Turbomeca

Safran Helicopter Engines

Jean-Philippe Ousty

Pierre Biscay

Lionel Scuiller

Geoffroy Louis-Henri Marie Billotey

Marc Maurice Dijoud

Pascal Pierre Le Brusq

Geoffroy Billotey

Gilles Cazenave-Larroche

Nicolas Rochuon

Geoffroy Louis Billotey

Marc Dijoud

A method to prevent blockage of air passages in curvic couplings between drive parts and to prevent potential damage to the drive parts during weakening of protective elements. To this end, axial abutments are formed by ring gears of the curvic couplings. A coupling includes two rings, each ring being on the end of one drive part and engaged with the other so as to transmit to the drive part a rotation around a central axis while allowing air to pass between male and female portions of the teeth of the rings behind a bearing area. The rings are extended in an at least partially radial manner relative to each other to form an outer ring extension and an inner ring extension respectively facing elements surrounding the drive part that are mounted onto the other ring. The rotor lines can be used in turbine engines.

Method for protecting the passage of air in a drive part coupling in an unprotected environment, coupling for implementation, and rotor line fitted with such couplings

A turbine wheel including: a plurality of first and second blades, at least one of the first blades being adjacent to at least one of the second blades; a disk presenting an axis of rotation and a periphery having the blades mounted thereat, each of the blades including a head solid with a root engaged in a housing that opens to the periphery of the disk, each of the blades including a keying mechanism including a respective shelf arranged between the head and the root of the blade, the shelves of the first blades presenting an azimuth length different from the azimuth length of the shelves of the second blades; and a damper device arranged at least between the adjacent blades, the damper device being arranged between the shelves of the blades and the periphery of the disk.

Turbine wheel having de-tuned blades and including a damper device

A compressor impeller including at least one blade connected to an impeller hub via a junction of curved shape, the blade extending along a defined chord between a leading edge and a trailing edge of the blade. The junction presents the shape of an ellipse that varies along the chord.

Compressor impeller blade with variable elliptic connection

Growing community of inventors

Soumoulou, France

Jean-Philippe Ousty