Patents by Inventor Thomas Gerard Daniel Riviere
Thomas Gerard Daniel Riviere 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: 11441486Abstract: The invention relates to a semiconductor body revolving around a main axis (A) for a spark plug of a turbine engine, the semiconductor body comprising a baseplate and an upper portion extending from the baseplate along the main axis, the baseplate comprising a bottom surface substantially defined in a plane perpendicular to the main axis and a first conical surface intended to cooperate by form-fitting at least partially with a contact surface of an outer electrode of the spark plug. According to the invention, the upper portion comprises an interface located opposite the bottom surface along the main axis (A) and featuring a profile that is at least partially corrugated.Type: GrantFiled: February 21, 2020Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thomas Gérard Daniel Riviere, Guillaume Thierry Richen, David Gino Stifanic
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Publication number: 20200271058Abstract: The invention relates to a semiconductor body revolving around a main axis (A) for a spark plug of a turbine engine, the semiconductor body comprising a baseplate and an upper portion extending from the baseplate along the main axis, the baseplate comprising a bottom surface substantially defined in a plane perpendicular to the main axis and a first conical surface intended to cooperate by form-fitting at least partially with a contact surface of an outer electrode of the spark plug. According to the invention, the upper portion comprises an interface located opposite the bottom surface along the main axis (A) and featuring a profile that is at least partially corrugated.Type: ApplicationFiled: February 21, 2020Publication date: August 27, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Thomas Gérard Daniel Riviere, Guillaume Thierry Richen, David Gino Stifanic
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Patent number: 10640222Abstract: The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.Type: GrantFiled: October 10, 2017Date of Patent: May 5, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nora El Ghannam, Matthieu Etienne Attali, Romain Jean-Claude Ferrier, Caroline Marie Frantz, Thomas Gerard Daniel Riviere, Nicolas Xavier Trappier
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Patent number: 10287025Abstract: The invention relates to a system for suspending two modules of a propulsion unit, such as two fan modules, said system comprising a pylon (28) and a rudder bar (30). One part (30?) of the rudder bar is hinged to the pylon, while the opposing ends thereof are hinged to connecting rods (34, 36). The system also comprises a torque bar (40) which has an elongate shape and is mounted on the pylon such that it can pivot about an axis substantially parallel to an axis (B) of elongation of the torque bar, the opposing ends (42) of said bar being secured on each side of the above-mentioned part of the rudder bar.Type: GrantFiled: September 21, 2016Date of Patent: May 14, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thomas Gerard Daniel Riviere, Antoine Elie Hellegouarch
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Publication number: 20180281980Abstract: The invention relates to a system for suspending two modules of a propulsion unit, such as two fan modules, said system comprising a pylon (28) and a rudder bar (30). One part (30?) of the rudder bar is hinged to the pylon, while the opposing ends thereof are hinged to connecting rods (34, 36). The system also comprises a torque bar (40) which has an elongate shape and is mounted on the pylon such that it can pivot about an axis substantially parallel to an axis (13) of elongation of the torque bar, the opposing ends (42) of said bar being secured on each side of the above-mentioned part of the rudder bar.Type: ApplicationFiled: September 21, 2016Publication date: October 4, 2018Inventors: Thomas Gerard Daniel RIVIERE, Antoine Elie HELLGOUARCH
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Publication number: 20180134402Abstract: A cradle for supporting an aircraft turbine engine, said cradle comprising an attachment interface for attaching a gas generator of the turbine engine. The cradle is produced in at least two portions comprising: an upper half-cradle, which is designed to be attached to a wing of the aircraft, a lower half-cradle, which is movable between a position in which it is connected to the upper half-cradle and a position in which it is disconnected from the upper half-cradle, and which comprises at least a portion of the attachment interface for attaching the gas generator, a guide configured for slidably guiding the lower half-cradle between the connected and disconnected positions thereof, and at least one lock for locking the lower half-cradle in the connected position thereof.Type: ApplicationFiled: November 14, 2017Publication date: May 17, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Antoine Elie Hellegouarch, Frédéric Paul Eichstadt, Thomas Gérard Daniel Riviere
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Publication number: 20180105278Abstract: The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.Type: ApplicationFiled: October 10, 2017Publication date: April 19, 2018Inventors: Nora EL GHANNAM, Matthieu Etienne ATTALI, Romain Jean-Claude FERRIER, Caroline Marie FRANTZ, Thomas Gerard Daniel RIVIERE, Nicolas Xavier TRAPPIER
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Patent number: 9828877Abstract: A bypass turbojet engine including a cylindrical cold stream flow path supported by link rods which are attached to a cylindrical outer shell ring of an exhaust case at attachment points. The attachment points for the exhaust case are crevice mounts including lugs that extend radially from the outer shell ring, a bore of the crevice mounts being directed in a direction of generatrices of the outer shell ring.Type: GrantFiled: May 7, 2012Date of Patent: November 28, 2017Assignee: SNECMAInventors: Thomas Gérard Daniel Riviere, François Robert Bellabal, Olivier Renon, Guilhem Seize
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Patent number: 8919723Abstract: Device for adjusting the length of a connecting rod and consisting of a bushing positioned inside an eye of the said connecting rod, the said bushing comprising at least one element in which there is made a bore to act as a support for a pivot pin intended to pass through the eye, characterized in that the said element is a cylinder made of a metallic material covered by a cylinder made of an elastomeric material so as to form with the metallic cylinder a cylinder homothetic with the previous one, the generatrices of the said cylinders being oriented in a direction that is inclined with respect to the longest length of the said connecting rod.Type: GrantFiled: July 30, 2012Date of Patent: December 30, 2014Assignee: SNECMAInventors: Francois Robert Bellabal, Thomas Gerard Daniel Riviere
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Publication number: 20140112770Abstract: A bypass turbojet engine including a cylindrical cold stream flow path supported by link rods which are attached to a cylindrical outer shell ring of an exhaust case at attachment points. The attachment points for the exhaust case are crevice mounts including lugs that extend radially from the outer shell ring, a bore of the crevice mounts being directed in a direction of generatrices of the outer shell ring.Type: ApplicationFiled: May 7, 2012Publication date: April 24, 2014Applicant: SNECMAInventors: Thomas Gérard, Daniel Riviere, François Robert Bellabal, Olivier Renon, Guilhem Seize
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Publication number: 20130037688Abstract: Device for adjusting the length of a connecting rod and consisting of a bushing positioned inside an eye of the said connecting rod, the said bushing comprising at least one element in which there is made a bore to act as a support for a pivot pin intended to pass through the eye, characterized in that the said element is a cylinder made of a metallic material covered by a cylinder made of an elastomeric material so as to form with the metallic cylinder a cylinder homothetic with the previous one, the generatrices of the said cylinders being oriented in a direction that is inclined with respect to the longest length of the said connecting rod.Type: ApplicationFiled: July 30, 2012Publication date: February 14, 2013Applicant: SNECMAInventors: François Robert BELLABAL, Thomas Gérard Daniel RIVIERE