US 12,078,124 B2
Thrust reverser assembly for a turbojet engine
Pierre Charles Caruel, Moissy-Cramayel (FR)
Assigned to SAFRAN NACELLES, Gonfreville-l'Orcher (FR)
Appl. No. 18/565,461
Filed by SAFRAN NACELLES, Gonfreville-l'Orcher (FR)
PCT Filed May 30, 2022, PCT No. PCT/FR2022/051029
§ 371(c)(1), (2) Date Nov. 29, 2023,
PCT Pub. No. WO2022/254141, PCT Pub. Date Dec. 8, 2022.
Claims priority of application No. 2105724 (FR), filed on May 31, 2021.
Prior Publication US 2024/0254946 A1, Aug. 1, 2024
Int. Cl. F02K 1/76 (2006.01); F02K 1/72 (2006.01)
CPC F02K 1/763 (2013.01) [F02K 1/72 (2013.01); F02K 1/766 (2013.01); F05D 2240/11 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A thrust reverser assembly for a turbojet engine, comprising:
a stationary structure of the thrust reverser assembly, having a main axis;
a movable shroud, which is capable of moving in translation along the main axis between an attached position, in which the shroud is attached to the stationary structure, and a spaced position, in which the shroud is spaced from the stationary structure;
at least one latch capable of holding the stationary structure and the shroud in the attached position;
at least one actuator, mounted between the stationary structure and the shroud, configured to move the shroud along the main axis between the attached position and the spaced position; and
a gasket, configured to provide a seal between the stationary structure and the shroud in the attached position, wherein the gasket has a varying cross section along its circumference.