Safran Aircraft Engines

Snecma

Onera

Laurence Francine Vion

Adrien Jacques Philippe Fabre

Norman Bruno André Jodet

Mathieu Simon Paul Gruber

Anthony Binder

Jonathan Evert Vlastuin

Sébastien Emile Philippe Tajan

Adrien Louis Nicolas Laurenceau

Rasika Fernando

Gregory Delattre

Laurent Jacquin

Benoit Rodriguez

Ronan Boisard

Biel Ortun

Fabrice Falissard

Adrien Dubois

Norman Bruno Jodet

Mathieu Simon Gruber

Grégory Delattre

The invention relates to a nubomachine with a longitudinal axis, comprising two, respectively upstream () and downstream, coaxial outer propellers (), characterised in that at least some of the blades () of the upstream propeller () comprise at least one internal air circulation chimney () that communicates with air-bleeding openings () in tire boundary layers of the blades (), and communicates with air outflow openings () on the radially outer end thereof, the air-bleeding openings () leading to opening inlets () on tire passive surfaces () of the blades (), the inlets () of the air-bleeding openings being radially arranged in an area (H) contained between 10% and 45% of the radial dimension (H) of the blades (), measured above turd from the radial height of the blades for which the tangent of the leading edge () of the blades is orthogonal to the longitudinal axis, and the inlets () of the air bleeding openings being arranged in an area contained between 0% and 30% of the local chord of the blades (), measured at the level of said inlets () and from the leading edges () of tire blades ().

Turbomachine with coaxial propellers

The invention relates to an unducted-fan aircraft engine comprising a generally cylindrical nacelle through which a primary jet flows, the nacelle bearing a fan rotor comprising variable-pitch vanes () located radially outside the nacelle in order to be traversed by a secondary jet () flowing longitudinally around the nacelle. The rotor comprises a hub bearing variable-pitch vane supports each carrying one vane (), each vane () comprising a blade extending from a root that is used to removably attach same to a base of the associated support (). Each base () is located radially outside the nacelle so that it is in the secondary jet, and each assembly formed by a base () and the vane root supported by the base () is surrounded and covered by a detachable aerodynamic cover ().

Unducted-fan aircraft engine including a propeller comprising vanes with roots outside the nacelle and covered by detachable covers

A turbomachine including at least two unducted propellers, one of which is an upstream propeller and one a downstream propeller, the upstream propeller including a plurality of blades, at least one first blade of which has a different length from that of a second blade.

Turbomachine with multi-diameter propeller

A blade for a turbine engine propeller, in particular a propfan engine, comprising a protruding part on the leading edge thereof, wherein said blade comprises means for controlling the position of the protruding part along the leading edge thereof.

Blade for a turbine engine propeller, in particular a propfan engine, propeller, and turbine engine comprising such a blade

A blade for a fan of a turbomachine, for example of unducted fan type, a corresponding fan, and a corresponding turbomachine. The blade includes a mechanism arranged, at a single location, to locally, as the fan rotates, disturb a distribution of flow around the blade so as to form two independent main vortices downstream.

Blade for a fan of a turbomachine, notably of the unducted fan type, corresponding fan and corresponding turbomachine

Growing community of inventors

Moissy-Cramayel, France

Laurence Francine Vion