US 11,913,404 B2
Nacelle air outlet for aircraft turbojet engine comprising a straightening device for facilitating a reverse thrust phase
Philippe Gérard Chanez, Moissy-Cramayel (FR); and Daniel-Ciprian Mincu, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/758,650
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jan. 14, 2021, PCT No. PCT/EP2021/050736
§ 371(c)(1), (2) Date Jul. 12, 2022,
PCT Pub. No. WO2021/156036, PCT Pub. Date Aug. 12, 2021.
Claims priority of application No. 2001026 (FR), filed on Feb. 3, 2020.
Prior Publication US 2023/0038787 A1, Feb. 9, 2023
Int. Cl. F02K 1/66 (2006.01); B64D 27/16 (2006.01); B64D 29/00 (2006.01); F02K 1/32 (2006.01)
CPC F02K 1/32 (2013.01) [B64D 27/16 (2013.01); B64D 29/00 (2013.01); F02K 1/66 (2013.01)] 19 Claims
OG exemplary drawing
 
1. 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 nacelle forming a revolution around the longitudinal axis of the bypass turbojet engine, 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 the trailing edge, each flap of the plurality of flaps being mounted along a pivoting axis 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.