Safran Aircraft Engines

Yacine Cheraga

Daniel-Ciprian Mincu

Francois Marie Paul Marlin

Philippe Gérard Chanez

Kaelig Merwen Orieux

Jean-Loïc Hervé Lecordix

Frederic Jacques Eugene Goupil

Philippe Verseux

An air intake for an aircraft propulsion assembly extending along a longitudinal axis and including a turbine engine that includes 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 for changing the secondary airflow into a reverse airflow during a thrust reversal. The air intake including a peripheral external enclosure including, 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 air intake at the fan.

Nacelle air intake for an aircraft propulsion assembly to promote a thrust reversal phase

An air inlet of a nacelle of an aircraft propulsion assembly assembly comprising an inner wall and an outer wall which are connected upstream by an air inlet lip. The air inlet lip comprising thick portions and thin portions distributed alternately over the circumference of the air inlet lip. Each thick portion comprising an upstream leading edge to separate an upstream air flow into an outer air flow guided by the outer wall and an inner air flow guided by the inner wall during a thrust phase. Each thin portion comprising a downstream leading edge situated longitudinally downstream of each upstream leading edge so as to detach a reverse air flow at the air inlet lip during a thrust reversal phase.

Air inlet of a nacelle of an aircraft propulsion assembly for promoting a thrust phase and a reverse thrust phase, and method for using same

An annular intermediate casing for a turbomachine through which an aerodynamic airstream circulates, including a radially internal shroud, a radially external shroud, at least one stator blade including a vane with a leading edge, and at least one aero-dynamic member which is formed of a structural arm extending radially at least in part between the radially internal shroud and the radially external shroud. The aerodynamic member includes a leading edge which is aligned with the leading edge of the stator blade in one plane and which is borne by a profiled portion positioned upstream of the structural arm in the direction of circulation of the aerodynamic airstream, the profiled portion, the structural arm, the radially internal shroud and the radially external shroud being monobloc.

Intermediate flow-straightening casing with monobloc structural arm

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MOISSY-CRAMAYEL, France

Yacine Cheraga