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AssigneeSafran Aircraft Engines
InventorsFernando Gea Aguilera, Adrien Clément Marcel Dubois, Jean-Michel Daniel Paul Boiteux, Ludovic Mathieu René Wiart
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Propulsion assembly for an aircraft comprising a turbomachine having at least one rotating part rotating about an axis of rotation, an attachment strut, and a structural element carrying the turbomachine via the attachment strut, the rotating part being disposed upstream of the structural element and of the attachment strut such that an air jet emerging from the rotating part, in the wake of thereof, impacts the structural element and the attachment strut, a leading edge of the structural element and/or of said attachment strut locally comprising at least one acoustic attenuation device disposed at least partly in the wake of the rotating part, the acoustic attenuation device being a local modification of the structure and/or of the profile of the leading edge.
A propulsion assembly for an aircraft comprising a turbomachine having at least one rotating part configured to rotate about an axis of rotation of the turbomachine, an attachment strut, and an aircraft wing carrying the turbomachine via the attachment strut which is intercalated between the aircraft wing and the turbomachine, the at least one rotating part being disposed upstream of the aircraft wing and of the attachment strut such that an air jet emerging from the rotating part, in the wake thereof, impacts said aircraft wing and said attachment strut, a leading edge of said aircraft wing locally comprising at least one acoustic attenuation device disposed at least partly in the wake of the rotating part, the acoustic attenuation device being a local modification of a structure and/or of a profile of the leading edge, and extending over a distance L of the aircraft wing, such that L<2.5D, where D is a diameter of the rotating part of the turbomachine.
A propulsion assembly for an aircraft comprising a turbomachine having at least one rotating part configured to rotate about an axis of rotation of the turbomachine, an attachment strut, and an aircraft airfoil carrying the turbomachine via the attachment strut, the at least one rotating part being disposed upstream of the airfoil and of the attachment strut such that an air jet emerging from the rotating part, in the wake thereof, impacts said airfoil and said attachment strut, a leading edge of said airfoil locally comprising at least one acoustic attenuation device disposed at least partly in the wake of the rotating part, the acoustic attenuation device being a local modification of a structure and/or of a profile of the leading edge, and extending over a distance L of the airfoil, such that L<2.5D, where D is a diameter of the rotating part of the turbomachine, wherein the acoustic attenuation device comprises corrugations along the leading edge, the corrugations having a succession of valleys and peaks, wherein an amplitude h(z) of the corrugations and/or a spacing λ(z) between two successive peaks of the corrugations varies along the leading edge as a function of a distance E, the distance E being a distance between a position z along the leading edge and the rotating part, along a direction parallel to the axis of rotation, wherein the amplitude h(z) of the corrugations is such that 0.005c(z)<h(z)<0.5c(z), c(z) being a value of a chord of the airfoil as a function of a position z along the leading edge.
Dependencies are inferred from the claim text.