An air intake for an aircraft propulsion assembly extending along a longitudinal axis and comprising a turbine engine that comprises a primary flow path and a secondary flow path for respectively guiding a primary air flow and a secondary air flow during a thrust, and thrust reversal means for changing the secondary airflow into a reverse airflow during a thrust reversal. The air intake comprising a peripheral external enclosure comprising, in each plane radial to the axis, a point of maximum curvature for detaching the reverse airflow, an osculating circle defining a radius of curvature that is defined at each of the points of maximum curvature. The average value of the radii of curvature being less than a product of 0.028 times an internal radius of the intake at the fan.
ENTRÉE D'AIR DE NACELLE D'ENSEMBLE PROPULSIF D'AÉRONEF POUR FAVORISER UNE PHASE D'INVERSION DE POUSSÉE
NACELLE AIR INTAKE FOR AN AIRCRAFT PROPULSION ASSEMBLY TO PROMOTE A THRUST REVERSAL PHASE
GONDELLUFTEINLASS FÜR EINE FLUGZEUGANTRIEBSANORDNUNG ZUR FÖRDERUNG EINER SCHUBUMKEHRPHASE
2025-06-04
Patent
Electronic Resource
French
European Patent Office | 2022
|European Patent Office | 2023
|European Patent Office | 2020
|European Patent Office | 2020
|European Patent Office | 2023
|