US 12,240,618 B2
Turbojet engine fan casing
Guillaume Glemarec, Paris (FR); Quentin Matthias Emmanuel Garnaud, Paris (FR); and Frédéric Dautreppe, Paris (FR)
Assigned to Safran Aircraft Engines, Paris (FR)
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed on Dec. 13, 2021, as Appl. No. 17/549,291.
Application 17/549,291 is a continuation of application No. PCT/EP2020/064762, filed on May 27, 2020.
Claims priority of application No. 19/06245 (FR), filed on Jun. 12, 2019.
Prior Publication US 2022/0106049 A1, Apr. 7, 2022
Int. Cl. B64D 29/06 (2006.01); F02K 1/82 (2006.01); F02K 3/06 (2006.01); B64D 27/16 (2006.01)
CPC B64D 29/06 (2013.01) [F02K 1/827 (2013.01); F02K 3/06 (2013.01); B64D 27/16 (2013.01); F05D 2220/36 (2013.01)] 8 Claims
OG exemplary drawing
 
8. A fan casing for an aircraft bypass turbojet engine, the fan casing comprising:
one single wall including a main portion, a rear end portion, and at least one reinforcement extending from the main portion to the rear end portion, the at least one reinforcement removably covered by a movable cowl of a nacelle, the one single wall having an inner surface and an outer surface that define a thickness of the main portion, the main portion extending from an air inlet lip to the at least one reinforcement,
wherein the air inlet lip, the main portion, the movable cowl of the nacelle, and the rear end portion jointly form a continuous aerodynamic line when the at least one reinforcement is covered by the movable cowl, the at least one reinforcement configured to stiffen the fan casing, the at least one reinforcement extending inwardly from the inner surface of the main portion towards an inside of the nacelle to define at least one annular area and to allow the fan casing to be fastened to a plurality of fixed arms crossing a secondary stream flow path of the aircraft bypass turbojet engine, the at least one reinforcement having a longitudinal cross-section substantially similar to a W or U shape,
wherein the at least one reinforcement continuously extends from a rear end of the main portion, is recessed from the outer surface of the main portion, and forms at least one cavity exposed from the nacelle and opening outside the nacelle when the movable cowl is moved to uncover the at least one reinforcement.