Abstract: An ice protection system for an aircraft may comprise an electric heater embedded within a composite aircraft component. In the event of malfunction of the embedded heater, a secondary heater may be attached to an interior surface of the composite aircraft component. The wiring may be detached from the embedded heater and attached to the secondary heater. The secondary heater may be used to provide ice protection to the composite aircraft component.

Abstract: A nacelle may include a pylon and a thrust reverser having an inner fixed structure. A locking mechanism may automatically engage and prevent relative movement between a thrust reverser half and the pylon. A bumper may be coupled to the inner fixed structure. The locking mechanism may limit deflections between the thrust reverser and the pylon in response to a burst duct. The locking mechanism may allow the thrust reverser halves to be opened for access to the engine.

Abstract: An ice protection system for an aircraft may comprise an electric heater embedded within a composite aircraft component. In the event of malfunction of the embedded heater, a secondary heater may be attached to an interior surface of the composite aircraft component. The wiring may be detached from the embedded heater and attached to the secondary heater. The secondary heater may be used to provide ice protection to the composite aircraft component.

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: Methods are provided forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis. The nacelle inlet structure includes an inlet lip portion and an outer barrel portion. One of the method may include steps of: forming the inlet lip portion; forming the outer barrel portion; arranging the inlet lip portion axially adjacent the outer barrel portion; and friction stir welding the inlet lip portion to the outer barrel portion to provide a circumferentially extending weld joint between the inlet lip portion and the outer barrel portion.

Abstract: An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly includes an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween. The inner nacelle includes a nacelle wall and at least one access panel, which is adapted to at least partially cover an aperture in the nacelle wall. The outer nacelle axially overlaps the access panel.

Abstract: A system for controlling aircraft boundary layer airflow comprising a frame structure configured to be coupled or integral to an inner surface of an aircraft nacelle, the frame configured to support to the nacelle, and/or a modular plenum configured to be received by the frame structure, the modular plenum comprising a truncated tetrahedron intersected at its apex by a duct. The frame may comprise a plurality of sub-frames. The system may further comprise a plurality of modular plenums, each configured to fit within a sub-frame. The system may further comprise a flexible material configured to couple a first duct to a second duct. The system may further comprise a nacelle configured to receive the system.

Abstract: Methods are provided forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis. The nacelle inlet structure includes an inlet lip portion and an outer barrel portion. One of the method may include steps of: forming the inlet lip portion; forming the outer barrel portion; arranging the inlet lip portion axially adjacent the outer barrel portion; and friction stir welding the inlet lip portion to the outer barrel portion to provide a circumferentially extending weld joint between the inlet lip portion and the outer barrel portion.

Abstract: A nacelle is provided for an aircraft propulsion system. This nacelle includes an outer barrel and an active laminar flow control system. The active laminar flow control system includes an array of perforations in the outer barrel, a suction source and a drain mechanism. The suction source is fluidly coupled with the array of perforations. The drain mechanism is fluidly coupled with and between the array of perforations and the suction source.

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 nacelle may include a pylon and a thrust reverser having an inner fixed structure. A locking mechanism may automatically engage and prevent relative movement between a thrust reverser half and the pylon. A bumper may be coupled to the inner fixed structure. The locking mechanism may limit deflections between the thrust reverser and the pylon in response to a burst duct. The locking mechanism may allow the thrust reverser halves to be opened for access to the engine.

Abstract: A system for controlling aircraft boundary layer airflow comprising a frame structure configured to be coupled or integral to an inner surface of an aircraft nacelle, the frame configured to support to the nacelle, and/or a modular plenum configured to be received by the frame structure, the modular plenum comprising a truncated tetrahedron intersected at its apex by a duct. The frame may comprise a plurality of sub-frames. The system may further comprise a plurality of modular plenums, each configured to fit within a sub-frame. The system may further comprise a flexible material configured to couple a first duct to a second duct. The system may further comprise a nacelle configured to receive the system.

Abstract: An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly includes an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween. The inner nacelle includes a nacelle wall and at least one access panel, which is adapted to at least partially cover an aperture in the nacelle wall. The outer nacelle axially overlaps the access panel.

Abstract: An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on an outside surface. An inner barrel portion and an outer barrel portion of the nacelle inlet define a space therebetween. Ice protection-related equipment such as controllers, cables, switches, connectors, and the like, may reside in this space. One or more access openings are formed in the outer barrel to enable an operator to gain access to this equipment. The inlet cowling attaches to the inner and outer barrels with its outer lip extending sufficiently far in the aft direction to cover the access opening. When the cowling is removed, the access opening is uncovered, thereby permitting access to the equipment.

Abstract: An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on an outside surface. An inner barrel portion and an outer barrel portion of the nacelle inlet define a space therebetween. Ice protection-related equipment such as controllers, cables, switches, connectors, and the like, may reside in this space. One or more access openings are formed in the outer barrel to enable an operator to gain access to this equipment. The inlet cowling attaches to the inner and outer barrels with its outer lip extending sufficiently far in the aft direction to cover the access opening. When the cowling is removed, the access opening is uncovered, thereby permitting access to the equipment.

Abstract: An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on an outside surface. An inner barrel portion and an outer barrel portion of the nacelle inlet define a space therebetween. Ice protection-related equipment such as controllers, cables, switches, connectors, and the like, may reside in this space. One or more access openings are formed in the outer barrel to enable an operator to gain access to this equipment. The inlet cowling attaches to the inner and outer barrels with its outer lip extending sufficiently far in the aft direction to cover the access opening. When the cowling is removed, the access opening is uncovered, thereby permitting access to the equipment.

Abstract: An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on an outside surface. An inner barrel portion and an outer barrel portion of the nacelle inlet define a space therebetween. Ice protection-related equipment such as controllers, cables, switches, connectors, and the like, may reside in this space. One or more access openings are formed in the outer barrel to enable an operator to gain access to this equipment. The inlet cowling attaches to the inner and outer barrels with its outer lip extending sufficiently far in the aft direction to cover the access opening. When the cowling is removed, the access opening is uncovered, thereby permitting access to the equipment.

Abstract: A computer based product catalog system is provided for automatically distributing product information to members of a network. Electronically stored catalogs of multiple manufacturers' products, including descriptions of the products, are provided. An electronically stored distributor catalog, including selected products from the various manufacturers is also provided. Descriptions of the products in the manufacturers' catalogs may be updated automatically. In response to the updating of the manufacturers' catalogs, the descriptions of the products in the distributor's catalog may be automatically updated in real time. A terminal located at the retail level of distribution may be operatively connected to the manufacturers' catalogs and to the distributor catalog to allow viewing of product information therewithin. The terminal may enable users to order products from a manufacturer's and distributor's catalog.