US 12,247,528 B2
Deflector provided with a spoiler for a thrust reverser of an aircraft engine nacelle
Frédéric Chelin, Toulouse (FR); Christophe Bourdeau, Toulouse (FR); Romain Cusset, Toulouse (FR); and Lauren Davis, Toulouse (FR)
Assigned to AIRBUS OPERATIONS SAS, Toulouse (FR)
Filed by Airbus Operations SAS, Toulouse (FR)
Filed on Apr. 19, 2023, as Appl. No. 18/303,076.
Claims priority of application No. 2203681 (FR), filed on Apr. 21, 2022.
Prior Publication US 2023/0340929 A1, Oct. 26, 2023
Int. Cl. F02K 1/72 (2006.01); F02K 1/76 (2006.01)
CPC F02K 1/72 (2013.01) [F02K 1/766 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A thrust reverser for a nacelle of an aircraft engine, the thrust reverser comprising:
an orbital deflector, the orbital deflector arranged in a direction normal to a direction of an engine centerline of the aircraft; and
a lateral deflector, the lateral deflector arranged in the direction of the engine centerline, and, wherein each of the orbital deflector and the lateral deflector comprises:
a deflector plate configured to act on an aerodynamic flow, said deflector plate having a concave face and a convex face, as well as an intake end and an exhaust end, the deflector plate configured to fit entirely within a thickness of the aircraft engine nacelle during an opening phase of the nacelle wherein a mobile cover of the nacelle is moved backwards in relation to an air intake of the nacelle, and,
a spoiler rigidly connected to the exhaust end of the deflector plate, wherein an angle of the spoiler from a line normal to the centerline of the aircraft engine is greater than an angle of the exhaust end of the deflector plate from the line normal to the centerline of the aircraft engine;
wherein the exhaust end of the deflector plate and the spoiler meet at a deflection point where the spoiler becomes orthogonal to the line normal to the centerline of the engine.