Patent ID: 8827199

Claim:
A pylon supporting a turboshaft engine on an aircraft, the pylon longitudinally extending from upstream to downstream and comprising: an upper securing part for securing to the aircraft and a lower securing part for securing to the turboshaft engine, the upper securing part to the aircraft being downstream from the lower securing part to the turboshaft engine; and an absorption part configured to extend in an exhaust stream of the turboshaft engine, located downstream from the lower securing part to the turboshaft engine and located bottomly with respect to the upper securing part to the aircraft, wherein the absorption part comprises an internal part upstream of an exhaust plane of the turboshaft engine and extending inside the turboshaft engine, and an external part downstream of the exhaust plane of the turboshaft engine, the internal part including a main securing zone and a secondary securing zone, and wherein an outer surface of a downstream end of the external part of the absorption part is covered with a porous material arranged to reduce intensity of acoustic waves at an outlet of the turboshaft engine.