An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure and a thrust reverser. The translating structure is configured to translate between a stowed position and a deployed position. The thrust reverser includes a blocker door, an actuation linkage and a door lock. The blocker door is pivotally coupled to the translating structure. The actuation linkage operatively couples the blocker door to the fixed structure such that translation of the translating structure to the deployed position actuates pivoting of the blocker door into a flowpath. The door lock is configured to lock the actuation linkage to the translating structure such that the pivoting of the blocker door into the flowpath is delayed as the translating structure translates from the stowed position towards the deployed position.

An assembly for an aircraft propulsion system includes a fixed structure, a translating structure and a thrust reverser. The thrust reverser includes a blocker door, a door link and a structure link. The blocker door is pivotally coupled to the translating structure. The door link includes a first door link arm, a second door link arm and a door link mount connected to the first door link arm and the second door link arm. The first door link arm and the second door link arm are each pivotally coupled to the blocker door. The first door link arm and the second door link arm laterally converge towards one another as the first door link arm and the second door link arm extend longitudinally towards the door link mount. The structure link extends longitudinally between and is pivotally coupled to the door link mount and the fixed structure.

An assembly is for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure and a thrust reverser. The translating structure is configured to translate between a stowed position and a deployed position. The thrust reverser includes a blocker door, a linkage mount and an actuation linkage. The blocker door is pivotally coupled to the translating structure. The linkage mount includes a mount link, a mount spring and a mount stop. The mount link is pivotally coupled to the fixed structure about a pivot axis. The mount spring is configured to bias the mount link about the pivot axis against the mount stop. The actuation linkage operatively couples the blocker door to the mount link.

A cascade for a jet engine thrust reverser is fabricated by co-consolidating pre-consolidated thermoplastic strongbacks and vanes. The strongbacks are reinforced with continuous fibers, and the vanes are reinforced with discontinuous fibers.

A thrust reverser blocker door may comprise a proximal surface, a distal surface located opposite the proximal surface, a first attachment feature extending from the distal surface, a second attachment feature extending from the distal surface, a drag link housing extending from the distal surface, a first diagonal stiffener extending from the distal surface and extending between the first attachment feature and the drag link housing, a second diagonal stiffener extending from the distal surface and extending between the second attachment feature and the drag link housing, a first perimetrical stiffener extending from the distal surface and extending from the first attachment feature and the drag link housing, a second perimetrical stiffener extending from the distal surface and extending from the second attachment feature and the drag link housing, and a middle stiffener extending between the first attachment feature and the second attachment feature.

A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, and an actuator. The transcowl is mounted on the support structure and is axially translatable between a stowed position and a deployed position. The actuator is coupled to the transcowl and the support structure, and is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The actuator includes an actuator housing, a screw, a nut, a rod end, and a tension rod. The tension rod is engaged by the nut when the transcowl is in the deployed position and is engaged by the rod end when the transcowl is in the stowed position, whereby actuator loads, in both the deployed and stowed positions, are transmitted through the tension rod to the support structure.

An aircraft nacelle equipped with a thrust reversal device which comprises: at least one deflection system configured to deflect an air stream channeled in the nacelle toward a lateral opening of the nacelle, in the activated state; at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system toward the upstream end of the nacelle, at least one downstream deflector positioned at the downstream edge of the lateral opening and configured to deflect the air stream deflected by the deflection system toward the upstream end of the nacelle.

A gas turbine engine includes a thrust reverser including a plurality of blocker doors moveable between a deployed position and a stowed position. A gap is defined between adjacent blocker doors when in the stowed position. A plurality of divots are mounted forward of the plurality of blocker doors to substantially cover the gap between the adjacent blocker doors when in the stowed position.

A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material.

A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, an actuator, and a retractable cable. The support structure is configured to be mounted to the turbine engine. The transcowl is mounted on the support structure and is axially translatable, relative to the support structure, between a stowed position and a deployed position. The actuator is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The retractable cable is coupled to the transcowl and the support structure, and is configured to react reverse thrust loads on the transcowl at least when the transcowl is in the deployed position, to thereby at least reduce thrust loading on the actuator.