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公开(公告)号：US11118509B2
公开(公告)日：2021-09-14
申请号：US15994265
申请日：2018-05-31
发明人： Thomas Julien Nguyen Van , Olivier Belmonte , Jeremy Phorla Lao , Clementine Charlotte Marie Mouton , Emmanuel Pierre Dimitri Patsouris , Didier Jean-Louis Yvon
摘要： 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.
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2.发明授权公开(公告)号：US10584641B2
公开(公告)日：2020-03-10
申请号：US15566861
申请日：2016-04-14
发明人： Didier Rene Andre Escure , Jean-Francois Endy Bersot , Tewfik Boudebiza , Gilles Alain Charier , Thomas Julien Nguyen Van , Jean Philippe Pierre-Alain Reigner
摘要： Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53A) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).
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3.发明授权公开(公告)号：US10443609B2
公开(公告)日：2019-10-15
申请号：US15137302
申请日：2016-04-25
发明人： Emmanuel Pierre Dimitri Patsouris , Olivier Belmonte , Clementine Charlotte Marie Mouton , Thomas Julien Nguyen Van
摘要： A device for controlling the pitch of fan blades in a turbine engine having an unducted fan including at least one set of adjustable pitch fan blades, each fan blade being coupled, for pitch adjustment purposes, to a radial control shaft constrained to rotate with the set of fan blades and suitable for pivoting about a radial pitch axis of the fan blade, the device including a stationary actuator centered on a longitudinal axis of the turbine engine and driving an outer ring of a load transfer bearing in translation, the outer ring of the load transfer bearing being coupled directly to a lever arm of each control shaft via a respective ball joint connection in order to adjust its pivoting.
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公开(公告)号：US11052994B2
公开(公告)日：2021-07-06
申请号：US16067523
申请日：2016-12-22
摘要： A turbine engine module including an upstream propulsive unit including a propellers doublet that are upstream and downstream, respectively mounted around an axis, a power turbine shaft with axis of rotation intended for rotating the propellers doublet, a speed reducer connected to the propellers doublet and driven by the shaft, and, a pitch-changing system including a cylinder that controls the pitch of the blades of the upstream propeller the rotational axis of the propellers doublet is shifted in relation to that of the shaft. The cylinder is placed downstream of the reducer, and the pitch-changing system includes a shaft for controlling the pitch of the blades that connect the cylinder to the blades of the upstream propeller.
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公开(公告)号：US10302187B2
公开(公告)日：2019-05-28
申请号：US15567493
申请日：2016-04-21
发明人： Jérémy Phorla Lao , Olivier Belmonte , Clémentine Charlotte Marie Mouton , Thomas Julien Nguyen Van , Emmanuel Pierre Dimitri Patsouris
摘要： 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.
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公开(公告)号：US20180163850A1
公开(公告)日：2018-06-14
申请号：US15567493
申请日：2016-04-21
发明人： Jérémy Phorla Lao , Olivier Belmonte , Clémentine Charlotte Marie Mouton , Thomas Julien Nguyen Van , Emmanuel Pierre Dimitri Patsouris
CPC分类号： F16H57/082 , F01D25/18 , F02C7/36 , F02K3/025 , F05D2220/324 , F05D2230/53 , F05D2260/40311 , F16H57/0479 , F16H57/0482 , F16H2057/085 , Y02T50/671
摘要： 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.
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