Abstract: The invention relates to an arrangement, in a pod of an aircraft propulsion assembly, for drawing in air and trapping foreign bodies. Said arrangement includes a main air inlet duct (11) separating into, on one hand, a channel (13) for leading air to a compressor and, on the other hand, a bypass channel (12) capable of trapping foreign bodies (5) that enter said main duct (11). Said arrangement comprises a heat exchanger (6) that extends along a section of the bypass channel (12). Said heat exchanger (6) carries out surface heat exchange along said section and is coupled with an external oil system in order to cool the oil thereof by heat exchange with the air (4) flowing in the bypass channel (12). Said bypass channel (12) has an air outlet (12a) acting as a means for discharging the foreign bodies (5).

Abstract: A turbine engine nozzle having confluent streams, the nozzle including a core cowl arranged around an annular central body and co-operating therewith to define a core annular channel for passing a flow of a core stream, the core stream on entry into the nozzle possessing an azimuth component driving residual gyratory movement of the core stream in two opposite gyratory flow directions corresponding to two operating speeds of the engine, the core cowl having an annular upstream portion that is extended downstream by an annular terminal portion having longitudinal cuts forming a plurality of flaps that overlap radially in pairs via their respective side edges in such a manner that, for each flap, one of the two side edges of the flap is positioned internally relative to the corresponding side edge of one of the adjacent flaps, while the other side edge of the flap is positioned externally relative to the corresponding side edge of the other adjacent flap.

Abstract: The invention relates to an arrangement, in a pod of an aircraft propulsion assembly, for drawing in air and trapping foreign bodies. Said arrangement includes a main air inlet duct (11) separating into, on one hand, a channel (13) for leading air to a compressor and, on the other hand, a bypass channel (12) capable of trapping foreign bodies (5) that enter said main duct (11). Said arrangement comprises a heat exchanger (6) that extends along a section of the bypass channel (12). Said heat exchanger (6) carries out surface heat exchange along said section and is coupled with an external oil system in order to cool the oil thereof by heat exchange with the air (4) flowing in the bypass channel (12). Said bypass channel (12) has an air outlet (12a) acting as a means for discharging the foreign bodies (5).

Abstract: A turbine engine nozzle having confluent streams, the nozzle including a core cowl arranged around an annular central body and co-operating therewith to define a core annular channel for passing a flow of a core stream, the core stream on entry into the nozzle possessing an azimuth component driving residual gyratory movement of the core stream in two opposite gyratory flow directions corresponding to two operating speeds of the engine, the core cowl having an annular upstream portion that is extended downstream by an annular terminal portion having longitudinal cuts forming a plurality of flaps that overlap radially in pairs via their respective side edges in such a manner that, for each flap, one of the two side edges of the flap is positioned internally relative to the corresponding side edge of one of the adjacent flaps, while the other side edge of the flap is positioned externally relative to the corresponding side edge of the other adjacent flap.