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AssigneeSafran Aircraft Engines
InventorsPhilippe Gerard Chanez, Mathieu Patrick Jean-Louis Lallia, Christian Sylvain Vessot
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The invention relates to an aircraft propulsion assembly (10), comprising a single gas generator (11) and two fans (12) drive in rotation by the gas generator (11) and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane. According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17′) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.
A propulsion assembly for an aircraft, intended to be attached below a wing of said aircraft, the assembly comprising a single gas generator and two fans being each driven in rotation by the gas generator and offset on either side of a vertical plane passing through a longitudinal axis of the gas generator, the rotational axes of the fans lying substantially in the same fan plane, wherein the propulsion assembly comprises an air inlet fairing formed upstream of a nacelle connecting the fans, said fairing having, between the fans, an air inlet opening lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator with a part of the air entering through the air inlet and to take off, from the remaining part of the air entering through the air inlet opening, a cooling airflow intended to cool elements of the propulsion assembly and/or the wing supporting the propulsion assembly.
Dependencies are inferred from the claim text.