Abstract: Described herein are devices and methods related to compositionally graded buffers (CGB) and methods and/or systems for producing CGBs. CGBs enable the growth of high quality materials that are lattice mismatched to a substrate. More specifically, the present disclosure relates to methods for making CGBs by hydride vapor phase epitaxy (HVPE). HVPE methods using a single chamber for producing a CGB may result in a transience in the CGB layers as the flows supplying the reactants are switched to produce the next subsequent layer in the CGB. In contrast to this static style of grading, the present disclosure describes a dynamic method for producing CGBs, in which multiple growth chambers are utilized.

Abstract: 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.

Abstract: 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.

Abstract: A propulsion system includes a drive shaft that rotates about an axis, a fan, a fan shaft that drives the fan about the axis, a reduction mechanism coupling the drive and fan shafts, a compression section driven by the drive shaft, and an inlet channel that extends between the fan and the compression section. The inlet channel includes inner and outer ferrules delimiting an air inlet flow path, the inner ferrule having a minimum radius. The reduction mechanism includes two reduction stages including two or more planet gears circumferentially distributed around the axis, each planet gear including a first portion meshed with the drive shaft and a second portion meshed with the fan shaft and being mounted fixed with respect to the inner ferrule and having a maximum radius greater than the minimum radius such that the air inlet flow path extends partly between the two or more planet gears.

Abstract: A method of estimating a pose for a custom character is disclosed. A skeleton corresponding to a user-supplied character is received or access. Features of the skeleton of the user-supplied character are computed. A set of betas and a scale value that correspond to a skinned multi-person linear (SMPL) model of the user-supplied skeleton are computed. The pose of the skeleton of the custom character is estimated using the SMPL model.

Abstract: 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.

Abstract: 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.

Abstract: Load aware load balancing may be provided. Flow duration data associated with a plurality of flows associated with a plurality of servers may be obtained. Then a plurality of queue lengths respectively associated with the plurality of servers may be obtained. Next, a Shortest Expected Delay (SED) score may be determined for each of the plurality of servers based on the flow duration data and the plurality of queue lengths. A flow may then be assigned to a one of the plurality of servers having the lowest SED score.

Abstract: A propulsion system includes a drive shaft that rotates about an axis, a fan, a fan shaft that drives the fan about the axis, a reduction mechanism coupling the drive and fan shafts, a compression section driven by the drive shaft, and an inlet channel that extends between the fan and the compression section. The inlet channel includes inner and outer ferrules delimiting an air inlet flow path, the inner ferrule having a minimum radius. The reduction mechanism includes two reduction stages including two or more planet gears circumferentially distributed around the axis, each planet gear including a first portion meshed with the drive shaft and a second portion meshed with the fan shaft and being mounted fixed with respect to the inner ferrule and having a maximum radius greater than the minimum radius such that the air inlet flow path extends partly between the two or more planet gears.

Abstract: A diagnostic manometry device comprises a catheter including a plurality of lumens, a fluid charger configured to operatively couple with the catheter, and a charging mechanism for moving fluid simultaneously from fluid pressure chambers of the plurality of fluid pressure chambers into the respective lumens of the plurality of lumens when the catheter is operatively coupled with the fluid charger. Each fluid pressure chamber of the plurality of fluid pressure chambers is configured to be in fluid communication with a respective lumen of the plurality of lumens when the catheter is operatively coupled with the fluid charger. Each pressure sensor of the plurality of pressure sensors is located and configured to measure a fluid pressure change in a respective fluid pressure chamber of the plurality of fluid pressure chambers. Additional manometry devices and methods of forming a manometry device are also disclosed.

Abstract: A pre-assembly method for an aircraft turbomachine, having preliminary assembling, outside the turbomachine, the following components with each other a reduction gear configured to transmit a rotation between at least two rotors of the turbomachine while modifying the speed and torque ratio from one to the other of said at least two rotors, a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of said at least two rotors, a bearing support, and at least one bearing mounted on the bearing support and configured to rotatably support the shaft.

Abstract: A planet carrier for a mechanical gearbox for a turbomachine includes a one-piece cage that extends about an axis of rotation defining an internal housing configured to receive a sun gear and planet gears of the gearbox. The planet carrier further includes a lubrication system with at least one bore formed in the cage and extending parallel to the axis over more than 30% of a maximum axial dimension (Lmax) of the cage. The lubrication system also includes for the at least one bore, at least two sprinklers which are fitted to the cage and which are each mounted in a recess of the cage.

