Abstract: An arrangement for an aircraft turbine engine, including a shaft and a follower element rotatably coupled to the shaft by a spline connection, the arrangement including upstream and downstream connections for radially centring the follower element relative to the shaft; means for spraying a lubricant into a collection cavity; a passage for receiving lubricant, which passage opens into the collection cavity and into a cavity for lubricating the splines which is partially defined by the upstream and downstream radial centring connections; and a passage for discharging lubricant, which passage opens into the cavity for lubricating the splines and outside the arrangement.

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 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 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: The present invention relates to a process for preparing the macrocyclic ligand of formula (L) below: involving: i) decomplexation of the complex of formula (II): constituted of at least 80% of a diastereoisomeric excess comprising a mixture of isomers II-RRR and II-SSS of formulae: ii) removing the gadolinium salt formed in step i), for example by filtration, and ii) recovering the free macrocyclic ligand of formula (L). The present invention also relates to a composition comprising the diastereoisomerically enriched complex of formula (II) and the macrocyclic ligand of formula (L).

Abstract: The invention relates to a turbine engine module, comprising: - a fan shaft (6), - a power shaft (15) rotating the fan shaft via a speed reducer (21) arranged in a lubrication chamber (22), - a lubrication system (50) for the speed reducer (21) having a main circuit (51), which is closed, for supplying the lubrication chamber, and an auxiliary circuit (60), which is closed, for supplying the lubrication chamber when the main circuit is inactive, the auxiliary circuit comprising an auxiliary pump (61) driven by an electric motor (63), and - an electric machine (65) configured to power the electric motor (63), the electric machine having a rotor connected to the fan shaft in order to be rotated and a stator mounted on a stationary member at least partially supporting the electric machine.

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: Many embodiments can comprise a system. The system can comprise a processor and a memory coupled to the processor. The memory can include instructions that, when executed by the processor, cause the processor to: determine a direction of gravity in each image of a sequence of images around an object; estimate a center of mass of the object in each image of the sequence of images using the direction of gravity and dimensions of the object; stabilize each image in the sequence of images using the center of mass; and generate a 360 degree display of the object using each image in the stabilized sequence of images. Other embodiments are disclosed herein.

Abstract: An arrangement for an aircraft turbine engine, including a shaft and a follower element rotatably coupled to the shaft by a spline connection, the arrangement including upstream and downstream connections for radially centring the follower element relative to the shaft; means for spraying a lubricant into a collection cavity; a passage for receiving lubricant, which passage opens into the collection cavity and into a cavity for lubricating the splines which is partially defined by the upstream and downstream radial centring connections; and a passage for discharging lubricant, which passage opens into the cavity for lubricating the splines and outside the arrangement.

Abstract: The present invention relates to a complex of formula (II) constituted of at least 90% of a diastereoisomeric excess comprising a mixture of isomers II-RRR and II-SSS of formulae: The present invention also relates to a process for preparing and purifying said complex of formula (II), and also to a composition comprising said complex.

Abstract: Many embodiments can comprise a system. The system can comprise one or more processors and one or more storage devices. The one or more storage devices can be configured to store computing instructions that, when executed, cause the processor to receive a plurality of images of an object, the plurality of images comprising different views of the object from around the object; iteratively align one or more images within one or more subsets of the plurality of images until the object is aligned from image to image within the one or more subsets of the plurality of images; and selectively align respective images of the one or more subsets to each other to produce a surround image. Other embodiments are disclosed herein.

Abstract: The present invention relates to a complex of formula (II) constituted of at least 90% of a diastereoisomeric excess comprising a mixture of isomers II-RRR and II-SSS of formulae: The present invention also relates to a process for preparing and purifying said complex of formula (II), and also to a composition comprising said complex.

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: An aero-propulsion system includes a drive shaft, a low-pressure compressor, a fan shaft driving a fan, a reduction device that couples the drive shaft and the fan shaft, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet having a predetermined mean radius, a ratio between a mean radius of the inlet channel and the mean radius of the low-pressure compressor, on the one hand, and the reduction ratio of the reduction mechanism, on the other hand, being less than 0.35.

Abstract: The present invention relates to a complex of formula (II) constituted of at least 80% of a diastereoisomeric excess comprising a mixture of isomers II-RRR and II-SSS of formulae: The present invention also relates to a process for preparing said complex of formula (II), and also to two synthetic intermediates.

Abstract: A turbine engine mechanical reduction gear, for example, of an aircraft, the reduction gear comprising: a sun gear having an axis of rotation; a ring gear which extends around the sun gear and which is configured to be immobile in rotation about the axis; planetary gears which are meshed with the sun gear and the ring gear and which are supported by a planetary carrier which is configured to be mobile in rotation about the axis; at least one lubrication oil distributor which comprises a stator portion immobile in rotation and a rotating integral rotor portion of the planetary carrier; and an annular oil deflector which is integral with the ring gear, wherein the stator portion of the distributor is integral with the deflector.

Abstract: The present invention relates to a complex of formula (II) constituted of at least 90% of a diastereoisomeric excess comprising a mixture of isomers II-RRR and II-SSS of formulae: The present invention also relates to a process for preparing and purifying said complex of formula (II), and also to a composition comprising said complex.

Abstract: The present invention relates to a complex of formula (II) constituted of at least 80% of a diastereoisomeric excess comprising a mixture of isomers II-RRR and II-SSS of formulae: The present invention also relates to a process for preparing said complex of formula (II), and also to two synthetic intermediates.

Abstract: The present invention relates to a complex of formula (II) constituted of at least 90% of a diastereoisomeric excess comprising a mixture of isomers II-RRR and II-SSS of formulae: The present invention also relates to a process for preparing and purifying said complex of formula (II), and also to a composition comprising said complex.

Abstract: The present invention relates to a complex of formula (II) constituted of at least 90% of a diastereoisomeric excess comprising a mixture of isomers II-RRR and II-SSS of formulae: The present invention also relates to a process for preparing and purifying said complex of formula (II), and also to a composition comprising said complex.