US 12,344,376 B2
Nacelle air intake for an aircraft propulsion assembly to promote a thrust reversal phase
Yacine Cheraga, Moissy-Cramayel (FR); Daniel-Ciprian Mincu, Moissy-Cramayel (FR); Philippe Gérard Chanez, Moissy-Cramayel (FR); and Jean-Loïc Hervé Lecordix, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/250,914
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Oct. 28, 2021, PCT No. PCT/EP2021/079953
§ 371(c)(1), (2) Date Apr. 27, 2023,
PCT Pub. No. WO2022/096359, PCT Pub. Date May 12, 2022.
Claims priority of application No. 2011473 (FR), filed on Nov. 9, 2020.
Prior Publication US 2024/0002036 A1, Jan. 4, 2024
Int. Cl. B64C 7/02 (2006.01); B64D 29/00 (2006.01); B64D 33/02 (2006.01); F02C 7/04 (2006.01); F02C 7/042 (2006.01)
CPC B64C 7/02 (2013.01) [B64D 29/00 (2013.01); B64D 33/02 (2013.01); F02C 7/04 (2013.01); F02C 7/042 (2013.01); B64D 2033/0226 (2013.01); B64D 2033/0286 (2013.01)] 16 Claims
OG exemplary drawing
 
1. An assembly of a nacelle, air intake, and of a fan of a turbine engine of an aircraft propulsion assembly, said aircraft propulsion assembly extending along a longitudinal axis oriented from upstream to downstream and comprising the turbine engine defining a radially inner primary flow path and a radially outer secondary flow path configured to guide from upstream to downstream, respectively, a primary air flow and a secondary air flow during a thrust phase, said turbine engine comprising the fan rotatably mounted about the longitudinal axis, said aircraft propulsion assembly comprising thrust reversal means configured to modify the secondary air flow into a reverse airflow circulating from downstream to upstream in the secondary flow path during a thrust reversal phase, said fan comprising a plurality of variable-pitch blades so as to form the thrust reversal means of the aircraft propulsion assembly, said nacelle extending outwardly around the turbine engine and comprising at its upstream end the air intake, said air intake extending outwardly around the fan, said air intake comprising a peripheral external enclosure of the longitudinal axis comprising an inner wall turned towards the longitudinal axis and an outer wall opposite the inner wall which are connected upstream by an air intake lip comprising a leading edge to promote the thrust phase, said air intake comprising an inner radius at the fan, said peripheral external enclosure comprising a variable curvature in a plane radial to the longitudinal axis, wherein:
a profile of the air intake is stationary and non-deformable, so that the profile remains unchanged between the thrust phase and the thrust reversal phase, and
the peripheral external enclosure comprises, in each radial plane, a point of maximum curvature so as to detach the reverse airflow from the peripheral external enclosure in order to promote the thrust reversal phase, an osculating circle comprising a radius of curvature being defined at each of the points of maximum curvature, an average value of the radii of curvature at the periphery of the air intake being less than a product of 0.028 times the inner radius of the air intake at the fan.