Abstract: 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.

Abstract: A propulsion system includes a drive shaft, a fan, a fan shaft, and a reduction device coupling the drive and fan shafts. The reduction device includes a first reduction stage and a second reduction state, and include a sun gear, centered on an axis of rotation of the drive and fan shafts and driven in rotation by the drive shaft, a ring gear, coaxial with the sun gear and that drives the fan shaft in rotation about the axis, and planet gears distributed circumferentially about the axis between the sun and ring gears, each planet gear including a first portion which is meshed with the sun gear and a second portion which is meshed with the ring gear, a diameter of the first portion being different from a diameter of the second portion, and an oil transfer bearing positioned between the fan and the reduction device.

Abstract: A mechanical reducer for a turbomachine for an aircraft, this reducer having a sun gear with internal splines and an external toothing, a ring gear which extends around the sun gear and which has an internal toothing, planet gears which are arranged between the sun gear and the ring gear and which each have at least one external toothing meshing with the external toothing of the sun gear and the internal toothing of the ring gear, and a planet carrier which carries first bearings for guiding the planet gears in rotation. The reducer can further include at least one second bearing for guiding the sun gear in rotation. The at least one second bearing can be mounted between the sun gear and the planet carrier.

Abstract: The present invention relates to an oil transfer device (1) for lubricating a planet carrier, movable in rotation, of an epicyclic gear train for a turbomachine, the device (1) extending around an axis (A) and having: an annular casing (11) which extends around the axis (A), the casing (11) comprising a plurality of oil feed grooves (14), axially juxtaposed, each having an oil ejection opening configured to lead radially to a lubrication circuit of the planet carrier to be lubricated, the device (1) being characterized in that one of the oil feed grooves (14) is a high-pressure oil feed groove (14), called a high-pressure groove (14a), and another of the other oil feed grooves (14) is a low-pressure oil feed groove (14), called a low-pressure groove (14b), axially juxtaposed to the high-pressure groove (14a), the grooves (14) being arranged axially along the axis (X) so that the oil is able to be transferred axially from the high-pressure groove (14a) to the low-pressure groove (14b).

Abstract: A mechanical reduction gear for a turbomachine, in particular for an aircraft, the reduction gear 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 bearings being carried by a planet carrier and including cylindrical bodies which are engaged in the planet gears and which are configured so as to be supplied with oil and so as to form guiding oil films between the bodies and the planet gears, wherein each of the planet gears is guided by two hydrodynamic bearings independent of each other and disposed on either side of the plane.

Abstract: A propulsion system includes a drive shaft movable in rotation about an axis of rotation, a low-pressure compressor driven in rotation by the drive shaft, the low-pressure compressor having a mean radius, a fan shaft, a fan driven in rotation by the fan shaft, a reduction mechanism coupling the drive shaft and the fan shaft, having a reduction ratio, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet channel having an inlet adjacent to the fan and an outlet opposite the inlet and adjacent to the low-pressure compressor, the inlet having a mean radius. A first ratio between a ratio of a mean radius of the inlet channel and the mean radius of the low-pressure compressor, and the reduction ratio of the reduction mechanism, is strictly less than 0.35.

Abstract: A propulsion system includes a drive shaft movable about an axis of rotation, a fan, a fan shaft that drives the fan, and a reduction device coupling the drive shaft and the fan shaft. The reduction device has first and second reduction stages and includes a sun gear, centered on the axis and driven by the drive shaft, a ring gear that is coaxial with the sun gear and that drives the fan shaft about the axis, and planet gears distributed circumferentially about the axis between the sun gear and the ring gear. Each planet gear includes a first portion meshed with the sun gear and a second portion meshed with the ring gear. A diameter of the first portion is different from a diameter of the second portion, and the first portion of the planet gears extend between the second portion of the planet gears and the fan.

Abstract: A method for manufacturing a mechanical reducer for an aircraft turbomachine including a central pinion, an outer crown, N planet pinions, where N?3, each planet pinion including a first stage meshing with the central pinion, and a second stage meshing with the outer crown, the method including the assembly marking, wherein N teeth of the central pinion are marked, and N pairs of teeth of the first stage of each planet pinion are marked, the N planet pinions each being marked identically, and the assembly of the mechanical reducer, so that the teeth of the pairs of marked teeth of the first stage of each planet pinion are disposed on either side of a marked tooth of the central pinion.