Patents by Inventor Francois Pierre Michel COMTE
Francois Pierre Michel COMTE 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: 11542833Abstract: A device (26) for cooling an annular outer turbine casing (17) includes at least one circumferentially extending tube (27) having an air inlet intended for conveying cooling air, the tube having a radially inner wall provided with cooling air discharge openings and a radially outer wall arranged radially opposite each other, an air inlet manifold (28), the inlet of the tube opening into the manifold, the tube (27) including at least one intermediate wall extending over a circumferential portion of the tube from the air inlet, the intermediate wall being located radially between the radially inner wall and the radially outer wall, the radially inner wall and the intermediate wall forming a first air conveying duct, the radially outer wall and the intermediate wall forming a second air conveying duct extending circumferentially beyond the first air conveying duct, relative to the air inlet.Type: GrantFiled: June 4, 2018Date of Patent: January 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Arnaud Lasantha Genilier, François Pierre Michel Comte, Fabien Stéphane Garnier, Vincent François Georges Millier
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Patent number: 11408305Abstract: The invention relates to a lubrication device (1) for a turbo machine, comprising: a rotor (2) rotating around an axis, at least one lubrication chamber (6) formed in the rotor (2), a stator (22) in which the rotor (2) is rotatably mounted, a bearing (11) for rotationally guiding the rotor (2), mounted between the rotor (2) and the stator, lubricating fluid supply means which supply at least the chamber (6) and the bearing (11), the lubricating fluid supply means comprising a nozzle (23) mounted on the stator provided with an ejection nozzle (34) at a free end of the nozzle (23), said nozzle (34) being configured to project the lubricating fluid into the chamber (6), characterized in that the nozzle (23) has a movable part (27) including said ejection nozzle (34), said movable part (27) being movable between a retracted position in which the ejection nozzle (34) is remote from the chamber (6) or at least partially located outside the chamber (6), and an extended position in which the nozzle (34) is closerType: GrantFiled: April 26, 2019Date of Patent: August 9, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Fabien Stéphane Garnier, François Pierre Michel Comte, Arnaud Lasantha Genilier, Vincent François Georges Millier
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Patent number: 10984153Abstract: A method of determining a maximum acceptable alternating stress at a point of a part subjected to cyclic loading: simulating that the part is subjected to constant loading equal to a threshold value during a level period, and assuming that the part has elasto-viscoplastic behavior; from the results of the simulation, determining a final static stress at the point at the end or after the end of the level period; and for the point under consideration, using a Goodman diagram to determine the maximum acceptable alternating stress, which is determined for a static stress equal to the final static stress; the duration of the level period being equal to the duration of the loading of the testpieces that were used to draw up the Goodman diagram.Type: GrantFiled: July 19, 2016Date of Patent: April 20, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Geoffrey Juan Desmeure, Francois Pierre Michel Comte, Anais Suzanne Amelie Gaubert, Arnaud Cyril Longuet, Marine Laetitia Camille Chevalier, Michael Piers Hansom, Lucie Marie Ida Lanciaux
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Patent number: 10920593Abstract: A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised in that it comprises:—a fixing ferrule (44) fixed between the upstream (20a) and downstream (20b) discs by the bolting thereof; a part forming a movable ring (42), said part supporting radial sealing members (32) and being fixed between the upstream disc (20a) and the ferrule (44);—and a seal (46) interposed between said part forming the movable ring (42) and the ferrule (44).Type: GrantFiled: October 6, 2017Date of Patent: February 16, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vincent Francois Georges Millier, Francois Pierre Michel Comte, Fabien Stephane Garnier, Alain Dominique Gendraud, Arnaud Lasantha Genilier
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Publication number: 20200182089Abstract: The invention relates to a device (26) for cooling an annular outer turbine casing (17), the device (26) comprising at least one circumferentially extending tube (27) having an air inlet intended for conveying cooling air, said tube (27) having a radially inner wall provided with cooling air discharge openings and a radially outer wall arranged axially opposite each other, an air inlet manifold (28), the inlet of the tube (27) opening into said manifold (28), characterized in that the tube (27) comprises at least one intermediate wall extending over a circumferential portion of the tube (27) from the air inlet, the intermediate wall being located radially between the radially inner wall and the radially outer wall, the radially inner wall and the intermediate wall forming a first air conveying duct, the radially outer wall and the intermediate wall forming a second air conveying duct extending circumferentially beyond the first air conveying duct, relative to the air inlet.Type: ApplicationFiled: June 4, 2018Publication date: June 11, 2020Inventors: Arnaud Lasantha GENILIER, François Pierre Michel COMTE, Fabien Stéphane GARNIER, Vincent François Georges MILLIER
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Publication number: 20200040735Abstract: A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised in that it comprises:—a fixing ferrule (44) fixed between the upstream (20a) and downstream (20b) discs by the bolting thereof; a part forming a movable ring (42), said part supporting radial sealing members (32) and being fixed between the upstream disc (20a) and the ferrule (44);—and a seal (46) interposed between said part forming the movable ring (42) and the ferrule (44).Type: ApplicationFiled: October 6, 2017Publication date: February 6, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vincent Francois Georges MILLIER, Francois Pierre Michel COMTE, Fabien Stephane GARNIER, Alain Dominique GENDRAUD, Arnaud Lasantha GENILIER
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Publication number: 20190331001Abstract: The invention relates to a lubrication device (1) for a turbo machine, comprising: a rotor (2) rotating around an axis, at least one lubrication chamber (6) formed in the rotor (2), a stator (22) in which the rotor (2) is rotatably mounted, a bearing (11) for rotationally guiding the rotor (2), mounted between the rotor (2) and the stator, lubricating fluid supply means which supply at least the chamber (6) and the bearing (11), the lubricating fluid supply means comprising a nozzle (23) mounted on the stator provided with an ejection nozzle (34) at a free end of the nozzle (23), said nozzle (34) being configured to project the lubricating fluid into the chamber (6), characterized in that the nozzle (23) has a movable part (27) including said ejection nozzle (34), said movable part (27) being movable between a retracted position in which the ejection nozzle (34) is remote from the chamber (6) or at least partially located outside the chamber (6), and an extended position in which the nozzle (34) is closerType: ApplicationFiled: April 26, 2019Publication date: October 31, 2019Inventors: Fabien Stéphane GARNIER, François Pierre Michel COMTE, Arnaud Lasantha GENILIER, Vincent François Georges MILLIER
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Publication number: 20180232472Abstract: A method of determining a maximum acceptable alternating stress at a point of a part subjected to cyclic loading: simulating that the part is subjected to constant loading equal to a threshold value during a level period, and assuming that the part has elasto-viscoplastic behavior; from the results of the simulation, determining a final static stress at the point at the end or after the end of the level period; and for the point under consideration, using a Goodman diagram to determine the maximum acceptable alternating stress, which is determined for a static stress equal to the final static stress; the duration of the level period being equal to the duration of the loading of the testpieces that were used to draw up the Goodman diagram.Type: ApplicationFiled: July 19, 2016Publication date: August 16, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Geoffrey Juan DESMEURE, Francois Pierre Michel COMTE, Anais Suzanne Amelie GAUBERT, Arnaud Cyril LONGUET, Marine Laetitia Camille CHEVALIER, Michael Piers HANSOM, Lucie Marie Ida LANCIAUX