PROPULSION SYSTEM FOR AN AIRCRAFT

Abstract: an aeronautical thruster of longitudinal axis includes a hub, an annular row of unducted upstream rotor blades, and an annular row of unducted downstream stator blades. the annular row of downstream stator blades includes at least one downstream stator blade of a first type, each of which is located about the longitudinal axis in a first angular sector about the longitudinal axis. each downstream stator blade of the first type has a fixed pitch. the annular row of downstream blades further includes at least one downstream stator blade of a second type, each of which is located about the longitudinal axis outside said first angular sector, wherein each downstream stator blade of the second type has a variable pitch.

Inventor(s): Eva Julie LEBEAULT, Fernando GEA AGUILERA, Anthony BINDER, Clément COTTET

CPC Classification: F04D29/544 (NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps ; ion pumps ; electrodynamic pumps ))

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