Turboshaft engine with reduced noise emission for aircraft
According to the invention, a plurality of embossments ( 20 ) having a rectangular section is provided at the inner periphery of the outlet opening ( 7 ) of the fan duct ( 12 ), said embossments being separated by longitudinal channels ( 21 ) having a convergent ( 22 C) and a divergent ( 22 D) for the cold flow ( 9 ).
1. A bypass turbojet engine for an aircraft, comprising, around its longitudinal axis (L-L):
a nacelle ( 2 ) provided with a nacelle outer cowl ( 3 ) and containing a fan ( 8 ) generating the cold flow ( 9 ) and a central generator ( 10 ) generating the hot flow ( 11 );
an annular cold flow duct ( 12 ) created around said central hot flow generator ( 10 );
a fan outer cowl ( 14 ) delimiting said annular cold flow duct ( 12 ) on said nacelle outer cowl ( 3 ) side;
a cold flow outlet orifice ( 6 ) of which the edge ( 7 ), which forms the trailing edge of said nacelle ( 2 ), is determined by said nacelle outer cowl ( 3 ) and by said fan outer cowl ( 14 ) converging toward one another until they meet; and
in the vicinity of said cold flow outlet orifice ( 6 ), a plurality of bosses ( 20 ) distributed at the periphery of said fan outer cowl ( 14 ), projecting into said annular cold flow duct ( 12 ) and forming, for said cold flow ( 9 ), a convergent face portion followed by a divergent face portion connected to the edge ( 7 ) of said cold flow outlet orifice ( 6 ),
wherein each boss ( 20 ) has a convex face ( 22 ) forming said convergent face portion ( 22 C) and said divergent face portion ( 22 D) and two planar lateral faces ( 20 L), which run longitudinally with respect to said turbojet engine, said convex face ( 22 ) and said lateral faces ( 20 L) giving said boss ( 20 ) an at least approximately rectangular cross section that evolves in a direction parallel to said longitudinal axis (L-L),
wherein a peripheral width (l 20 ) of the bosses ( 20 ) is equal to a peripheral width (l 21 ) of a plurality of longitudinal ducts ( 21 ) delimited between the bosses ( 20 ).
2. The turbojet engine as claimed in claim 1 , wherein said bosses ( 20 ) are uniformly distributed at the periphery of said fan outer cowl ( 14 ).
3. The turbojet engine as claimed in claim 1 , wherein said bosses ( 20 ) are components that are added on and attached to said outer fan cowl ( 14 ).