-
公开(公告)号：US20200332721A1
公开(公告)日：2020-10-22
申请号：US16848642
申请日：2020-04-14
摘要： A mechanical reduction gear for a turbomachine, in particular for an aircraft, this reduction gear including a sun gear having an axis of rotation, a ring gear which extends around the sun gear and which is configured to be fixed in rotation around the axis, planet gears which are in mesh with the sun gear and the ring gear and which are held by a planet carrier which is configured to be fixed or in rotation around the axis, each planet gear including a first toothing of average diameter D1 for the meshing with the sun gear, and a second toothing of average diameter D2, different from D1, for the meshing with the ring gear, wherein the first and second toothings of each planet gear include herringbone teeth and are symmetrical with respect to a plane perpendicular to the axis and passing substantially in the middle of the planet gear.
-
公开(公告)号：US20230400093A1
公开(公告)日：2023-12-14
申请号：US18332609
申请日：2023-06-09
CPC分类号： F16H57/082 , F02C6/20 , F05D2260/40311 , F05D2220/323
摘要： A planet carrier for a mechanical gearbox of a turbomachine, in particular for an aircraft, the planet carrier being formed in a single piece and comprising two annular flasks connected by material bridges and together defining housings configured to receive planet gears, the flasks comprising orifices for mounting the planet gears which are oriented axially and which open into the housings. One of the flasks can include at least one thinning around its orifices, the at least one thinning defining a minimum thickness of material in the axial direction which is less than a minimum thickness of the other flask around each of its orifices.
-
公开(公告)号：US20230091328A1
公开(公告)日：2023-03-23
申请号：US17933606
申请日：2022-09-20
发明人： Guillaume Pierre MOULY , Adrien Louis SIMON , Guillaume Julien BECK , Simon Loic Clement LEFEBVRE
IPC分类号： F02C7/36
摘要： A power transmission module for an aircraft, the module including a torque input connected to a turbine shaft, a first torque output and a second torque output, the power transmission module including a mechanical reducer including a sun gear forming the torque input, and planet gears carried by a planet carrier, wherein each of the planet gears includes at least three independent toothings and further includes a first toothing meshed with the sun gear, a second toothing meshed with an element forming one of the torque outputs, and a third toothing meshed with another element
-
公开(公告)号：US20220243662A1
公开(公告)日：2022-08-04
申请号：US17582546
申请日：2022-01-24
摘要： The present invention relates to a mechanical reducer (6) for a turbomachine, in particular an aircraft, this reducer (6) including: a sun gear extending around an axis (61) of rotation, a crown which extends around the sun gear and which is configured to be fixed in rotation around said axis (61), planet gears which are meshed with the sun gear and the crown and which are held by a planet carrier (62) which is configured to be movable in rotation about said axis (61), In addition, the oil distributor (65) comprises a plurality of oil distribution modules (67) assembled together, each module (67) comprising at least one lubrication pipe (68) having an inlet intended to receive oil and an outlet (69) adapted to lead the oil into an opening (63) of the planet carrier (62), the opening (63) being intended for lubricating the reducer.
-
公开(公告)号：US20240151303A1
公开(公告)日：2024-05-09
申请号：US18177988
申请日：2023-03-03
CPC分类号： F16H57/0479 , F16H57/043 , F16H2057/085
摘要： A mechanical reducer for a turbomachine, in particular for an aircraft, this reducer including a sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, hydrodynamic bearings for guiding the planet gears in rotation, these hydrodynamic bearings being carried by a planet carrier and including cylindrical bodies which include an internal oil circulation cavity and first pipelines for conveying oil from this cavity to at least one external cylindrical surface of the body, wherein each of the cylindrical bodies further includes second oil evacuation pipelines, which are different from the first pipelines, and which extend from said at least one external cylindrical surface to at least one of the longitudinal ends of that body.
