US 12,140,107 B2
Thrust reverser for the nacelle of an aircraft turbofan engine
Sebastien Laurent Marie Pascal, Moissy-Cramayel (FR); and Luigi Bisanti, Moissy-Cramayel (FR)
Assigned to SAFRAN NACELLES, Gonfreville-l'Orcher (FR)
Appl. No. 18/556,312
Filed by SAFRAN NACELLES, Gonfreville-l'Orcher (FR)
PCT Filed Apr. 27, 2022, PCT No. PCT/FR2022/050797
§ 371(c)(1), (2) Date Oct. 19, 2023,
PCT Pub. No. WO2022/229556, PCT Pub. Date Nov. 3, 2022.
Claims priority of application No. 2104530 (FR), filed on Apr. 30, 2021.
Prior Publication US 2024/0209813 A1, Jun. 27, 2024
Int. Cl. F02K 1/72 (2006.01); F02K 1/76 (2006.01); F02K 1/80 (2006.01)
CPC F02K 1/72 (2013.01) [F02K 1/763 (2013.01); F02K 1/805 (2013.01); F05D 2240/55 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A thrust reverser for a nacelle of an aircraft turbofan engine, the thrust reverser having a generally annular shape about an axis and comprising:
a stationary upstream annular structure which extends around an annular duct for a secondary flow,
deflection grids distributed around the axis,
at least one annular cover movable in axial translation relative to the stationary structure, from an upstream position in which the grids are covered, to a downstream thrust-reversal position in which the grids are uncovered, the cover comprising an upstream annular segment and a downstream annular segment,
fairings carried by the cover, these fairings being distributed around the axis, each of the fairings extending inside and at a distance from the upstream segment of the cover and comprising a downstream base connected to an upstream end of the downstream annular segment of the cover, an upstream tip, and two lateral edges connecting the tip to the base,
deflection flaps for deflecting the secondary flow through the grids, the flaps being distributed around the axis and mounted between the fairings, the flaps being movable from a first position in which the flaps extend inside and at a second distance from the upstream segment of the cover and in an extension of the adjacent fairings of the fairings, when the cover is in the upstream position, and a second position in which the flaps extend into the duct to deflect the secondary flow, when the cover is in the downstream position, each of the flaps comprising:
an upstream edge designed to be flush with said upstream structure in the first position,
a downstream edge intended to be flush with the upstream end of the downstream segment of the cover in the first position, and
lateral edges each comprising two portions, respectively an upstream portion and a downstream portion, the upstream portions of the lateral edges of the flaps being flush with the upstream portions of the lateral edges of adjacent flaps in the first position, and the downstream portions of the lateral edges of the flaps being flush with the lateral edges of the fairings in the first position, and flush with the downstream portions of the lateral edges of the flaps in the second position,
and a moving device for moving the cover and the flaps,
wherein each of the flaps comprises a rigid wall extending as far as each of the upstream edge, the downstream edge, and the lateral edges of the respective flap, and defining each of the upstream edge, the downstream edge, and the lateral edges of the respective flap, the wall comprising an aerodynamic internal face and an external face facing the upstream segment of the cover in the first position,
and in that the reverser further comprises:
first sealing elements located on the external face of the wall of each of the flaps and/or on an external face of each of the fairings, the first sealing elements extending along the lateral edges of the flaps and/or of the lateral edges of the fairings so as to provide a sealing along the lateral edges of the flaps and the lateral edges of the fairings in the first position.