Abstract: A cowl door includes a cowl door body having a first side, a second side, and an interior surface and an exterior surface extending between the first side and the second side. The cowl door body is configured to be rotatably mounted to a structure at the first side of the cowl door body. At least one stiffener is mounted to the interior surface of the cowl door body and extends lengthwise at least a portion of a distance between the first side and the second side of the cowl door body. The at least one stiffener includes a stiffener body having a latch housing section disposed at a second stiffener end of the stiffener body proximate the second side of the cowl door body. A latch member is mounted to the stiffener body and disposed at least partially within the latch housing section of the stiffener body.

Abstract: A nacelle system is disclosed. In various embodiments, the nacelle system may include a nacelle component; an attachment structure; and a bracket configured to secure the nacelle component to the attachment structure, the bracket comprising a first arm having a first bead structure disposed between a proximal end and a distal end of the bracket.

Abstract: A cowl door includes a cowl door body having a first side, a second side, and an interior surface and an exterior surface extending between the first side and the second side. The cowl door body is configured to be rotatably mounted to a structure at the first side of the cowl door body. At least one stiffener is mounted to the interior surface of the cowl door body and extends lengthwise at least a portion of a distance between the first side and the second side of the cowl door body. The at least one stiffener includes a stiffener body having a latch housing section disposed at a second stiffener end of the stiffener body proximate the second side of the cowl door body. A latch member is mounted to the stiffener body and disposed at least partially within the latch housing section of the stiffener body.

Abstract: A nacelle may comprise a fan cowl and a tie rod assembly coupled to the fan cowl. The tie rod assembly may comprise a first tie rod coupled to the fan cowl and a second tie rod coupled to the first tie rod and the fan cowl. Rotational motion may be transferred between the first tie rod and the second tie rod. A retention structure may be coupled to an interior surface of the fan cowl.

Abstract: A nacelle system is disclosed. In various embodiments, the nacelle system may include a nacelle component; an attachment structure; and a bracket configured to secure the nacelle component to the attachment structure, the bracket comprising a first arm having a first bead structure disposed between a proximal end and a distal end of the bracket.

Abstract: A drag link assembly for use in a thrust reverser of a propulsion system is provided. The thrust reverser includes a fixed structure and a translating structure that at least partially define an annular airstream bypass duct there between. The translating structure is moveable relative to the fixed structure. The translating structure includes a blocker door disposed at least partially within the airstream bypass duct. The drag link assembly includes a drag link fitting and a drag link. The drag link fitting is fastened to the fixed structure of the thrust reverser. The drag link includes a first end portion and an opposing second end portion. The first end portion is pivotably connected to the blocker door. The second end portion is pivotably connected to the drag link fitting. The second end portion includes a curved section.

Abstract: A nacelle may comprise a fan cowl and a tie rod assembly coupled to the fan cowl. The tie rod assembly may comprise a first tie rod coupled to the fan cowl and a second tie rod coupled to the first tie rod and the fan cowl. Rotational motion may be transferred between the first tie rod and the second tie rod. A retention structure may be coupled to an interior surface of the fan cowl.

Abstract: A compression rod may include a plunger and a spring. A proximal end and a distal end of the compression rod may contact engagement features in a core cowl of a gas turbine engine. The compression rod may transmit loads between halves of the core cowl. The spring may cause the plunger to extend and contract in response to vibrations or other relative movement between halves of the core cowl.

Abstract: A nacelle is provided for an aircraft propulsion system. The nacelle may include an outer barrel and an active laminar flow control system. The active laminar flow control system may include a plurality of suction sources and a plurality of arrays of perforations in the outer barrel. The active laminar flow control system may be configured with a plurality of zones. Each of the zones may include a respective one of the suction sources which is fluidly coupled with a respective one of the arrays of perforations in the outer barrel.

Abstract: A nacelle inlet is provided for an aircraft propulsion system. This nacelle inlet includes an outer barrel, a bulkhead and a plurality of supports. The outer barrel extends around an axis and along the axis to an aft end. The bulkhead is within and connected to the outer barrel. An aft portion of the outer barrel projects axially aftward from the bulkhead to the aft end. The supports are disposed around the axis and next to the bulkhead. The supports are configured to support the aft portion of the outer barrel.

Abstract: A thrust reverser of a propulsion system nacelle is provided. The thrust reverser includes a fixed structure, a translating structure, and an aerodynamic feature. The fixed structure includes an annular wall that partially defines an annular bypass airstream duct. The fixed structure is bifurcated into left and right side sections. The annular wall extends between upper and lower bifurcation walls of the left side section, and extends between upper and lower bifurcation walls of the right side section. The translating structure is moveable relative to the fixed structure, between a stowed position and a deployed position. The aerodynamic feature that includes a flange disposed relative to an aft end portion of one of the lower bifurcation walls. The flange aids in preventing aerodynamic drag.

