Abstract: Aspects of the disclosure are directed to a thrust reverser system of an aircraft comprising: a translating cascade sleeve, a blocker door, and a kinematic mechanism configured to actuate the blocker door, the kinematic mechanism comprising: a first link coupled to the translating cascade sleeve, a second link coupled to the first link and a fixed structure, and a third link coupled to the first link and the blocker door.

Abstract: A system for a thrust reverser of an aircraft includes a primary sleeve and a secondary sleeve having cascades. The secondary sleeve is coupled to a set of blocker doors. The sliding motions of the primary sleeve and the secondary sleeve are not directly coupled when each moves between its stowed and deployed positions. The sliding motion of the primary sleeve may begin at a different time and continue at a different rate from the sliding motion of the secondary sleeve.

Abstract: Aspects are directed to a system associated with a thrust reverser of an aircraft, comprising: a blocker door and a fan case, where when the thrust reverser is stowed the blocker door is stowed at least in part radially outboard of the fan case. Aspects include a thrust reverser system comprising: a fixed structure, a translating sleeve configured to translate relative to the fixed structure, at least one blocker door pivotally mounted to the translating sleeve, and a rod coupled to the fixed structure and to the at least one blocker door, where during a first phase of thrust reverser deployment the blocker door translates with the translating sleeve when the translating sleeve is translating toward its deployed position and does not rotate, and during a second phase following the first phase, the blocker door pivots relative to the translating sleeve from a stowed position to a deployed position.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure, a blocker door and a folding linkage. The translating structure is configured to move between a stowed position and a deployed position. The blocker door is pivotally attached to the translating structure at a first pivot joint. The folding linkage links the blocker door to the fixed structure. The folding linkage includes a member pivotally attached to the blocker door at a second pivot joint that is radially outboard of a skin of the blocker door when the translating structure is in the stowed position. The second pivot joint is radially outboard of the first pivot joint when the translating structure is in the stowed position.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a target-type thrust reverser and a tubular trailing edge body. The target-type thrust reverser includes a plurality of thrust reverser doors. Each of the thrust reverser doors is configured to pivot between a stowed position to a deployed position. The tubular trailing edge body is configured to at least partially form a gas path nozzle for the aircraft propulsion system. The tubular trailing edge body is configured to be displaced when the thrust reverser doors pivot from the stowed position to the deployed position.

Abstract: The present disclosure provides a thrust reverser comprising a stationary structure defining an annular body with a centerline, a first reverser door pivotally coupled to the stationary structure by a pair of first reverser door hinges, a first reverser door hinge axis extending through the first reverser door hinges and positioned at a first angle relative to a centerline, and a second reverser door pivotally coupled to the stationary structure by a pair of second reverser door hinges, a second hinge line axis extending through the second reverser door hinges and positioned at a second angle relative to the centerline.

Abstract: A thrust reverser may comprise a frame, a first reverser door being movable relative to the frame, and a second reverser door being movable relative to the frame and rotationally movable relative to the first reverser door via a first pivot point, the first pivot point being movable relative to the frame via a first link rotationally mounted to the frame via a second pivot point.

Abstract: A thrust reverser for a gas turbine engine may comprise a frame, a first reverser door pivotally mounted to the frame at a first pivot point, a second reverser door pivotally mounted to the frame at a second pivot point, a first nacelle defining a first trailing edge of the gas turbine engine coupled between the frame and the first reverser door, and a second nacelle defining a second trailing edge of the gas turbine engine coupled between the frame and the second reverser door. The first nacelle and the second nacelle translate in an aft and radial outward direction relative to the gas turbine engine in response to the thrust reverser moving to a deployed position.

Abstract: A system for a thrust reverser of an aircraft includes a primary sleeve and a secondary sleeve having cascades. The secondary sleeve is coupled to a set of blocker doors. The sliding motions of the primary sleeve and the secondary sleeve are not directly coupled when each moves between its stowed and deployed positions. The sliding motion of the primary sleeve may begin at a different time and continue at a different rate from the sliding motion of the secondary sleeve.

Abstract: A kinematic system is provided that includes an outer cylinder, a mid-cylinder and an inner cylinder. The mid-cylinder is within the outer cylinder, and mated with the outer cylinder at a mid-outer threaded interface configured to transform axial translation of the outer cylinder into rotational motion of the mid cylinder along an axis. The inner cylinder is within the mid-cylinder, and mated with the mid-cylinder at a mid-inner threaded interface configured to transform the rotational movement of the mid-cylinder into axial translation of the inner cylinder along the axis. A first one of the mid-outer threaded interface and the mid-inner threaded interface includes a thread configured with a first thread portion and a second thread portion. The first thread portion is disposed at a first angle relative to the axis. The second thread portion is disposed at a second angle relative to the axis that is different from the first angle.

