Patents by Inventor Eric Englebert
Eric Englebert 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: 10907504Abstract: A structural casing for an axial turbine engine includes an outer ring, an inner hub, and a plurality of struts extending radially from the hub to the ring, wherein the ring is made of a plurality of angular segments welded together. The segments extend circumferentially of different angles, some segments being larger angularly than others. The structural casing is adapted to be an intermediate casing between two compressors of a turbine engine.Type: GrantFiled: January 31, 2019Date of Patent: February 2, 2021Assignee: SAFRAN AERO BOOSTERS SAInventors: Ludovic Bovyn, Eric Englebert, Maxime Peeters
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Publication number: 20190242271Abstract: A structural casing for an axial turbine engine includes an outer ring, an inner hub, and a plurality of struts extending radially from the hub to the ring, wherein the ring is made of a plurality of angular segments welded together. The segments extend circumferentially of different angles, some segments being larger angularly than others. The structural casing is adapted to be an intermediate casing between two compressors of a turbine engine.Type: ApplicationFiled: January 31, 2019Publication date: August 8, 2019Applicant: SAFRAN AERO BOOSTERS SAInventors: Ludovic Bovyn, Eric Englebert, Maxime Peeters
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Publication number: 20180345457Abstract: A method for manufacturing a component of an axial turbine engine includes the following steps: (a) providing or producing a component with a temporary surface; (b) placing the component in a chamber containing particles; and (c) vibratory peening of the temporary surface using the particles. The chamber includes an abrasive paste mixed with the particles so as to polish the surface of the component during the peening step (c). Thus, at the end of the peening step (c), the surface becomes a polished surface with a surface compression stress or prestress. The present application is notably applicable to a one-piece bladed drum of an aircraft turbojet engine low-pressure compressor.Type: ApplicationFiled: May 30, 2018Publication date: December 6, 2018Applicant: SAFRAN AERO BOOSTERS SAInventor: Eric Englebert
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Patent number: 10105770Abstract: A method for selecting a milling cutter, which method makes it possible to select a milling cutter on the basis of a part to be machined such that the cutting force is constant while the part is being machined.Type: GrantFiled: January 20, 2017Date of Patent: October 23, 2018Assignee: SAFRAN AERO BOOSTERS S.A.Inventor: Eric Englebert
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Publication number: 20180281066Abstract: The present invention relates to a three-dimensional printer in which a localized powder flow is deposited on a construction surface. The three-dimensional printer comprises an electrostatic charge detector for measuring a characteristic of an electrostatic charge of the powder flow, for example the electrostatic charge thereof or the electrostatic charge thereof per unit of time. Said detector makes it possible to prevent explosions caused by the accumulation of electrostatic charge.Type: ApplicationFiled: March 28, 2018Publication date: October 4, 2018Applicant: Safran Aero Boosters S.A.Inventors: Laurent Schuster, Eric Englebert
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Patent number: 9957980Abstract: The present application relates to a stator of an axial turbomachine compressor. The stator includes a circular wall, such as an internal shroud, with a guiding surface in order to guide the primary flow of the turbomachine. The stator further includes a circular row of stator vanes, each of them including an airfoil which extends radially in the primary flow of the turbomachine, and a securing portion. The securing portion of the vane includes a lattice which has rods and which is secured and/or sealed in the shroud in order to fix the vanes to the shroud via the lattices. The stator includes a joint of abradable material which is arranged inside the internal shroud, and in which the lattice is secured in order to ensure retention, a fixing between the vane and the internal shroud. The vane is produced by means of additive production.Type: GrantFiled: July 24, 2015Date of Patent: May 1, 2018Assignee: SAFRAN AERO BOOSTERS SAInventor: Eric Englebert
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Publication number: 20170209945Abstract: A method for selecting a milling cutter, which method makes it possible to select a milling cutter on the basis of a part to be machined such that the cutting force is constant while the part is being machined.Type: ApplicationFiled: January 20, 2017Publication date: July 27, 2017Applicant: SAFRAN AERO BOOSTERS S.A.Inventor: Eric Englebert
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Publication number: 20170114795Abstract: A vane of a low pressure compressor of an axial turbine engine. The vane can be connected to the rotor or to the stator. The vane includes an airfoil forming a body in composite material with an organic matrix, and a reinforcing frame. This frame displays a base of a vane intended to be welded to the compressor drum, an upstream portion extending from the base and forming the leading edge of the vane, and a stiffener. The stiffener is situated at a central position of the base and remains enveloped in the airfoil of the vane. In the core, it forms a strip with orifices. The frame also has a cut-out separating the upstream portion from the stiffener, the upstream portion extending from the base along the height of the stiffener. This architecture reduces the mass of the frame, while preserving the general stiffness.Type: ApplicationFiled: July 14, 2016Publication date: April 27, 2017Inventor: Eric Englebert
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Patent number: 9598968Abstract: The invention relates to the design of rotor blades of an axial turbomachine compressor, especially the method of attaching the blades to the rotor. The blades comprise an aerofoil portion and a platform for attaching them to the rotor. The platform comprises, along the main axis of the blade, a first layer forming a surface bounding the fluid stream and skirting the aerodynamic surfaces and a second layer, underneath the first layer with respect to the aerodynamic surfaces, designed to be able to mate with the inner face of a wall of the rotor around an aperture in the rotor for the purpose of attaching it.Type: GrantFiled: September 4, 2013Date of Patent: March 21, 2017Assignee: Safran Aero Boosters SAInventor: Eric Englebert
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Publication number: 20160025108Abstract: The present application relates to a stator of an axial turbomachine compressor. The stator includes a circular wall, such as an internal shroud, with a guiding surface in order to guide the primary flow of the turbomachine. The stator further includes a circular row of stator vanes, each of them including an airfoil which extends radially in the primary flow of the turbomachine, and a securing portion. The securing portion of the vane includes a lattice which has rods and which is secured and/or sealed in the shroud in order to fix the vanes to the shroud via the lattices. The stator includes a joint of abradable material which is arranged inside the internal shroud, and in which the lattice is secured in order to ensure retention, a fixing between the vane and the internal shroud. The vane is produced by means of additive production.Type: ApplicationFiled: July 24, 2015Publication date: January 28, 2016Applicant: Techspace Aero S.A.Inventor: Eric Englebert
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Publication number: 20140079552Abstract: The invention relates to the design of rotor blades of an axial turbomachine compressor, especially the method of attaching the blades to the rotor. The blades comprise an aerofoil portion and a platform for attaching them to the rotor. The platform comprises, along the main axis of the blade, a first layer forming a surface bounding the fluid stream and skirting the aerodynamic surfaces and a second layer, underneath the first layer with respect to the aerodynamic surfaces, designed to be able to mate with the inner face of a wall of the rotor around an aperture in the rotor for the purpose of attaching it.Type: ApplicationFiled: September 4, 2013Publication date: March 20, 2014Applicant: Techspace Aero S.A.Inventor: Eric Englebert
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Publication number: 20130236254Abstract: The invention relates to a cutting tool, more particularly to a monobloc carbide cutter comprising a rod shrunk within the body of the cutter and extending to the so-called front end of the cutter having cutting edges. The shrunken rod enables bending vibrations to be damped through friction. Each cutting edge is formed directly and continuously from the material of the rod and the material of the body. As those parts of the cutting edges formed in the material of the rod rotate at lower speeds than those parts formed in the material of the body, the material of the rod can have cutting speed performance lower than that of the material of the body.Type: ApplicationFiled: October 27, 2011Publication date: September 12, 2013Applicant: TECHSPACE AERO S.A.Inventor: Eric Englebert