Safran Aircraft Engines

Clémentine Charlotte Marie Mouton

Didier René André Escure

Baptiste Dorian Lawniczek

Olivier Belmonte

Christophe Paul Jacquemard

Jérémy Phorla Lao

Emmanuel Pierre Dimitri Patsouris

Clément Cottet

Didier Jean-Louis Yvon

Olivier Bazot

Thomas Julien Nguyen Van

Maeva Daphné Gros-Borot

A blade includes a root to be mounted in a slot of plural slots which opens out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the rotor disk further including blades circumferentially distributed at the outer periphery of the rotor disk, each blade being mounted in a corresponding slot, the root including a first platform which has a radially outer surface, a shroud having a second platform which has a radially inner surface, and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge. The shroud is formed of a material and has a defined difficulty.

Aeronautical propulsion system

The invention relates to a turbine blade () for a movable wheel of a low-pressure turbine of an aeronautical propulsion system, comprising a root (), a shroud (), and an aerodynamically profiled airfoil () extending from the root () to the shroud (), wherein a parameter N2S is defined as: where:

Blade and slotted rotor wheel for a gas turbine engine

An unducted rectifier for a turbomachine is provided. The rectifier includes: (1) stator vanes each having a root and a blade radially projecting from the root, the root having two half-platforms; (2) pivots, each associated with a vane mounted so as to pivot about a pitch axis and configured to connect to a system for changing the pitch of the blades, each pivot having an upper platform and a cylindrical lower portion; and (3) attachment systems for attaching the half-platforms of the root of the vane to the associated pivot, each having two plates having a substantially identical shape to each half-platform and a clamping system for clamping the half-platforms between the plates of the attachment system and the upper platform of the pivot.

Unducted rectifier for a turbomachine, turbomachine module and aircraft turbomachine

A blade includes a root to be mounted in a slot of plural slots which open out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the rotor disk having an upstream surface and a downstream surface, each slot being delimited by a bottom surface, the rotor disk including blades circumferentially distributed at the outer periphery of the rotor disk, each blade being mounted in a corresponding slot, the root including a first platform which has a radially outer surface; a shroud having a second platform which has a radially inner surface; and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge.

A blade includes a root to be mounted in a slot of plural slots which opens out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the root including a first platform which has a radially outer surface; a shroud including a second platform which has a radially inner surface; and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge.

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.

Reduction gear having an epicyclic gear train for a turbine engine

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.

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Moissy-Cramayel, France

Clémentine Charlotte Marie Mouton