Patent ID: 6032901
Filing Date: 2000-03-07
Classification: B64D,F01D,F02K,Y02T,Y10T

Abstract:
A linkage system for an aircraft turbojet engine equipped with a thrust reverser, the linkage system comprising:a turbojet engine (1) having an external casing (3) and a longitudinal axis (2);a thrust reverser comprising two half clamshells (16) mounted around the turbojet engine (1) and its external casing (3);at least one annular inner linkage element (35) rigidly affixed to the external casing (3);at least one annular outer linkage element (40) rigidly affixed to each of the clamshells (16), the outer linkage elements (40) each comprising a radially outwardly facing seat (50); anda plurality of movable latching members (62) mounted on the external casing (3), the latching members (62) being movable between a closed position in which one end (62a) of each latching member (62) is located radially outwardly above a respective one of the seats (50) and an open position in which the one end (62a) of each latching member (62) is not located radially outwardly above the respective seat (50), the movement of each of the latching members (62) substantially taking place in a plane perpendicular to a straight line which is radial to the longitudinal axis (2) and passes through the respective seat (50) where a respective one of the latching members (62) covers the respective seat (50);wherein the clamshells (16) are axially connected to the external casing (3) by a mutual radial penetration of the at least one inner linkage element (35) and the at least one outer linkage element (40), the mutual radial penetration substantially taking place in a plane perpendicular to the longitudinal axis (2) such that movement of the latching members (62) into the closed position prevents the outer linkage elements (40) from moving radially away from the inner linkage elements (35).