Patent ID: 11891965
Assignee: SAFRAN NACELLES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 21:
22. An engine nacelle of a bypass turbojet engine type disposed along a main axis, the engine nacelle comprising:
a thrust reverser system having at least one movable cowl movable axially between a direct jet front position and a reverse jet rear position which tilts a plurality of pivoting flaps while at least partially closing an annular flow path, and which opens lateral openings of the annular flow path upstream of the plurality of pivoting flaps, equipped with thrust reverser cascades returning a cold air flow towards outside forwards, wherein each movable cowl includes:
a control sector sliding in a transverse plane relative to the main axis;
a return device connecting a fixed portion of the engine nacelle to the control sector to slide the control sector to a reversal position when the at least one movable cowl is recoiled; and
a plurality of flap tie-rods connecting the control sector to the plurality of pivoting flaps disposed in front of the at least one movable cowl and movable by the control sector, the plurality of flap tie-rods tilting the plurality of pivoting flaps by closing the annular flow path upon movement by the control sector when sliding the control sector towards the reversal position,

wherein the return device includes a return plate spaced apart from the fixed portion of the engine nacelle and the control sector and pivotable relative to the fixed portion and the control sector, and wherein pivoting of the return plate relative to the fixed portion of the engine nacelle causes the return plate to pivot relative to the control sector and changes a distance of the return plate from the fixed portion of the engine nacelle and from the control sector.