Safran Transmission Systems

Safran Aircraft Engines

Clément Paul René Niepceron

Boris Pierre Marcel Morelli

Olivier Belmonte

Adrien Louis Simon

Paul Ghislain Albert Levisse

Marc Dominique Seyfrid

Amélie Argie Antoinette Chassagne

Florian Rappaport

Simon Loïc Clément Lefebvre

Olivier Formica

Fabrice Joel Luc Chevillot

Romain Truco

Bernard Guy Antoine Charpentier

Fabrice Joël Luc Chevillot

A turbomachine having a contrarotating turbine for an aircraft, the turbomachine including a contrarotating turbine of which a first rotor is configured to rotate in a first direction of rotation and is connected to a first turbine shaft, and a second rotor configured to rotate in an opposite direction of rotation and connected to a second turbine shaft. The first rotor includes turbine wheels interleaved between turbine wheels of the second rotor, the turbomachine further including a planetary-type epicyclic mechanical reduction gear which has a sun gear driven in rotation by the second shaft, a ring gear driven in rotation by the first shaft, and a planet carrier attached to a first stator casing of the turbomachine located upstream of the contrarotating turbine with respect to a direction of flow of gas in the turbomachine. The turbomachine includes bearings for guiding the first and second shafts.

Turbomachine having a contrarotating turbine for an aircraft

An epicyclic reduction gear for a turbomachine includes a sun gear that is rotatable about a first axis and a ring gear surrounding the sun gear and also rotatable about the first axis. The ring gear is secured to a ring gear carrier that rotates a fan shaft. At least one planet gear is rotatable about a second axis and is meshed with the sun gear and the ring gear. The planet gear is guided in rotation about the second axis relative to a bearing of the planet carrier. A piece of equipment comprising a rotor. The piece of equipment is attached to the bearing of the planet carrier and has a rotor rotated by the ring gear carrier.

Epicyclic reduction gear for a turbomachine

A turbomachine with a counter-rotating turbine for an aircraft includes a counter-rotating turbine and a mechanical reduction gear with an epicyclic, planetary-type gear train. The gear train includes a planet carrier secured to a stator housing of the turbomachine situated upstream from the counter-rotating turbine in relation to a direction of gas flow within the turbomachine. The planet carrier is secured to the stator housing by an annular part with an elongated shape extending inside the second shaft. The annular part includes an upstream end secured to the intermediate casing and a downstream end coupled to the planet carrier. The annular part also includes an integrated circuit for conveying lubrication oil from its upstream end to the planet carrier.

Turbomachine with counter-rotating turbine for an aircraft

The invention relates to an epicyclic reduction gear for a turbomachine, including a sun wheel that is rotatable about a first axis (A); a ring gear surrounding the sun wheel and being rotatable about the first axis (A); at least one planetary gear that is rotatable about a second axis (B), the planetary gear being meshed with the sun wheel and the ring gear; an immobile planet carrier, the planetary gear being rotatably guided about the second axis (B) with respect to a bearing of the planet carrier; an item of equipment including a rotor. The invention is characterized in that the item of equipment is fastened to the bearing of the planet carrier and the rotor of the item of equipment is rotatably driven by the planetary gear.

A reduction gear for a turbomachine () extending around an axis (X-X) of rotation, comprising a ring gear () connected to a ring gear carrier (), wherein the ring gear carrier () has, according to a section view along a plane including the axis (X-X), an internal segment (), an external segment () and a ring gear support (), extending successively from the internal shaft () until the ring gear support (), the internal segment () extends until a radius Rwith respect to the axis (X-X), the external segment () forms an angle &#x3b2; with the internal segment (), the ring gear support () forms an angle &#x3b1; with the external segment (), and is secured to the ring gear () via a bolted connection accomplished at a nominal radius Rwith respect to the axis (X-X), in that the ratio R/Ris comprised between 0.3 and 0.7.

Reduction gear for ring gear retention

A mechanical reduction gear for a turbomachine, in particular for an aircraft, including a first sun gear having a central axis forming a main axis of the reduction gear, a ring gear, planet gears, a planet carrier, and at least one electric generator, in which the electric generator has a first set of electromagnetic elements and a second set of electromagnetic elements, wherein one among the first and second set of electromagnetic elements is a first set of coils, each coil of this first set of coils being wound around a direction parallel to the main axis, and in which the other among the first and second set of electromagnetic elements is configured to induce a current in the first set of coils when it is driven with a relative movement with respect to the first set of coils.

Reduction gear for turbomachine equipped with an electric generator

The invention concerns a process for the assembly of an epicyclic or planetary gear train of a planet gear carrier comprising one or more bores, each of the bores being intended to receive a pivot (), the process comprising the following steps:

Process for the assembly of an epicyclic or planetary gear train

The invention concerns a process for the assembly of an epicyclic or planetary gear train from at least one pivot () and a planet gear carrier () comprising one or more bores, each of said bores being intended to receive a pivot (), the process comprising the following steps:

Process for the assembly of a gear train

A mechanical reduction gear is suitable for a turbomachine and, in particular, a turbomachine of an aircraft. The reduction gear includes a sun gear, a ring gear formed by two half-ring gears, planet gears arranged between the sun gear and the ring gear, and at least one shaft rotationally fixed to the ring gear. The reduction gear further includes an annular covering part that extends around the ring gear and is independently fixed by flanges and/or splines to each of the half-ring gears.

Growing community of inventors

Moissy-Cramayel, France

Clément Paul René Niepceron