Snecma

Safran Aircraft Engines

Emmanuel Da Costa

Alain Dominique Gendraud

Philippe Pierre Vincent Bouiller

Renaud James Martet

Eddy Stephane Joel Fontanel

Giuliana Elisa Rossi

Eddy Stéphane Joël Fontanel

Julien Foll

Josselin Sicard

Bruno Andre Jean Varin

Eddy Stephane Fontanel

Philippe Bouiller

Renaud Martet

Bruno André Jean Varin

A journal configured to be driven in rotation in a housing of a turbine engine, or for an aircraft, the journal including: a circumferential main body including plural ventilation openings configured to allow plural axial airflows to circulate from upstream to downstream in the turbine engine, two consecutive ventilation openings being connected by a connecting segment, and a circumferential ring for recovering a flow of lubrication oil, which ring is rigidly connected to the main body and is radially inside the ventilation openings, the circumferential ring including plural radial discharge openings for allowing plural radial flows of oil to be discharged towards the outside, each discharge opening being radially aligned with a connecting segment of the main body to allow each flow of oil to be discharged radially between the airflows.

Journal for a turbine engine comprising a ring for recovering a flow of lubricating oil with a plurality of lubricating oil discharge ports

A turbomachine assembly in which a foil is configured to cover mainly one of bulbs of a disc and to be held, radially with respect to the disc, by the bulb of the disc and a pocket for a blade that can collaborate therewith, when these two are effectively collaborating, and the bulb of the disc includes at least one longitudinal cavity configured to form, with the foil, when the foil is covering the bulb of the disc, a secondary passage through which a secondary cooling air flow can pass.

Cooling for the retaining dovetail of a turbomachine blade

Growing community of inventors

Saint Maur des Fosses, France

Emmanuel Da Costa