Abstract: Guide systems for installing aircraft structures are disclosed. An example apparatus includes a first guide system structured to removably couple to a first aircraft structure having a first hinge component. A second guide system is structured to removably couple to a second aircraft structure having a second hinge component. The first guide system is to engage the second guide system to enable alignment between the first hinge component and the second hinge component during assembly of the first aircraft structure and the second aircraft structure.

Abstract: Guide systems for installing aircraft structures are disclosed. An example apparatus includes a first guide system structured to removably couple to a first aircraft structure having a first hinge component. A second guide system is structured to removably couple to a second aircraft structure having a second hinge component. The first guide system is to engage the second guide system to enable alignment between the first hinge component and the second hinge component during assembly of the first aircraft structure and the second aircraft structure.

Abstract: A fire seal end cap including a cap portion and a plug portion, wherein the plug portion protrudes from the cap portion, and wherein the cap portion and the plug portion are formed from a fire-resistant material.

Abstract: A method of forming a weld on a work piece is disclosed. The method may include creating an internal cavity along the work piece and extending a conduit having an exit orifice into the internal cavity such that the exit orifice may be positioned adjacent to the weld to be formed. The method may further include supplying a purge gas to the conduit, the purge gas being carried through the conduit and pushed out of the exit orifice so as to displace undesirable gasses away from the weld to be formed and then subsequently forming the weld.

Abstract: A propulsion system comprises a turbine engine, and an engine nacelle including an SPF/DB inner wall having a hot side face sheet against the engine and a cold side face sheet that has noise attenuation openings.

Abstract: A fire seal end cap including a cap portion and a plug portion, wherein the plug portion protrudes from the cap portion, and wherein the cap portion and the plug portion are formed from a fire-resistant material.

Abstract: A multi-member assembly including a first structural member, a second structural member opposed from the first structural member, a crossover seal positioned between the first and second structural members, wherein the crossover seal defines a bore, and an end cap including a cap portion and a plug portion protruding from the cap portion, wherein the plug portion is at least partially received in the bore such that the cap portion bridges the first and second structural members.

Abstract: A method of forming a weld on a work piece is disclosed. The method may include creating an internal cavity along the work piece and extending a conduit having an exit orifice into the internal cavity such that the exit orifice may be positioned adjacent to the weld to be formed. The method may further include supplying a purge gas to the conduit, the purge gas being carried through the conduit and pushed out of the exit orifice so as to displace undesirable gasses away from the weld to be formed and then subsequently forming the weld.

Abstract: A nacelle inlet is provided for a turbo-fan engine for an aircraft. The nacelle inlet includes a lip skin having first and second pad-ups, an inner barrel including a forward flange and a bulkhead. The bulkhead, the lip skin and the inner barrel are attached together at mating surfaces. The bulkhead and the lip skin are attached together at mating surfaces. Each mating surface defines a surface geometry which approximates a developable surface having parallel ruling lines. The developable surfaces are formed by machining.

Abstract: A hybrid structure comprises a metallic built-up sandwich structure, and a monolithic superplastic formed and diffusion bonded structure joined to the built-up sandwich structure.

Abstract: An aircraft engine anti-icing barrier assembly having a slip joint subassembly, a barrier subassembly, and a vapor barrier subassembly. The slip joint subassembly has a forward end for fixed attachment at a forward bulkhead of an aircraft engine, and has an aft end having a sliding joint. The barrier subassembly is attached to an aft side of an aft bulkhead and inserted through the aft bulkhead. The barrier subassembly has two mount pads with an upper mount pad and a lower mount pad configured for joined sealed attachment around the slip joint subassembly to form a barrier between an engine fan case compartment and an aft compartment in an engine inlet. The vapor barrier subassembly is attached to the aft side of the aft bulkhead and adjacent the barrier subassembly, has a boot element and a boot element retainer, and forms a vapor barrier to the slip joint subassembly.

Abstract: Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed.

Abstract: In one embodiment, a gas turbine engine assembly comprises an engine assembly disposed about a longitudinal axis, a core nozzle positioned adjacent the engine assembly to direct a core flow generated by the engine assembly, a fan nozzle surrounding at least a portion of the core nozzle to direct a fan flow, wherein the core nozzle defines a plenum to receive a portion of the core stream flow from the core nozzle and a thermoelectric generator assembly positioned in the plenum. Other embodiments may be described.

Abstract: Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed.

Abstract: Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a first support structure to be coupled to a wing, a second support structure to be coupled to the wing and a nacelle. The support structures are coupled to opposite sides of the nacelle. The support structures are to be coupled to opposite sides of an engine to enable thrust loads to be reacted through the support structures to the wing.

Abstract: A hybrid structure comprises a metallic built-up sandwich structure, and a monolithic superplastic formed and diffusion bonded structure joined to the built-up sandwich structure.

Abstract: A thermoelectric generator assembly may comprise a frame that may include a first frame member and a second frame member. The first frame member and the second frame member are adapted to retain one or more thermoelectric generator devices in position therebetween for transferring heat energy through the one or more thermoelectric generator devices from a heat source to a heat sink to generate electrical energy. The thermoelectric generator assembly may also include a spacer positioned between the first frame member and the second frame member. A power bus may be included to provide the electrical energy generated by the one or more thermoelectric generator devices for powering an electrical device.

Abstract: There is provided an aircraft engine anti-icing (EAI) barrier assembly. The aircraft EAI barrier assembly has a slip joint subassembly having a forward end and an aft end. The forward end is configured for fixed attachment at a forward bulkhead of an engine of an aircraft, and an aft end with a sliding joint. The aircraft EAI barrier assembly has a barrier subassembly attached through an aft bulkhead and has two mount pads configured for joined sealed attachment around the aft end of the slip joint subassembly to form a barrier to an engine inlet of the engine.

Abstract: A nacelle inlet is provided for a turbo-fan engine for an aircraft. The nacelle inlet includes a lip skin having first and second pad-ups, an inner barrel including a forward flange and a bulkhead. The bulkhead, the lip skin and the inner barrel are attached together at mating surfaces. The bulkhead and the lip skin are attached together at mating surfaces. Each mating surface defines a surface geometry which approximates a developable surface having parallel ruling lines. The developable surfaces are formed by machining.

Abstract: A heat exchanger and associated method are provided that may eliminate or reduce the need for an external mechanical or electrical power source to drive the fan by utilization, instead, of a Stirling engine. A heat exchanger includes a plurality of coils configured to carry a primary fluid. The heat exchanger also includes a fan including a plurality of fan blades configured to force a secondary fluid across the plurality of coils to facilitate heat transfer between the primary and secondary fluids. The heat exchanger also includes a Stirling engine operably connected to the fan and configured to cause rotation of the fan blades. A corresponding method is also provided.