Abstract: A compression rod may include a plunger and a spring. A proximal end and a distal end of the compression rod may contact engagement features in a core cowl of a gas turbine engine. The compression rod may transmit loads between halves of the core cowl. The spring may cause the plunger to extend and contract in response to vibrations or other relative movement between halves of the core cowl.

Abstract: A nacelle inlet is provided for an aircraft propulsion system. This nacelle inlet includes an outer barrel, a bulkhead and a plurality of supports. The outer barrel extends around an axis and along the axis to an aft end. The bulkhead is within and connected to the outer barrel. An aft portion of the outer barrel projects axially aftward from the bulkhead to the aft end. The supports are disposed around the axis and next to the bulkhead. The supports are configured to support the aft portion of the outer barrel.

Abstract: A nacelle is provided for an aircraft propulsion system. The nacelle may include an outer barrel and an active laminar flow control system. The active laminar flow control system may include a plurality of suction sources and a plurality of arrays of perforations in the outer barrel. The active laminar flow control system may be configured with a plurality of zones. Each of the zones may include a respective one of the suction sources which is fluidly coupled with a respective one of the arrays of perforations in the outer barrel.

Abstract: A compression rod may include a plunger and a spring. A proximal end and a distal end of the compression rod may contact engagement features in a core cowl of a gas turbine engine. The compression rod may transmit loads between halves of the core cowl. The spring may cause the plunger to extend and contract in response to vibrations or other relative movement between halves of the core cowl.

Abstract: A compression rod may include a plunger and a spring. A proximal end and a distal end of the compression rod may contact engagement features in a core cowl of a gas turbine engine. The compression rod may transmit loads between halves of the core cowl. The spring may cause the plunger to extend and contract in response to vibrations or other relative movement between halves of the core cowl.

Abstract: A drag link assembly for use in a thrust reverser of a propulsion system is provided. The thrust reverser includes a fixed structure and a translating structure that at least partially define an annular airstream bypass duct there between. The translating structure is moveable relative to the fixed structure. The translating structure includes a blocker door disposed at least partially within the airstream bypass duct. The drag link assembly includes a drag link fitting and a drag link. The drag link fitting is fastened to the fixed structure of the thrust reverser. The drag link includes a first end portion and an opposing second end portion. The first end portion is pivotably connected to the blocker door. The second end portion is pivotably connected to the drag link fitting. The second end portion includes a curved section.

Abstract: A thrust reverser of a propulsion system nacelle is provided. The thrust reverser includes a fixed structure, a translating structure, and an aerodynamic feature. The fixed structure includes an annular wall that partially defines an annular bypass airstream duct. The fixed structure is bifurcated into left and right side sections. The annular wall extends between upper and lower bifurcation walls of the left side section, and extends between upper and lower bifurcation walls of the right side section. The translating structure is moveable relative to the fixed structure, between a stowed position and a deployed position. The aerodynamic feature that includes a flange disposed relative to an aft end portion of one of the lower bifurcation walls. The flange aids in preventing aerodynamic drag.

Abstract: An assembly useful in reducing aircraft engine noise such as turbofan engine noise comprises: (a) a core portion comprising at least one entrance end and at least one exit end for the passage of acoustic energy therethrough; (b) a first member having an exterior face and an interior face, wherein the first member is adjacent to at least a part of the core portion, and the first member has a plurality of openings therein to permit the passage of acoustic energy therethrough; and (c) a second member having an exterior face and an interior face, wherein the interior face of the second member is adjacent to the core portion. The core portion may be a honeycomb acoustic structure, and the first member may be perforated to permit the passage of acoustic energy into and out of the conduit portion.

Abstract: A thrust reverser for a turbofan engine having an air duct defined radially inwardly by a wall around the turbofan engine and radially outwardly in part by a fan cowl of the engine. A bulkhead is adapted to be mounted on the fan cowl having a shaped surface defining an upstream wall. A translating cowl is supported for movement axially between a closed position substantially adjacent the bulkhead and an open position spaced axially apart from the bulkhead so as to form an outlet for discharge of air from the air duct. The translating cowl has a first wall and a kicker plate defining a shaped surface. The kicker plate and/or the bulkhead may have a dimension which varies at different radial locations about a circumference of the translating cowl to selectively control the forward component of velocity of the air discharged from the air duct. A plume control device may extend longitudinally across the outlet to divide the air discharged from the air duct into a plurality of plumes.