-
公开(公告)号：US20240084876A1
公开(公告)日：2024-03-14
申请号：US18461740
申请日：2023-09-06
发明人： Guillaume Pierre MOULY , Guillaume Julien BECK , Patrice Julien PTASZYNSKI , Jean-Pierre SEREY , Adrien Louis SIMON
摘要： A planet carrier for a speed reducer of an aircraft turbomachine, the planet carrier including a cage carrier and a cage. The cage can have two parts: a first part having a wall and bridges, these bridges projecting axially from a face of this wall and including first axial ends connected to this face and second free axial ends; and a second part having another of the walls, this other wall including a face to which the free ends of the bridges are applied. The two parts of the cage can be attached together by screws.
-
公开(公告)号：US20240084738A1
公开(公告)日：2024-03-14
申请号：US18465630
申请日：2023-09-12
发明人： Guillaume Pierre MOULY , Guillaume Julien BECK , Jordane Emile Andre PELTIER , Jean-Pierre SEREY , Adrien Louis SIMON
CPC分类号： F02C7/36 , F16H1/28 , F16H57/0456 , F16H57/08 , F16H2057/085
摘要： An aircraft turbomachine including a mechanical reduction gear including one sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, each planet gear including a first toothing for meshing with the sun gear, and a second toothing for meshing with the ring gear, the first toothing of each planet gear having a diameter greater than that of the second toothing of the planet gear, and a planet carrier, wherein the sun gear is coupled to a first rotor shaft of the turbomachine, the planet carrier is coupled to a second rotor shaft of the turbomachine, the ring gear is fixed to a stator of the turbomachine.
-
公开(公告)号：US20240084712A1
公开(公告)日：2024-03-14
申请号：US18465336
申请日：2023-09-12
IPC分类号： F01D15/12
CPC分类号： F01D15/12 , F05D2240/50 , F05D2260/40311 , F05D2260/98
摘要： A drive assembly for a mechanical reducer for a turbomachine, in particular for an aircraft, includes planet gears, a planet carrier having at least one transverse wall, plain bearings for guiding the planet gears in rotation, and an oil supply circuit for the plain bearings. The planet carrier has collars for attaching the planet gears to the at least one transverse wall, and each of the planet gears includes at least one external cylindrical surface for forming an oil film with an internal cylindrical surface portion of each of the collars for forming said oil film.
-
公开(公告)号：US20220145769A1
公开(公告)日：2022-05-12
申请号：US17453607
申请日：2021-11-04
摘要： A mechanical gearbox for turbomachine, in particular for aircraft. The gearbox includes a sun gear including an external toothing, a ring gear including an internal toothing, and planet gears which are meshed with the sun gear and the stationary ring gear. The planet gears are carried by a movable planet carrier and each having external toothings of different diameters. The movable planet carrier includes a movable ring gear which carries an internal toothing and which is independent of the stationary ring gear, each of the planet gears being meshed with the sun gear and the stationary and movable ring gears.
-
公开(公告)号：US20210388769A1
公开(公告)日：2021-12-16
申请号：US17341893
申请日：2021-06-08
发明人： Guillaume Julien BECK , Guillaume Pierre MOULY , Simon Loic Clement LEFEBVRE , Quentin Pierre Henri PIGOTT , Adrien Louis SIMON
摘要： A mechanical reduction gear for turbomachine, in particular for aircraft. The reduction gear includes a sun gear having an axis of rotation, a ring gear which extends around the sun gear, planet gears which are meshed with the sun gear and the ring gear and which each includes a first toothing and a second toothing each including two series of teeth located on either side of a median plane, each of the planet gears being centred and guided in rotation by bearings, including an upstream bearing interposed axially between the series of upstream teeth of the second toothing and the plane, and a downstream bearing interposed axially between the series of downstream teeth of the second toothing and the plane.
-
-
-
-
-
-
-
-
-
搜索结果
10 条记录 (耗时 0.015 秒)
