Safran Aircraft Engines

Centre National De La Recherche Scientifique

Safran Transmission Systems

Ecole Centrale De Lyon

Ecole Nationale D'ingenieurs De Saint-etienne

Fabrice Joel Luc Chevillot

Olivier Belmonte

Julien Fabien Patrick Becoulet

Arnaud Nicolas Negri

Paul Ghislain Albert Levisse

Emmanuel Pierre Dimitri Patsouris

Clément Paul René Niepceron

Olivier Formica

Romain Truco

Marie-Oceane Parent

Fabrice Hugues Jean Pierre Thouverez

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

The invention concerns a power transmission system of a turbomachine, comprising: According to the invention, the recovery chamber is provided with an inlet opening () directed radially outwardly and defined in a plane radially lower than a plane where an outlet port () of the ejection means is defined.

Power transmission system including a lubrication oil recovery device and turbomachine provided with such a power transmission system

The present invention relates to a method for dimensioning a turbomachine comprising a casing and a disc to which at least one blade is secured, said disc being rotationally driven by a shaft about a turbomachine axis (z), comprising: &#x2014;acquisition (E) of the coordinates (P) of the ends of the leading edge and of the trailing edge of the blade in a frame of reference connected with the disc; &#x2014;expression (E) of the coordinates (P') of the ends of the leading edge and of the trailing edge of the blade in a frame of reference connected with the casing; &#x2014;calculation (E) of the distance (g) between the casing and the ends of the leading edge and trailing edge of the blade from the coordinates (P&#x2032;) expressed in the frame of reference connected with the casing; &#x2014;calculation (E) of the contact pressures between the blade and the casing along the end of the blade from the calculated distance (g); &#x2014;calculation (E) of the reaction forces and moments resulting from contact between the blade and the casing from the calculated pressures; &#x2014;dimensioning (E) of the turbomachine as a function of the calculated distances, pressures, forces and moments.

Method for dimensioning a turbomachine

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Paris, France

Fabrice Joel Luc Chevillot