Patents by Inventor Jacques Marcel Arthur Bunel
Jacques Marcel Arthur Bunel 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: 11971174Abstract: A turbomachine has the upstream portion of the annular combustion chamber is fixed to the outer housing via individual pins with a swivel connection. The swivel connection is established between the pin and a part of the outer housing. The pin is slidable radially, or with a radial component, by a slide established between the pin and a tubular part of the outer annular shroud and/or the annular wall of the chamber bottom.Type: GrantFiled: May 14, 2020Date of Patent: April 30, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Dan-Ranjiv Joory, Jacques Marcel Arthur Bunel, Benjamin Frantz Karl Villenave
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Patent number: 11952901Abstract: A turbomachine sealing ring has an axis of revolution and includes an annular support, an annular coating made of abradable material which is carried by the support, and an annular thermal protection plate which is carried by the support. The ring is divided into sectors and has a plurality of ring sectors disposed circumferentially next to one another about the axis. Each ring sector has a support sector, a coating sector, and a plate sector. Each plate sector ling includes a flat tab that is pressed against a face of the corresponding support sector and is fixed to this face by brazing. The tab is inserted into a through-slot in the support sector in order to improve its integrity in operation.Type: GrantFiled: September 11, 2020Date of Patent: April 9, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Etienne Gérard Joseph Canelle, Jacques Marcel Arthur Bunel, Bruno Giardini
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Patent number: 11808456Abstract: A combustion chamber includes a bottom wall having at least one opening, at least one sleeve mounted upstream of the bottom wall and fixed to the bottom wall, a closing ring defining an annular groove with the sleeve and fixed to the sleeve, and at least one air and fuel injection system having an axis, mounted in the opening of the bottom wall. The injection system has an annular flange extending radially with respect to the axis and is mounted in the groove with radial clearance. A baffle is situated downstream of the bottom wall and is fixed to the sleeve and/or to the bottom wall.Type: GrantFiled: February 19, 2020Date of Patent: November 7, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Benjamin Frantz Karl Villenave
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Patent number: 11802512Abstract: The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall (58) and a wall made of a refractory material (16). A device (76) guides a spark plug (48) in said two orifices, the guiding device comprising a metal flange (80) and a floating ring (82), the flange being shrunk onto or welded to the metal wall (58).Type: GrantFiled: April 13, 2021Date of Patent: October 31, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan-Ranjiv Joory, Benjamin Frantz Karl Villenave
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Publication number: 20230175412Abstract: A turbomachine sealing ring has an axis of revolution and includes an annular support , an annular coating made of abradable material which is carried by the support, and an annular thermal protection plate which is carried by the support. The ring is divided into sectors and has a plurality of ring sectors disposed circumferentially next to one another about the axis. Each ring sector having has a support sector, a coating sector, and a plate sector. Each plate sector having includes a flat tab that is pressed against a face of the corresponding support sector and is fixed to this face by brazing. The tab is inserted into a through-slot in the support sector in order to improve its integrity in operation.Type: ApplicationFiled: September 11, 2020Publication date: June 8, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Etienne Gérard Joseph CANELLE, Jacques Marcel Arthur BUNEL, Bruno GIARDINI
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Publication number: 20230151770Abstract: The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall (58) and a wall made of a refractory material (16). A device (76) guides a spark plug (48) in said two orifices, the guiding device comprising a metal flange (80) and a floating ring (82), the flange being shrunk onto or welded to the metal wall (58).Type: ApplicationFiled: April 13, 2021Publication date: May 18, 2023Inventors: Jacques Marcel Arthur BUNEL, William Louis Rodolphe DOUSSE, Dan-Ranjiv JOORY, Benjamin Frantz Karl VILLENAVE
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Patent number: 11614234Abstract: A combustion chamber for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine. The combustion chamber includes a radially outer annular shroud, a radially inner annular shroud coaxial with the radially outer shroud, and an end wall connecting the radially outer shroud and the radially inner shroud. The combustion chamber further includes a first annular sealing member coaxial with said radially inner and outer shrouds. The first annular sealing member is radially interposed between the end wall and the radially outer shroud.Type: GrantFiled: January 4, 2018Date of Patent: March 28, 2023Assignee: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, Dan-Ranjiv Joory, Patrice André Commaret, Romain Nicolas Lunel
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Patent number: 11534962Abstract: A method for obtaining, by additive manufacture, a component including at least one recess, this method including: a step of forming, by additive manufacture, a one-piece blank component, in which the at least one recess contains a support including a core in the form of a block of material and cellular elements that connect the core to the recess; and a step of detaching the support from the rest of the blank component in order to expose the recess.Type: GrantFiled: March 19, 2019Date of Patent: December 27, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Ovaere, Jacques Marcel Arthur Bunel, Thomas Gricourt, Paul André Somazzi, Sylvain Zambelli
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Patent number: 11480340Abstract: The present disclosure provides devices for guiding an element in a combustion chamber wall opening. Between the welds or brazes joining a bushing with a cup and the trajectory of the ring edge, an intermediate space is reserved in an internal annular groove for said welds or brazes to protrude into, so that said welds or brazes lie outside the trajectory of the ring edge.Type: GrantFiled: June 28, 2019Date of Patent: October 25, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jacques Marcel Arthur Bunel, Alexandre Eric Lefebvre
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Patent number: 11408303Abstract: A bearing support for an aircraft engine, manufactured, in one piece, by powder-bed additive manufacturing from a manufacturing platform, including a cylindrical element including an annular stiffener with a cross-section that changes along its circumference, this stiffener being formed with alternating portions having a ?-shaped cross-section, needing to be supported during the manufacture, and portions having a Y-shaped cross-section that are not supported during the manufacture.Type: GrantFiled: March 19, 2019Date of Patent: August 9, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Ovaere, Jacques Marcel Arthur Bunel, Thomas Gricourt, Paul André Somazzi, Sylvain Zambelli
