Patent ID: 11913404
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B  Y | IPC B  F

Claim 17:
18. An air outlet of a nacelle for a bypass turbojet engine having a bypass turbojet engine extending along a longitudinal axis and comprising a radially inner primary flow path and a radially outer secondary flow path wherein a secondary air flow circulates from upstream to downstream during a thrust phase and a reverse air flow from downstream to upstream circulates during a reverse thrust phase, said air outlet comprising (1) a downstream inner wall that is turned towards the longitudinal axis and configured to externally delimit the secondary flow path and to guide the secondary air flow and the reverse air flow, (2) a downstream outer wall, opposite to the downstream inner wall, configured to guide an outer air flow circulating from upstream to downstream, said downstream inner wall and said downstream outer wall being connected together downstream by a trailing edge, and (3) a straightening device comprising a plurality of flaps mounted on the trailing edge and projecting downstream from a trailing edge, each flap of the plurality of flaps being mounted along a pivoting axis having a structure with a diameter greater than 10 mm to support the plurality of flaps due to turbulence of external air flow and forming, with respect to the longitudinal axis, an angle of convergence of between 0° and 45° in a radial plane, and wherein each flap being pivotably mounted between:
a closed position, wherein each flap extends along the pivoting axis in an aerodynamic extension of the trailing edge to facilitate the thrust phase, and
a deployed position, wherein each flap extends in a deployed plane forming an angle of deployment with respect to the closed position around the pivoting axis, said angle of deployment being greater than 20° to straighten the reverse air flow admitted into said air outlet so as to facilitate the reverse thrust phase.