Propulsive assembly for aircraft

The subject of the invention is a propulsive assembly (8) for an aircraft. The propulsive assembly comprises an engine (16), a nacelle (18) arranged around the engine and a pylon (12) supporting the engine, the nacelle including two engine cowls (19) and reversing cowls (21), each cowl (19, 21) having an internal skin (23), characterized in that at least one of the cowls of the nacelle comprises at least one box (42) arranged in a space situated between the internal skin of the cowl and the engine, the box delimiting a volume of inert material, the inert material being flame retardant foam. The box partially blocks a zone of the engine where a fire is likely to begin, which makes it possible to limit the volume of a fire zone of the engine, and thus reduce the quantity of extinguishing agent which is necessary to extinguish a fire in the zone of the engine concerned. 本发明主题是一种飞行器的推进组件(8)，所述推进组件包括发动机(16)、短舱(18)以及吊挂架(12)，所述短舱布置在所述发动机周围，所述吊挂架支撑所述发动机，所述短舱包括两个发动机整流罩(19)以及反向整流罩(21)，每个整流罩(19，21)具有内部蒙皮(23)，其特征在于，所述短舱的