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Publication number: 20220196243Abstract: A turbomachine has the upstream portion of the annular combustion chamber is fixed to the outer housing via individual pins with a swivel connection. The swivel connection is established between the pin and a part of the outer housing. The pin is slidable radially, or with a radial component, by a slide established between the pin and a tubular part of the outer annular shroud and/or the annular wall of the chamber bottom.Type: ApplicationFiled: May 14, 2020Publication date: June 23, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Dan-Ranjiv JOORY, Jacques Marcel Arthur BUNEL, Benjamin Frantz Karl VILLENAVE
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Patent number: 11333358Abstract: A combustion chamber for a gas turbomachine. The combustion chamber comprising inner and outer walls, a chamber bottom, and a heat shield arranged downstream of the chamber bottom, to protect it thermally. The inner and outer walls and the heat shield form a one-piece unit.Type: GrantFiled: July 24, 2019Date of Patent: May 17, 2022Assignee: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
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Patent number: 11280494Abstract: An assembly for a combustion chamber of a turbomachine. The assembly comprises an annular shell extending along a longitudinal axis, the shell having an inner wall intended to be turned towards a furnace of the combustion chamber and an outer wall opposite the inner wall and a projecting element extending radially from an area of the outer wall. The shell has at least one deflector projecting from the outer wall and located downstream of the projecting element with respect to a direction of gas flow along the outer wall, oriented along the longitudinal axis. The deflector extends circumferentially. Perforations are provided axially between the projecting element and the or each deflector.Type: GrantFiled: May 15, 2019Date of Patent: March 22, 2022Assignee: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, Pierrick Bernard Jean
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Patent number: 11248793Abstract: A gas turbo machine having a combustion chamber. The combustion chamber includes a chamber bottom having an upstream wall and a downstream wall extending between inner and outer annular walls. Each upstream and downstream walls each having openings for mounting fuel injection devices for injecting fuel through said openings. The downstream wall is sectorised.Type: GrantFiled: February 28, 2019Date of Patent: February 15, 2022Assignee: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, Dan-Ranjiv Joory
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Publication number: 20220018543Abstract: A combustion chamber includes a bottom wall having at least one opening, at least one sleeve mounted upstream of the bottom wall and fixed to the bottom wall, a closing ring defining an annular groove with the sleeve and fixed to the sleeve, and at least one air and fuel injection system having an axis, mounted in the opening of the bottom wall. The injection system has an annular flange extending radially with respect to the axis and is mounted in the groove with radial clearance. A baffle is situated downstream of the bottom wall and is fixed to the sleeve and/or to the bottom wall.Type: ApplicationFiled: February 19, 2020Publication date: January 20, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: JACQUES MARCEL ARTHUR BUNEL, WILLIAM LOUIS RODOLPHE DOUSSE, BENJAMIN FRANTZ KARL VILLENAVE
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Patent number: 11085640Abstract: A method for producing an annular combustion chamber of a turbojet using CMC. For this, a shaping tool with movable slides is used and said chamber is produced around the tool, thereby producing a fibrous preform of which the shape is consolidated by drape moulding on the tool and pyrolysis, which is then densified by CVI. Several slides have back drafts, at least one other of such slides having a draft or neither a draft nor a back draft. Then, the slides are removed in a predetermined order imposed by the back drafts and the relative positions of the slides.Type: GrantFiled: July 24, 2019Date of Patent: August 10, 2021Assignee: Sanfran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
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Patent number: 11047259Abstract: The thermal shrinkage of a casing (2) to regulate as best as possible the internal play between the rotor and the stator is carried out by a ring (4) fixed onto the skin (2) rather than by a circular ramp at a distance therefrom. The ring (4) comprises, between a collection box (8) and the skin (2), a foraminous plate (7), placed on an opening of the box (8) parallel to the skin (2) and at a short distance, in order to impose invariable and known ventilation conditions.Type: GrantFiled: June 24, 2019Date of Patent: June 29, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jacques Marcel Arthur Bunel, Etienne Gérard Joseph Canelle, Emeric Christian Amaury D'Herbigny, Pierrick Bernard Jean
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Publication number: 20210140639Abstract: A gas turbo machine having a combustion chamber. The combustion chamber includes a chamber bottom having an upstream wall and a downstream wall extending between inner and outer annular walls. Each upstream and downstream walls each having openings for mounting fuel injection devices for injecting fuel through said openings. The downstream wall is sectorised.Type: ApplicationFiled: February 28, 2019Publication date: May 13, 2021Applicant: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, Dan-Ranjiv Joory
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Publication number: 20210131666Abstract: The present disclosure provides devices for guiding an element in a combustion chamber wall opening. Between the welds or brazes joining a bushing with a cup and the trajectory of the ring edge, an intermediate space is reserved in an internal annular groove for said welds or brazes to protrude into, so that said welds or brazes lie outside the trajectory of the ring edge.Type: ApplicationFiled: June 28, 2019Publication date: May 6, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jacques Marcel Arthur Bunel, Alexandre Eric Lefebvre
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Patent number: 10920619Abstract: A part for a turbine engine, the part having a general annular shape about an axis of revolution, this part including a first annular shrink-fitted mounting flange and comprising an annular row of orifices for the passage of screws, this part being made by casting and including protruding pads required for the control and the manufacture of the part by casting, wherein the pads are located on the flange and in that each comprises a thread configured to engage with an extraction screw of the flange.Type: GrantFiled: June 19, 2019Date of Patent: February 16, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Etienne Gerard Joseph Canelle, Jacques Marcel Arthur Bunel, Faouzi Aliouat