Patent ID: 8602360

Claim:
An aircraft nacelle comprising: a first pipe ( 32 ), a peripheral wall ( 34 ), a lip ( 36 ) oriented toward a front of the aircraft nacelle that connects to said first pipe ( 32 ) at a point B and said peripheral wall ( 34 ) at a point A and that delimits an air intake, as well as a frost treatment system that treats a zone that extends along a longitudinal section of the point A that is provided at the peripheral wall ( 34 ) at the point B that is provided at the first pipe ( 32 ), and a front frame ( 38 ) that delimits with said lip ( 36 ) a second pipe ( 51 ) in which the hot air for de-icing circulates, wherein said first pipe ( 32 ) comprises a coating ( 44 ) for the acoustic treatment, comprising, from the inside to the outside, a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure, wherein the front frame ( 38 ) comprises a junction zone with at least one of the lip ( 36 ) and the first pipe ( 32 ) that is offset toward the front of the aircraft nacelle relative to point B, wherein third pipes ( 50 ) are provided at the inside surface of the lip ( 36 ) and the pipe ( 32 ) for conveying the hot air from said second pipe ( 51 ) for hot air up to discharges that are arranged at a circle that corresponds to point B, wherein said third pipes ( 50 ) extend beyond the junction zone between the front frame ( 38 ), and at least one of the lip ( 36 ) and the first pipe ( 32 ) and are delimited by at least one partition that isolates the hot air from a coating ( 44 ) for the acoustic treatment.