Abstract: The invention relates to a variable-section flow mixer for a double-flow turbojet for a supersonic airplane, the mixer comprising a central body, a primary cover, a secondary cover, and a nozzle extending the secondary cover. The nozzle has a plurality of external-air admission openings having mounted therein lobes that are movable between two positions: a closed position in which they close the openings; and a deployed position in which they disengage said openings and deploy into the nozzle so as to allow external air to be admitted. All of the lobes present a common azimuth component in a common direction, and the mixer further includes a plurality of longitudinal grooves occupying at least a portion of the central body, all of the grooves presenting a common azimuth component in a common direction that is opposite to the direction of the azimuth component of the lobes.

Abstract: The invention relates to a mixer for a bypass turbomachine, the mixer comprising a member having a sinusoidal portion at its end defining inner lobes and outer lobes, each outer lobe comprising a pair of plane radial walls spaced apart from each other in the circumferential direction and interconnected by an outer dome, each inner lobe comprising a pair of plane radial walls spaced apart from each other in the circumferential direction and connected together by an inner dome, the walls of the outer lobes being disposed to extend the walls of the inner lobes radially, the radial walls of a given outer lobe extending radially in mutually parallel directions, with these walls, when extended geometrically, defining a zone from which the axis of symmetry of the cylindrical member is excluded.

Abstract: The invention relates to a variable-section flow mixer for a double-flow turbojet for a supersonic airplane, the mixer comprising a central body, a primary cover, a secondary cover, and a nozzle extending the secondary cover. The nozzle has a plurality of external-air admission openings having mounted therein lobes that are movable between two positions: a closed position in which they close the openings; and a deployed position in which they disengage said openings and deploy into the nozzle so as to allow external air to be admitted. All of the lobes present a common azimuth component in a common direction, and the mixer further includes a plurality of longitudinal grooves occupying at least a portion of the central body, all of the grooves presenting a common azimuth component in a common direction that is opposite to the direction of the azimuth component of the lobes.

Abstract: The invention relates to a mixer for a bypass turbomachine, the mixer comprising a member having a sinusoidal portion at its end defining inner lobes and outer lobes, each outer lobe comprising a pair of plane radial walls spaced apart from each other in the circumferential direction and interconnected by an outer dome, each inner lobe comprising a pair of plane radial walls spaced apart from each other in the circumferential direction and connected together by an inner dome, the walls of the outer lobes being disposed to extend the walls of the inner lobes radially, the radial walls of a given outer lobe extending radially in mutually parallel directions, with these walls, when extended geometrically, defining a zone from which the axis of symmetry of the cylindrical member is excluded.