Patents by Inventor Jeremy Phorla Lao
Jeremy Phorla Lao 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: 11118509Abstract: A turbojet of the unducted rotor type and an aircraft including such a turbojet, the turbojet including a gas generator, a first unducted propeller connected to a shaft of the gas generator via first reduction gearing, and a second unducted propeller connected to a shaft of the gas generator via second reduction gearing, wherein the first propeller and the first reduction gearing are mounted at the front of the gas generator, and wherein the second propeller and the second reduction gearing are mounted at the rear of the gas generator.Type: GrantFiled: May 31, 2018Date of Patent: September 14, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thomas Julien Nguyen Van, Olivier Belmonte, Jeremy Phorla Lao, Clementine Charlotte Marie Mouton, Emmanuel Pierre Dimitri Patsouris, Didier Jean-Louis Yvon
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Patent number: 10479514Abstract: An assembly for an aircraft turbine machine including a receiver for a pair of open rotor contra-rotating propellers, the assembly including a duct, ancillaries routed inside the duct, an attachment case, attachment device of the duct on an annular installation portion of the case. The attachment device in an assembled configuration include a split ring fitted with internal projections housed inside orifices in the duct; a radial loading surface of the ring made on the portion the surface being tapered and narrowing along a first axial direction, and being in contact with a peripheral surface of the complementary shaped tapered split ring; device of axially loading the ring along the first direction, the device being blocked in the axial direction on the portion.Type: GrantFiled: January 4, 2017Date of Patent: November 19, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clementine Charlotte Marie Mouton, Olivier Belmonte, Jeremy Phorla Lao, Didier Jean-Louis Yvon
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Patent number: 10302187Abstract: A reduction gear having an epicyclic gear train for a turbine engine, in particular of an aircraft, comprising: a planetary shaft having an axis of rotation A; a ring gear having an axis A extending around said planetary shaft; planet gears distributed around said axis A, which mesh with said ring gear and the planetary shaft; and a planet carrier including members for supporting bearings of the planet gears, having axes of rotation B, which are evenly distributed around the axis A, as well as a part holding each supporting member substantially by the middle thereof along the axis B thereof, wherein said supporting members are made as a single part having means for supplying lubricating oil to said bearings. A method for assembling said reduction gear is also provided.Type: GrantFiled: April 21, 2016Date of Patent: May 28, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jérémy Phorla Lao, Olivier Belmonte, Clémentine Charlotte Marie Mouton, Thomas Julien Nguyen Van, Emmanuel Pierre Dimitri Patsouris
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Patent number: 10280795Abstract: A device for recovering oil injected by centrifugal effect in a turbine engine, comprising a substantially circular ring around an axis, the ring comprising a first part forming a basin surrounding the axis and having an opening turned radially inward, so as to recover the oil injected radially across from the opening, and a second part forming a substantially toroidal chamber, radially open outward at a low point, so as to allow oil to escape, a passage being arranged between the basin and the chamber substantially over the entire circumference around the axis so as to cause the oil recovered by the basin to enter the chamber, wherein a rim is arranged between a radially inner bottom of the chamber and the passage, so as to contain the oil accumulating in this radially inner bottom of the chamber, and in some embodiments, at a high point.Type: GrantFiled: June 9, 2017Date of Patent: May 7, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jérémy Phorla Lao, Olivier Belmonte, Clémentine Charlotte Marie Mouton
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Publication number: 20180347460Abstract: A turbojet of the unducted rotor type and an aircraft including such a turbojet, the turbojet comprising a gas generator (3-8), a first unducted propeller (21) connected to a shaft (81) of the gas generator (3-8) via first reduction gearing (23), and a second unducted propeller (91) connected to a shaft (81) of the gas generator (3-8) via second reduction gearing (93), wherein the first propeller (21) and the first reduction gearing (23) are mounted at the front of the gas generator (3-8), and wherein the second propeller (91) and the second reduction gearing (93) are mounted at the rear of the gas generator (3-8).Type: ApplicationFiled: May 31, 2018Publication date: December 6, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Thomas Julien NGUYEN VAN, Olivier BELMONTE, Jeremy Phorla LAO, Clementine Charlotte Marie MOUTON, Emmanuel Pierre Dimitri PATSOURIS, Didier Jean-Louis YVON
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Publication number: 20180163850Abstract: A reduction gear having an epicyclic gear train for a turbine engine, in particular of an aircraft, comprising: a planetary shaft having an axis of rotation A; a ring gear having an axis A extending around said planetary shaft; planet gears distributed around said axis A, which mesh with said ring gear and the planetary shaft; and a planet carrier including members for supporting bearings of the planet gears, having axes of rotation B, which are evenly distributed around the axis A, as well as a part holding each supporting member substantially by the middle thereof along the axis B thereof, wherein said supporting members are made as a single part having means for supplying lubricating oil to said bearings. A method for assembling said reduction gear is also provided.Type: ApplicationFiled: April 21, 2016Publication date: June 14, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jérémy Phorla Lao, Olivier Belmonte, Clémentine Charlotte Marie Mouton, Thomas Julien Nguyen Van, Emmanuel Pierre Dimitri Patsouris
