Grid-type thrust reverser for turbojet engine
A grid-type thrust reverser for a turbojet engine includes a moving O-shaped thrust reverser body that is generally cylindrical in shape around a longitudinal central axis (A) and includes an inner wall configured to delimit a cold air stream, with an inner structure that surrounds the turbojet engine, the movable thrust reverser body being mounted so as to be able to slide along the longitudinal central axis (A) between a direct jet position in which the outer cowl covers the thrust reverser grids, and a thrust-reversal position in which the outer cowl uncovers the thrust reverser grids. The movable thrust reverser body includes a first half-portion and a second half-portion that are mounted so as to each pivot about a longitudinal pivot axis (B), between a closed position and an open gullwing position for removing the turbojet engine, via the cradle.
1. A cascade thrust reverser for a turbojet engine configured to form at least one portion of a downstream section of a nacelle accommodating the turbojet engine, the cascade thrust reverser comprising:
a front frame adapted to be mounted downstream of a fan casing and supporting thrust reverser cascades;
an O-type thrust reverser movable body having a cylindrical shape around a longitudinal central axis and comprising an inner wall adapted to delimit a cold air flow path with an inner structure, the cold flow path devoid of any connecting portions extending therethrough, the inner structure surrounding the turbojet engine, and an outer cowl, the O-type thrust reverser movable body being slidably mounted along the longitudinal central axis between a direct jet position in which the outer cowl covers the thrust reverser cascades, and a thrust reversal position in which the outer cowl uncovers the thrust reverser cascades; and
a cradle which is configured to link an upper portion of the O-type thrust reverser movable body on a suspension pylon of the nacelle to provide sliding of the O-type thrust reverser movable body,
wherein the O-type thrust reverser movable body comprises a first half-portion and a second half-portion, each of the first half-portion and the second half-portion being semi-cylindrical and linked to one another in a lower portion of the O-type thrust reverser movable body by a first dismountable link device, each of the first half-portion and the second half-portion of the O-type thrust reverser movable body being pivotally mounted about a longitudinal pivot axis, between a closed position and a butterfly open position for removing the turbojet engine, via the cradle.
2. The cascade thrust reverser according to claim 1 , wherein the outer cowl of the O-type thrust reverser movable body comprises a C-shaped first half-cowl and a C-shaped second half-cowl, each of the C-shaped first half-cowl and the C-shaped second half-cowl being pivotally mounted about a longitudinal pivot axis C, between a closed position and a maintenance butterfly open position.
3. The cascade thrust reverser according to claim 1 , further comprising a second dismountable link device which slidably links the thrust reverser cascades on the O-type thrust reverser movable body.
4. The cascade thrust reverser according to claim 3 , wherein the second dismountable link device is a screw-nut type dismountable link device.
5. The cascade thrust reverser according to claim 1 , wherein the first dismountable link device is a screw-nut type dismountable link device.
6. The cascade thrust reverser according to claim 1 , wherein the cradle comprises:
a first half-cradle carrying the first half-portion of the O-type thrust reverser movable body and pivotally mounted on the suspension pylon about the longitudinal pivot axis B of the first half-portion configured to provide pivoting of the first half-portion of the O-type thrust reverser movable body; and
a second half-cradle carrying the second half-portion of the O-type thrust reverser movable body and pivotally mounted on the suspension pylon about the longitudinal pivot axis of the second half-portion so as to provide pivoting of the second half-portion of the O-type thrust reverser movable body.
7. The cascade thrust reverser according to claim 6 , wherein the cascade thrust reverser comprises an anti-rotation device configured to pivotally lock the first half-portion and the second half-portion of the O-type thrust reverser movable body in the closed position, and wherein the anti-rotation device comprises:
a first lock which locks the first half-cradle pivotally on the suspension pylon; and
a second lock which locks the second half-cradle pivotally on the suspension pylon.
8. The cascade thrust reverser according to claim 6 , wherein the first half-cradle comprises a slide connection which slidably links the first half-portion of the O-type thrust reverser movable body on the suspension pylon, and the second half-cradle comprises a slide connection which slidably links the second half-portion of the O-type thrust reverser movable body on the suspension pylon.
9. The cascade thrust reverser according to claim 1 , wherein the cascade thrust reverser comprises an anti-rotation device configured to pivotally lock the first half-portion and the second half-portion of the O-type thrust reverser movable body in the closed position.
10. The cascade thrust reverser according to claim 1 , wherein the cascade thrust reverser comprises a plurality of actuators, each actuator of the plurality of actuators linking the front frame of the thrust reverser on the thrust reverser cascades and configured to slidably drive the thrust reverser cascades and the O-type thrust reverser movable body.
11. The cascade thrust reverser according to claim 1 , wherein the O-type thrust reverser movable body is detached from the inner structure.
12. A nacelle for an aircraft turbojet engine comprising a cascade thrust reverser according to claim 1 .