Abstract: A thrust reverser includes a frame having a longitudinal axis, a first reverser door pivotally mounted to the frame, a second reverser door pivotally mounted to the first reverser door, a crank pivotally mounted to the frame, a first link connecting the crank to the first reverser door, and a second link connecting the crank to the second reverser door. In various embodiments, both the first reverser door and the second reverser door are driven by a single actuator.

Abstract: A thrust reverser for a gas turbine engine includes a frame, a first reverser door pivotally mounted to the frame, and a second reverser door pivotally mounted to the first reverser door.

Abstract: Aspects of the disclosure are directed to a thrust reverser system of an aircraft comprising: a translating cascade sleeve, a blocker door, and a kinematic mechanism configured to actuate the blocker door, the kinematic mechanism comprising: a first link coupled to the translating cascade sleeve, a second link coupled to the first link and a fixed structure, and a third link coupled to the first link and the blocker door.

Abstract: A thrust reverser operable within a flowpath defined in-part by a surface carried by a fixed structure includes a translating sleeve constructed and arranged to move between first and second positions and a blocker door pivotally engaged to the translating sleeve for pivotal movement between a first state and a second state. A drag link assembly of the thrust reverser includes a base joint, a mid joint, and a distal joint. A base link extends between the base and mid joints, and a drag link extends between the mid and distal joints. The base joint operably connects the base link to the fixed structure, the mid joint operably connects the base link to the drag link, and the distal joint operably connects the drag link to the blocker door. The base joint and the mid joint are disposed beneath the surface when the blocker door is in the first state.

Abstract: An assembly is provided for an aircraft propulsion system with an axial centerline. The assembly includes a translating sleeve, a sleeve actuator and a locking apparatus. The sleeve actuator is connected to the translating sleeve. The sleeve actuator is configured to move the translating sleeve along the axial centerline between a stowed position and a deployed position. The locking apparatus includes a lock and a lock actuator. The lock comprises a locking element. The lock actuator is configured to move the locking element between a locked position and an unlocked position. The locking element is configured to lock the translating sleeve in the stowed position when the locking element is in the locked position. A first portion of the locking apparatus axially overlaps the sleeve actuator along the axial centerline. A second portion of the locking apparatus does not axially overlap the sleeve actuator along the axial centerline.

Abstract: An actuation system includes a linear actuator extends longitudinally along an actuation axis. A first link extends along a first centerline parallel to the actuation axis, where first link is on a first side of the linear actuator. A second link extends along a second centerline parallel to the actuation axis, where the second link is on a second side of the linear actuator. The first and the second links are configured to transfer a load along the first and the second centerlines between the component and the linear actuator.

Abstract: A thrust reverser of a turbofan engine has a translating structure and a blocker door device capable of diverting a bypass flowpath for reversing propulsion direction. The translating structure moves axially between a forward position and a rearward position and thereby drives a compound motion of a blocker door of the blocker door device that moves between respective stowed and deployed states. A passive linkage of the blocker door device is orientated between a stationary structure and the blocker door and may be utilized in combination with an extendable linkage that may be orientated between the blocker door and the stationary structure.

Abstract: A thrust reverser for a nacelle may include a translating sleeve. A plurality of linkless blocker doors may be coupled to the translating sleeve. The translating sleeve may translate along a line of action which is non-parallel to an engine centerline. The non-parallel translation of the translating sleeve may prevent interference between the translating sleeve and surrounding components.

Abstract: Aspects of the disclosure are directed to a system for a thrust reverser of an aircraft comprising: a primary sleeve, and a secondary sleeve, wherein a first stroke associated with the primary sleeve is different from a second stroke associated with the secondary sleeve, and wherein the primary sleeve traverses a first distance associated with the first stroke at the outset of a deployment of the thrust reverser and a second distance associated with the first stroke at a later stage of the deployment.

Abstract: A thrust reverser of a turbofan engine has a translating structure and a blocker door device capable of diverting a bypass flowpath for reversing propulsion direction. The translating structure moves axially between a forward position and a rearward position and thereby drives a compound motion of a blocker door of the blocker door device that moves between a respective stowed state and a deployed state. The compound motion is attributable through the blocker door being pivotally engaged to the translating structure, and through a multi-armed linkage of the device being pivotally engaged between a stationary structure, the blocker door and the translating structure. The linkage is further orientated such that it does not appreciably obstruct the bypass flowpath when the blocker door is in the stowed state.