Abstract: A method for joining thermoplastic composite components is provided that includes: providing a first thermoplastic composite (FTC) component having an FTC first zone and an FTC second zone; providing a second thermoplastic composite (STC) component having an STC first zone and an FTC second zone; forming a joint region between the FTC and STC components by disposing them in a stepped arrangement, wherein each material ply within the FTC first zone overlaps a material ply within the STC first zone by a first overlap distance, and at least one material ply within the FTC second zone overlaps a material ply within the STC second zone by a second overlap distance, and at least one material ply within the FTC second zone overlaps a material ply within the STC second zone by the first overlap distance; and joining the FTC and STC components by applying an elevated temperature and pressure.

Abstract: A seal arrangement includes a first outer skin and a second outer skin disposed about an axial centerline. The second outer skin is adjacent the first outer skin and includes at least one door. A bulkhead extends substantially radially at least a portion of a distance between the axial centerline and one of the first outer skin and the second outer skin. A first outer frame includes a first portion, a second portion, and a third portion. The first portion of the first outer frame is mounted to the bulkhead. A seal is mounted to one of the at least one door and the second portion. The at least one door is rotatable between a first position and a second position. In the second position the seal contacts the at least one door and the second portion. The third portion is configured to limit a compression of the seal.

Abstract: An anti-icing system for an aircraft nacelle includes an inner duct and an outer duct. The inner duct extends through a first bulkhead between a gas turbine engine and a plenum of the nacelle. The inner duct is configured to deliver heated gases from the gas turbine engine to the plenum. The outer duct includes a first end and a second end. The outer duct circumferentially encompasses at least a portion of the inner duct on a first side of the bulkhead. At least one of the first end and the second end of the outer duct is mounted to at least one of the respective first bulkhead and a second bulkhead by a bellows forming an annular seal between the respective bulkhead and the outer duct.

Abstract: A nacelle inlet may comprise a lip skin and a bulkhead mounted to the lip skin. The lip skin may define an orifice. The bulkhead may comprise a forward face, a first flange extending axially from an outer circumference of the forward face, and a ventilation groove formed in the forward face. The ventilation groove may be circumferentially aligned with the orifice.

Abstract: An anti-icing system is disclosed. In various embodiments, the anti-icing system includes an inner duct having a first end configured to deliver heated gas to a plenum and a second end spaced from the first end; an outer duct circumferentially encompassing at least a portion of the inner duct; and a seal system disposed proximate the second end, the seal system including a first annular seal having a radially inner end positioned proximate a flange disposed on the inner duct.

Abstract: A system is provided for a nacelle of an aircraft propulsion system. This system includes a tubular outer structure, a tubular inner structure and a seal assembly. The tubular inner structure projects through a bore of the tubular outer structure. The seal assembly is configured to close an end of an annulus between the tubular outer structure and the tubular inner structure. The seal assembly includes a seal land and a seal element. The seal land includes a seal land mount that circumscribes and is attached to the tubular inner structure. The seal land mount is configured with a v-shaped sectional geometry. The seal element is attached to the tubular outer structure. The seal element circumscribes and is sealingly engaged with the seal land. The seal element may be configured from or otherwise includes a polymer material.

Abstract: An anti-icing system is disclosed. In various embodiments, the anti-icing system includes an inner duct having a forward end configured to deliver a heated gas to a plenum and an aft end spaced from the forward end; an outer duct circumferentially encompassing at least a portion of the inner duct; and a forward seal system disposed proximate the forward end, the forward seal system including an aft attachment flange configured for positioning adjacent an aft bulkhead face of a forward bulkhead, the inner duct and the outer duct being connected to the aft attachment flange, and a seal configured for positioning adjacent a forward flange face of the aft attachment flange.

Abstract: A system is provided for a nacelle of an aircraft propulsion system. This system includes a tubular outer structure, a tubular inner structure and a seal assembly. The tubular inner structure projects through a bore of the tubular outer structure. The seal assembly is configured to close an end of an annulus between the tubular outer structure and the tubular inner structure. The seal assembly includes a seal land and a seal element. The seal land includes a seal land mount that circumscribes and is attached to the tubular inner structure. The seal land mount is configured with a v-shaped sectional geometry. The seal element is attached to the tubular outer structure. The seal element circumscribes and is sealingly engaged with the seal land. The seal element may be configured from or otherwise includes a polymer material.

Abstract: A nacelle inlet may comprise a lip skin and a bulkhead mounted to the lip skin. The lip skin may define an orifice. The bulkhead may comprise a forward face, a first flange extending axially from an outer circumference of the forward face, and a ventilation groove formed in the forward face. The ventilation groove may be circumferentially aligned with the orifice.

Abstract: A seal arrangement includes a first outer skin and a second outer skin disposed about an axial centerline. The second outer skin is adjacent the first outer skin and includes at least one door. A bulkhead extends substantially radially at least a portion of a distance between the axial centerline and one of the first outer skin and the second outer skin. A first outer frame includes a first portion, a second portion, and a third portion. The first portion of the first outer frame is mounted to the bulkhead. A seal is mounted to one of the at least one door and the second portion. The at least one door is rotatable between a first position and a second position. In the second position the seal contacts the at least one door and the second portion. The third portion is configured to limit a compression of the seal.

Abstract: An anti-icing system is disclosed. In various embodiments, the anti-icing system includes an inner duct having a forward end configured to deliver a heated gas to a plenum and an aft end spaced from the forward end; an outer duct circumferentially encompassing at least a portion of the inner duct; and a forward seal system disposed proximate the forward end, the forward seal system including an aft attachment flange configured for positioning adjacent an aft bulkhead face of a forward bulkhead, the inner duct and the outer duct being connected to the aft attachment flange, and a seal configured for positioning adjacent a forward flange face of the aft attachment flange.

Abstract: An anti-icing system is disclosed. In various embodiments, the anti-icing system includes an inner duct having a first end configured to deliver heated gas to a plenum and a second end spaced from the first end; an outer duct circumferentially encompassing at least a portion of the inner duct; and a seal system disposed proximate the second end, the seal system including a first annular seal having a radially inner end positioned proximate a flange disposed on the inner duct.

Abstract: An anti-icing system for an aircraft nacelle includes an inner duct and an outer duct. The inner duct extends through a first bulkhead between a gas turbine engine and a plenum of the nacelle. The inner duct is configured to deliver heated gases from the gas turbine engine to the plenum. The outer duct includes a first end and a second end. The outer duct circumferentially encompasses at least a portion of the inner duct on a first side of the bulkhead. At least one of the first end and the second end of the outer duct is mounted to at least one of the respective first bulkhead and a second bulkhead by a bellows forming an annular seal between the respective bulkhead and the outer duct.

Abstract: A guard defined by a wire-like framework can be mounted on a popcorn kettle to prevent burns from kettle contact. The guard is lightweight, and has resilient connector elements spacing the guard from the kettle.