A method for deploying a thrust reverser includes translating a carrier along a track, transferring a first load between the carrier and a first reverser door in response to the carrier translating along the track, rotating the first reverser door between a closed position and an open position in response to the carrier translating along the track, transferring a second load between the carrier and a deployable fairing in response to the carrier translating along the track, and rotating the deployable fairing between a stowed position and a deployed position in response to the carrier translating along the track.

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 frame, 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.

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 frame, 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.

A thrust reverser system for jet aircraft comprising an exhaust tailpipe mounted to the turbine engine aft turbine flange, clamshell doors, actuators and locking systems to prevent inadvertent deployment of the clamshell doors. Improved design clamshell doors shrouding the tailpipe fitted with two patented design actuators, enclosed between the doors and the tailpipe. The actuators throw the doors behind the tailpipe exhaust exit area using improved linkages attached to the tailpipe and the doors, to reverse the exhaust gases forward. The tailpipe can be of circular or any geometric shape. Reverse Exhaust gases are enclosed between the doors and two movable fairings. Several sound attenuation configurations provisions for the tailpipe, the fixed and movable fairings. Three independent locking systems provisions to prevent inadvertent deployment of the doors.

A method for gathering flight load data for a gas turbine engine includes providing a plurality of blocker doors rotatably mounted to a translating sleeve and a plurality of blocker door islands, each blocker door island disposed between circumferentially adjacent blocker doors of the plurality of blocker doors and mounted to at least one mounting point of the translating sleeve, wherein a blocker door island of the plurality of blocker door islands is a data acquisition unit; and connecting the data acquisition unit to at least one sensor in communication with the translating sleeve.

The subject matter of this specification can be embodied in, among other things, an engine assembly includes a nacelle configured to at least partially surround an engine, and a thrust reverser coupled to the nacelle, the thrust reverser having a thrust-reversing element movable relative to the nacelle between a stowed position and a deployed position, a hydraulic actuator operably coupled to move the thrust-reversing element between the stowed position and the deployed position, and a fluid control system configured to operate the hydraulic actuator, the fluid control system having an electrohydraulic servo valve operable to selectively route fluid between a pressurized fluid source, the hydraulic actuator, and a fluid return reservoir, and a bypass fluid line providing fluid communication between the hydraulic actuator and the fluid return reservoir independent of the electrohydraulic servo valve.

A position sensor for an aircraft nacelle thrust reverser door for an aircraft turbojet engine includes a target to be detected, a detector having a detection range and including a detection head configured to detect the target when it enters its detection range, and a target guide configured to guide the target in order to position it in the detection range of the detector. The detector is stationary relative to the target guide. In one form, the target is intended to be positioned on the door, and the detector and the target guide are intended to be positioned on a stationary structure of the thrust reverser. In another form, the target is intended to be positioned on a stationary structure of the thrust reverser, and the detector and the target guide are intended to be positioned on the door.

A position sensor for an aircraft nacelle thrust reverser door for an aircraft turbojet engine includes a target to be detected, a detector having a detection range and including a detection head configured to detect the target when it enters its detection range, and a target guide configured to guide the target in order to position it in the detection range of the detector. The detector is stationary relative to the target guide. In one form, the target is intended to be positioned on the door, and the detector and the target guide are intended to be positioned on a stationary structure of the thrust reverser. In another form, the target is intended to be positioned on a stationary structure of the thrust reverser, and the detector and the target guide are intended to be positioned on the door.

A method for forming a fiber-reinforced thermoplastic acoustic panel may comprise: stacking plies of thermoplastic composite sheets to a first thickness to form a top sheet; stacking plies of thermoplastic composite sheets to a second thickness to form a backskin; staking plies of thermoplastic composite sheets to a third thickness to form a stiffening member; forming the top sheet in a first contour; forming the backskin in a second contour, the second contour being different from the first contour; forming the stiffening member comprising a shape having a plurality of peaks and troughs; bonding the stiffening member to the top sheet and the backskin; and perforating the top sheet.

A first cascade segment of a thrust reverser system has a first cascade segment flow area and is associated with a first lateral sector. A second cascade segment has a second cascade segment flow area and is associated with a second lateral sector. The second cascade segment flow area may be at least 1.2 times the first cascade segment flow area. The first lateral sector has a first leakage flow area and a first total flow area that is equal to a sum of at least the first cascade segment flow area and the first leakage flow area. The second lateral sector has a second leakage flow area and a second total flow area that is equal to a sum of at least the second cascade segment flow area and the second leakage flow area. The second total flow area may be within 10% of the first total flow area.