee: SNECMAInventors: Emmanuel Da Costa, Alain Dominique Gendraud, Renaud Martet, Josselin Sicard, Bruno Andre Jean Varin
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Patent number: 9022744Abstract: A turbine engine blade having a plurality of blade sections stacked along a radial axis between a root and a tip. Each section extends along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between a pressure-side face and a suction-side face. Each section presents a camber line, a deviation defined for each section as the difference between an angle between the tangent to the camber line at the leading edge and the longitudinal axis, and an angle between the tangent to the camber line at the trailing edge and the longitudinal axis. The minimum deviation is at the root of the blade, and the maximum deviation is present at sections situated in the range 0.3H to 0.8H, where H is the height of the blade measured from its root to its tip.Type: GrantFiled: June 20, 2012Date of Patent: May 5, 2015Assignee: SNECMAInventors: Renaud Gabriel Constant Royan, Renaud Martet, Jean-Michel Guimbard
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Publication number: 20140294597Abstract: A turbomachine assembly in which a foil is configured to cover mainly one of bulbs of a disc and to be held, radially with respect to the disc, by the bulb of the disc and a pocket for a blade that can collaborate therewith, when these two are effectively collaborating, and the bulb of the disc includes at least one longitudinal cavity configured to form, with the foil, when the foil is covering the bulb of the disc, a secondary passage through which a secondary cooling air flow can pass.Type: ApplicationFiled: October 10, 2012Publication date: October 2, 2014Applicant: SNECMAInventors: Emmanuel Da Costa, Alain Dominique Gendraud, Renaud Martet, Josselin Sicard, Bruno Andre, Jean Varin
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Patent number: 8734096Abstract: 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: Jean-Michel Guimbard, Pierre Marche, Renaud Martet, Renaud Royan
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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: 8734115Abstract: 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 28, 2011Date of Patent: May 27, 2014Assignee: SNECMAInventors: Jean Bleuzen, Jean-Michel Guimbard, Pierre Marche, Renaud Martet
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Publication number: 20140105750Abstract: A turbine engine blade having a plurality of blade sections stacked along a radial axis between a root and a tip. Each section extends along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between a pressure-side face and a suction-side face. Each section presents a camber line, a deviation defined for each section as the difference between an angle between the tangent to the camber line at the leading edge and the longitudinal axis, and an angle between the tangent to the camber line at the trailing edge and the longitudinal axis. The minimum deviation is at the root of the blade, and the maximum deviation is present at sections situated in the range 0.3 H to 0.8 H, where H is the height of the blade measured from its root to its tip.Type: ApplicationFiled: June 20, 2012Publication date: April 17, 2014Applicant: SNECMAInventors: Renaud Gabriel Constant ROYAN, Renaud Martet, Jean-Michel Guimbard
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Patent number: 8672635Abstract: 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: March 18, 2014Assignee: SnecmaInventors: Jean Bleuzen, Renaud Martet, Pascal Routier, Renaud Royan
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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: 20120051931Abstract: 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: Jean BLEUZEN, Renaud Martet, Pascal Routier, Renaud Royan
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Publication number: 20120051895Abstract: 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: Jean-Michel GUIMBARD, Pierre Marche, Renaud Martet, Renaud Royan
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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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Publication number: 20120020799Abstract: 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 28, 2011Publication date: January 26, 2012Applicant: SNECMAInventors: Jean BLEUZEN, Jean-Michel Guimbard, Pierre Marche, Renaud Martet
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Patent number: 7972107Abstract: A device for cooling a turbine casing in a turbomachine including a turbine is disclosed. The turbine includes several stages, at least one of the stages includes a nozzle assembly formed of an annular row of fixed vanes and an impeller mounted to rotate in a cylindrical shroud formed of ring sectors fixed to the casing, a cooling circuit including ducts carrying cooling air into cavities formed in the vanes of the nozzle assembly, and an air-carrying arrangement which carries air to casing upstream hooks for suspending the ring sectors.Type: GrantFiled: March 29, 2007Date of Patent: July 5, 2011Assignee: SNECMAInventors: Alexandre Nicolas Dervaux, Philippe Hazevis, Renaud Martet, Philippe Jean-Pierre Pabion, Stephanie Roger, Eric Schwartz
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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
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Publication number: 20080184694Abstract: A gas turbine with contrarotating HP and LP turbines comprises an LP turbine having a plurality of moving wheels alternating with nozzles, the moving wheels of the LP turbine rotating in a direction opposite to the direction of rotation of the moving wheel of the HP turbine, and an inter-turbine casing having inner and outer casing walls defining a stream passage between the HP and LP turbines together with arms extending across the passage between the inner and outer casing walls. The gas turbine does not have a nozzle or device for forming the function of deflecting the stream between the outlet from the HP turbine and the first moving wheel of the LP turbine. The HP turbine is advantageously designed to deliver a stream that gyrates in the inter-turbine casing.Type: ApplicationFiled: February 5, 2008Publication date: August 7, 2008Applicant: SNECMAInventors: Jean-Michel Bernard Guimbard, Renaud Martet, Eric Schwartz
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Publication number: 20070231123Abstract: Device for cooling a turbine casing in a turbomachine, this turbine comprising several stages each including a nozzle assembly (18) formed of an annular row of fixed vanes (20) and an impeller mounted to rotate in a cylindrical shroud formed of ring sectors (34) fixed to the casing, and a cooling circuit comprising ducts carrying cooling air into cavities (46) formed in the vanes (20) of the nozzle assembly, and means for carrying air to casing upstream hooks (72) for suspending the ring sectors (34).Type: ApplicationFiled: March 29, 2007Publication date: October 4, 2007Applicant: SNECMAInventors: Alexandre Nicolas DERVAUX, Philippe HAZEVIS, Renaud MARTET, Philippe Jean-Pierre PABION, Stephanie ROGER, Eric SCHWARTZ