Safran Aircraft Engines

Matthieu Pierre Michel Dubosc

Gilles Alain Marie Charier

Nathalie Nowakowski

Kevin Morgane Lemarchand

Guillaume Pascal Jean-Charles Gondre

Nicolas Jérôme Jean Tantot

Olivier Bazot

Benjamin Bulot

Dominique Gerhardt Mayhew

A blade for a ducted fan of a turbomachine includes an airfoil formed of plural airfoil sections stacked along an airfoil axis. A difference in sweep corresponding to a difference between a leading edge sweep and a trailing edge sweep of an airfoil section is substantially identical for any airfoil section having a height of between 10% and 20% of an airfoil height of the airfoil, and/or substantially identical for any airfoil section having a height of between 75% and 90% of the airfoil height.

Blade for a ducted fan of a turbomachine

A blade for an unducted fan of a turbomachine includes an airfoil formed of plural airfoil sections that are stacked along an airfoil axis. A difference in sweeps corresponding to a difference between a leading edge sweep and a trailing edge sweep is negative, and substantially between −30° and 0°, for any airfoil section whose height is between 10% and 30% of an airfoil height of the airfoil, and is positive, and substantially between 0° and +40°, for any airfoil section whose height is between 50% and 90% of the airfoil height.

Blade for an unducted fan of a turbomachine

A method for manufacturing a blade from composite material having an added metal leading edge for a gas turbine aeroengine includes producing a blade body from composite material including a blade root part, a shank part and an airfoil body part; manufacturing, via additive manufacturing, a leading edge extending in a longitudinal direction between a lower end present at the shank part of the composite material and an upper end present at the tip; bonding the manufactured leading edge onto the foremost edge portion of the airfoil body of the blade body.

Blade made of composite material with variable-density attached leading edge

A turbomachine comprising a ducted fan, a low-pressure turbine shaft and a reduction gearbox housed in a casing between the fan and the low-pressure turbine shaft, the fan rotor supplying airflow to a primary stream and a secondary stream and comprising a hub of diameter D, wherein&#x2014;the diameter Dof the fan rotor is greater than 82 inches (2.08 metres), &#x2014;the pressure ratio of the fan is between 1.10 and 1.35, the turbomachine comprises a low-pressure compressor separate from the fan, the reduction gearbox being interposed between the fan rotor and a turbine shaft of the low-pressure compressor, and wherein the reduction gearbox casing has an outside diameter Dgreater than the diameter Dof the hub, the pitch diameter Dof the reduction gearbox ring being between 0.15 and 0.35 times the fan rotor diameter.

Turbomachine with fan rotor and reduction gearbox driving a low-pressure decompressor shaft

The invention relates to an assembly of turbine engine () parts having a longitudinal axis (X), the assembly comprising at least two adjacent fan blades made of a 3D woven composite material, each blade () comprising a root (), a vane () extending from the root (), and an integrated platform () inserted between the root () and the vane (), the platform () extending on either side of the vane () and forming a pressure face platform portion (I) and a suction face platform portion (E), the pressure face and suction face platform portions of adjacent blades being connected by a fin () extending at least radially at the outer side of the pressure face and suction face platform portions (I,E), relative to the longitudinal axis (X), having a substantially triangular transverse cross section and extending axially and so as to upper overlap the longitudinal edges (A,B) of the pressure face and suction face platform portions (I,E) of the adjacent blades.

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Paris, France

Matthieu Pierre Michel Dubosc