Abstract: This invention relates to a double-flow turboshaft engine with confluent nozzle, i.e. of the type having a central generator emitting via its outlet orifice a flow of hot gas and an annular bypass duct which surrounds the central generator and through which passes a bypass flow of relatively cold gas, the gas flows being freely confluent within the nozzle which extends the annular duct in convergent manner beyond the outlet orifice of the central generator, wherein it includes controlled means for momentarily varying on the periphery the passage of the flux of relatively cold gas in the annular bypass duct, with a view to compensating, at least partly, the degradation of the performances of the turboshaft engine when they are limited either by the maximum operational temperature of the central generator or by the maximum power of the engine, but not by these two conditions simultaneously.

Abstract: This invention relates to a thrust reverser for aircraft jet engine having at least one door mounted to the downstream end of the jet generator to pivot about an axis which is transverse and at least substantially diametral to said jet, the door being able to pivot between a retracted position and an extended position. According to the invention, an at least partially supple seal is provided between the opposite parts of the inner and outer surfaces, respectively, of the door and of the jet generator, the transverse section of the seal being continually adapted to the space between the door and the jet generator in retracted position of the door.