Abstract: An aircraft comprising a fuselage and a propulsion assembly, the propulsion assembly comprising at least one fan rotor located at the rear of the fuselage in the extension thereof along a longitudinal axis, and a nacelle forming a fairing of the at least one fan rotor into which a flow of air passes. The aircraft also comprises a plurality of radial stator arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle, the radial arms comprising blowing means configured for blowing, into the environment of a trailing edge of the radial arms, an additional air flow adding to the airflow in the extension of the trailing edge.

Abstract: An aircraft comprising a fuselage and a propulsion assembly, the propulsion assembly comprising at least one fan rotor located at the rear of the fuselage in the extension thereof along a longitudinal axis, and a nacelle forming a fairing of the at least one fan rotor into which a flow of air passes. The aircraft also comprises a plurality of radial stator arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle, the radial arms comprising blowing means configured for blowing, into the environment of a trailing edge of the radial arms, an additional air flow adding to the airflow in the extension of the trailing edge.

Abstract: A nacelle structure (10) surrounding a fan, the structure comprising an air inlet (100) having an inside surface (100A) defining an air feed channel; and at least one ring (22) arranged in the air inlet and selectively movable between a deployed position in which the ring is moved radially inwards from the inside surface to provide an obstacle to shock waves coming from the fan, and a retracted position in which the ring is moved radially outwards from the deployed position so as to become flush with the inside surface and thus reconstitute the air feed channel.

Abstract: A casing for a blisk of a turbomachine including an internal coating made of an abradable material, and a plurality of circumferential slots arranged in the coating of abradable material, the casing further including a circumferential cavity formed in the coating of abradable material, into which cavity the slots open, the slots opening into the cavity and extending between the cavity and an internal surface of the casing. A turbomachine can include such a casing and a blisk.

Abstract: A nacelle structure (10) surrounding a fan, the structure comprising an air inlet (100) having an inside surface (100A) defining an air feed channel; and at least one ring (22) arranged in the air inlet and selectively movable between a deployed position in which the ring is moved radially inwards from the inside surface to provide an obstacle to shock waves coming from the fan, and a retracted position in which the ring is moved radially outwards from the deployed position so as to become flush with the inside surface and thus reconstitute the air feed channel.

Abstract: A casing for a blisk of a turbomachine including an internal coating made of an abradable material, and a plurality of circumferential slots arranged in the coating of abradable material, the casing further including a circumferential cavity formed in the coating of abradable material, into which cavity the slots open, the slots opening into the cavity and extending between the cavity and an internal surface of the casing. A turbomachine can include such a casing and a blisk.