Abstract: A joining method is provided during which a first thermoplastic component joint section and a second thermoplastic component joint section are arranged between first tooling and second tooling. The second thermoplastic component joint section is abutted against the first thermoplastic component joint section at a joint area. The first thermoplastic component joint section is joined to the second thermoplastic component joint section to provide a unitized thermoplastic structure. The joining includes: pressing the first thermoplastic component joint section against the second thermoplastic component joint section at the joint area between the first tooling and the second tooling using a pressure device; and heating the first thermoplastic component joint section and the second thermoplastic component joint section at the joint area using a first heater configured with the first tooling. The unitized thermoplastic structure is cooled at the joint area using a first cooler configured with the first tooling.

Abstract: A method is provided for joining thermoplastic components. During this method, a skin is provided that is configured from or otherwise includes a skin fiber-reinforced thermoplastic composite. A support member is provided that is configured from or otherwise includes a support member fiber-reinforced thermoplastic composite. A shim is arranged at an interface between the skin and the support member. The shim is configured from or otherwise includes a shim fiber-reinforced thermoplastic composite. The support member is welded to the skin through the shim at the interface.

Abstract: During a formation method, a first component and a second component are provided. The first component is configured from or otherwise includes a first fiber-reinforced thermoplastic composite. The first component also includes a base and a material buildup on a portion of the base. The second component is configured from or otherwise includes a second fiber-reinforced thermoplastic composite. The second component is arranged with the first component. The second component abuts the material buildup. The second component is vibration welded to the first component to provide a weld joint between the first component and the second component. At least a portion of the material buildup is displaced during the vibration welding.

Abstract: An apparatus for aircraft anti-icing includes a nozzle body, at least one nozzle extending from the nozzle body, and at least one vane disposed in at least one of the nozzle(s), the at least one vane configured to impart rotational movement of a hot gas moving through the nozzle(s).

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: An apparatus for aircraft anti-icing includes a nozzle body, a nozzle extending from the nozzle body, an eductor shroud at least partially surrounding the nozzle, the eductor shroud configured to focus a first flow of ambient air towards a first flow of hot gas exiting the first nozzle.

Abstract: An apparatus for aircraft anti-icing includes a nozzle head including an inner wall and an outer wall, the inner wall defining a through-hole extending through the nozzle, the outer wall circumscribing the inner wall, wherein a plenum is disposed between the inner wall and the outer wall, and a neck extending from the outer wall of the nozzle head, the neck configured to supply a flow of hot gas to the plenum, wherein a maximum width of the inner surface of the neck is less than a maximum width of the through-hole.

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: An apparatus for aircraft anti-icing includes a nozzle body, a nozzle extending from the nozzle body, an eductor shroud at least partially surrounding the nozzle, the eductor shroud configured to focus a first flow of ambient air towards a first flow of hot gas exiting the first nozzle.

Abstract: An apparatus for aircraft anti-icing includes a nozzle body, at least one nozzle extending from the nozzle body, and at least one vane disposed in at least one of the nozzle(s), the at least one vane configured to impart rotational movement of a hot gas moving through the nozzle(s).

Abstract: An apparatus for aircraft anti-icing includes a nozzle head including an inner wall and an outer wall, the inner wall defining a through-hole extending through the nozzle, the outer wall circumscribing the inner wall, wherein a plenum is disposed between the inner wall and the outer wall, and a neck extending from the outer wall of the nozzle head, the neck configured to supply a flow of hot gas to the plenum, wherein a maximum width of the inner surface of the neck is less than a maximum width of the through-hole.

Abstract: A blocker door actuation system for use in an aircraft thrust reverser is provided. The blocker door actuation system may comprise a rack, a gear, a gear housing, a screw shaft, and a link. The blocker door actuation system may be mounted to a translating sleeve in an aircraft nacelle. In response to the thrust reverser being activated and the translating sleeve moving aft, the blocker door actuation system may move the blocker door from a stowed position to a deployed position in a fan air duct.

Abstract: A blocker door actuation system for use in an aircraft thrust reverser is provided. The blocker door actuation system may comprise a rack, a gear, a gear housing, a screw shaft, and a link. The blocker door actuation system may be mounted to a translating sleeve in an aircraft nacelle. In response to the thrust reverser being activated and the translating sleeve moving aft, the blocker door actuation system may move the blocker door from a stowed position to a deployed position in a fan air duct.