US 12,110,842 B2
Air outlet for a nacelle for an aircraft bypass turbojet engine comprising a guiding device to favor a reverse thrust phase
Eva Julie Lebeault, Moissy-Cramayel (FR); and Daniel-Ciprian Mincu, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/905,055
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Mar. 2, 2021, PCT No. PCT/EP2021/055103
§ 371(c)(1), (2) Date Aug. 25, 2022,
PCT Pub. No. WO2021/180509, PCT Pub. Date Sep. 16, 2021.
Claims priority of application No. 2002285 (FR), filed on Mar. 9, 2020.
Prior Publication US 2023/0090029 A1, Mar. 23, 2023
Int. Cl. F02K 1/66 (2006.01); F02K 1/72 (2006.01); F02K 3/04 (2006.01)
CPC F02K 1/66 (2013.01) [F02K 1/72 (2013.01); F02K 3/04 (2013.01); F05D 2260/70 (2013.01)] 15 Claims
OG exemplary drawing
 
1. An aircraft propulsion assembly comprising:
an aircraft bypass turbojet engine comprising a primary radially inner flow path and a secondary radially outer flow path in which a secondary air flow circulates from upstream to downstream during a thrust phase and a reverse air flow from downstream to upstream during a reverse thrust phase, a nacelle mounted on the turbojet engine and extending around the longitudinal axis of said turbojet engine, said turbojet engine comprising a plurality of guide vanes extending radially into the secondary flow path, said nacelle comprising an air outlet at a downstream end, said air outlet comprising a downstream inner wall, turned towards the longitudinal axis and configured to delimit externally the secondary flow path and to guide the secondary air flow and the reverse air flow, and a downstream outer wall, opposite to the downstream inner wall and 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, wherein said air outlet comprises:
a plurality of radial through apertures spread out on a circumference of said air outlet, each radial through aperture extending onto an angular portion of said air outlet along a transversal plane situated upstream of said trailing edge, each radial through aperture comprising an inner open face having an upstream edge and a downstream edge formed in said downstream inner wall and an outer open face having an upstream edge and a downstream edge formed in said downstream outer wall, each radial through aperture being axially positioned at a location between said guide vanes and said trailing edge and delimited by said upstream edges and said downstream edges, and
each radial through aperture having a single guiding device comprising a single inner moveable member and a single outer moveable member mounted, respectively, at said inner open face and said outer open face and are moveable between:
a closed position in which the inner moveable member closes off said inner open face of said downstream inner wall and the outer moveable member closes off said outer open face of said downstream outer wall, said radial through aperture defining a closed cavity delimited by said inner moveable member and said outer moveable member to conserve performances in the thrust phase,
an open position in which said inner moveable member and said outer moveable member are configured to allow said outer air flow in said radial through aperture from said outer open face to said inner open face to increase the reverse air flow admitted into the secondary flow path, to favor a reverse thrust phase; and
wherein said inner moveable member of said single guiding device is pivotally mounted along a pivoting axis tangential to said air outlet,
wherein said single guiding device comprises a displacement member for displacing the inner moveable member and the outer moveable member between the closed position and the open position, the displacement member being positioned upstream of the radial through aperture.