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Patent number: 9995176Abstract: The device (20) comprises two outer and inner concentric rings (22, 23), one of which is connected to an oil supply from one of the repositories, the other ring being connected to the other repository, the oil flowing between said rings, and bearings between the rings in order to change repositories between the two rings. According to the invention, the device (20) further comprises a flexible means (31) forming a shock absorber, provided between a first of said rings and an intermediate ring (41) that is separated from a second of said rings by said bearings (25), said flexible means (31) defining a deformable sealed chamber (32) in which oil travels between the two repositories.Type: GrantFiled: October 1, 2014Date of Patent: June 12, 2018Assignee: SNECMAInventors: Olivier Belmonte, Jérémy Phorla Lao
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Patent number: 9926944Abstract: A device for guiding variable pitch diffuser vanes of a turbine engine is provided. The device includes a first ring having an axial portion at its periphery that is extended by a collar extending radially outwards; a second ring mounted around the axial portion of the first ring so as to cooperate therewith to define a plurality of outwardly open sockets; a plurality of cylindrical bushings, each mounted in a respective socket for the purpose of receiving a guide pivot of a diffuser vane; and a resilient clamping ring for cooperating with one of the rings in order to clamp the two rings axially one against the other.Type: GrantFiled: July 28, 2014Date of Patent: March 27, 2018Assignee: SNECMAInventors: Clementine Charlotte Marie Mouton, Olivier Belmonte, Alain Marc Lucien Bromann, Jeremy Phorla Lao
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Publication number: 20170356306Abstract: A device for recovering oil injected by centrifugal effect in a turbine engine, comprising a substantially circular ring around an axis, the ring comprising a first part forming a basin surrounding the axis and having an opening turned radially inward, so as to recover the oil injected radially across from the opening, and a second part forming a substantially toroidal chamber, radially open outward at a low point, so as to allow oil to escape, a passage being arranged between the basin and the chamber substantially over the entire circumference around the axis so as to cause the oil recovered by the basin to enter the chamber, wherein a rim is arranged between a radially inner bottom of the chamber and the passage, so as to contain the oil accumulating in this radially inner bottom of the chamber, and in some embodiments, at a high point.Type: ApplicationFiled: June 9, 2017Publication date: December 14, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jérémy Phorla Lao, Olivier Belmonte, Clémentine Charlotte Marie Mouton
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Publication number: 20170190433Abstract: The invention relates to an assembly (60) for an aircraft turbine machine comprising a receiver for a pair of open rotor contra-rotating propellers, the assembly comprising a duct (52), ancillaries routed inside the duct, an attachment case (54), attachment means (62) of the duct on an annular installation portion (64) of the case (54). According to the invention, the attachment means (62) in an assembled configuration include: a split ring (66) fitted with internal projections (71) housed inside orifices (72) in the duct; a radial loading surface (68) of the ring made on the portion (64) the surface (68) being tapered and narrowing along a first axial direction, and being in contact with a peripheral surface (70) of the complementary shaped tapered split ring; means (80) of axially loading the ring along the first direction, these means (80) being blocked in the axial direction on the portion (64).Type: ApplicationFiled: January 4, 2017Publication date: July 6, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Clementine Charlotte Marie MONTON, Olivier BELMONTE, Jeremy Phorla LAO, Didier Jean-Louis YVON
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Publication number: 20160363133Abstract: The invention relates to a device for guiding variable pitch diffuser vanes of a turbine engine, the device comprising a first ring (26) having an axial portion (32) at its periphery that is extended by a collar (34) extending radially outwards, a second ring (28) mounted around the axial portion of the first ring so as to co-operate therewith to define a plurality of outwardly open sockets (36), a plurality of cylindrical bushings (22), each mounted in a respective socket for the purpose of receiving a guide pivot (12) of a diffuser vane (4), and a resilient clamping ring (30) for cooperating with one of the rings in order to clamp the two rings axially one against the other.Type: ApplicationFiled: July 28, 2014Publication date: December 15, 2016Applicant: SNECMAInventors: Clementine Charlotte Marie MOUTON, Olivier Belmonte, Alain Marc Lucien Bromann, Jeremy Phorla Lao
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Publication number: 20160245116Abstract: The device (20) comprises two outer and inner concentric rings (22, 23), one of which is connected to an oil supply from one of the repositories, the other ring being connected to the other repository, the oil flowing between said rings, and bearings between the rings in order to change repositories between the two rings. According to the invention, the device (20) further comprises a flexible means (31) forming a shock absorber, provided between a first of said rings and an intermediate ring (41) that is separated from a second of said rings by said bearings (25), said flexible means (31) defining a deformable sealed chamber (32) in which oil travels between the two repositories.Type: ApplicationFiled: October 1, 2014Publication date: August 25, 2016Inventors: Olivier BELMONTE, Jérémy Phorla LAO