Patent ID: 11933246
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Transport (Mechanical engineering)
Classification: CPC B  F  Y | IPC F

Claim 0:
1. An aircraft turbojet engine extending along an axis X and oriented from upstream to downstream in which an internal air flow circulates from upstream to downstream during a thrust phase and a reverse air flow from downstream to upstream during a thrust reversal phase, said turbojet engine comprising:
a fan configured to provide reverse thrust;
a nacelle comprising an air intake, the air intake circumferentially extending about the axis X and comprising an internal wall pointing to the axis X and configured to guide the internal air flow and the reverse air flow, and an external wall opposite to the internal wall and configured to guide an external air flow, the internal wall and the external wall being connected to each other by an air intake lip so as to form an annular cavity, wherein the air intake further comprising:
a deflection device comprising at least one deflection member movably mounted between an extended position, in which the at least one deflection member projectingly extends from the internal wall or from the air intake lip in a radially internal extension direction pointing to the axis X or in a longitudinal extension direction relative to the axis X in order to allow a separation of the reverse air flow from the internal wall to promote the thrust reversal phase, and a retracted position, in which the air intake has an aerodynamic profile so as to guide the internal air flow onto the internal wall to promote the thrust phase;

wherein the at least one deflection member is translationally mounted between the extended position and the retracted position; and
wherein the deflection device comprises a single deflection member circumferentially extending about the axis X.