Abstract: A hanger system includes a pin with a head section which defines a pin axis. A clip assembly captures the head section to permit movement of the pin within a hanger in a direction transverse to the pin axis. A fastener which retains the clip assembly to the hanger.

Abstract: An assembly for separating debris from a pressurization air flow adjacent to a bearing compartment seal includes a baffle and a capture annulus. The baffle is disposed in the pressurization air flow upstream of the compartment seal. The capture annulus is positioned adjacent the baffle and has a cavity to collect the debris.

Abstract: A fuel nozzle air swirler assembly has a slotted cap to provide stress-relief. The stress-relief slits in the cap have an axial and a tangential component to impart a swirl to the air leaking therethrough in the same direction as that of the air exiting the swirler body.

Abstract: An anti-icing system and method for an aircraft engine nacelle. The nacelle has an inlet lip that defines a leading edge of the nacelle and has a cross-sectional shape and oppositely-disposed exterior and interior surfaces. An anti-icing system contacts at least the inlet lip of the nacelle. The anti-icing system includes at least one heating element having a cross-sectional shape that conforms to the cross-sectional shape of the inlet lip and in which carbon nanotubes are oriented and arranged to conduct electrical current through the heating element. Passing an electrical current through the heating element causes Joule heating of the heating element and heating of the inlet lip by thermal conduction.

Abstract: A continuous detonation wave engine (CDWE) is disclosed. An example embodiment includes a generally annular combustion chamber dimensioned to allow a fuel mixture to detonate, a mixing chamber, and a fuel mixture channel that provides for fluid communication between the mixing chamber and the combustion chamber. At least part of the fuel mixture channel features a quenching structure dimensioned to substantially prevent detonation from spreading from the combustion chamber via the fuel mixture channel to the mixing chamber. Other embodiments are described and claimed.

Abstract: A new micro electro-mechanical system (MEMS) satellite thruster is described. An example of the new MEMS thruster includes a propellant layer on a flexible substrate to make a rolled propellant that can be mounted on a reel-to-reel system. Sections of the rolled propellant are rolled over a separate activation blast plate to initiate the propellant on that section, providing thrust. The new MEMS thruster can also be made with segmented propellant sections. The new MEMS thruster can be made in a variety of configurations and as a modular system that can be attached to existing satellites.

Abstract: An apparatus includes an inlet conduit assembly surrounding a gas flow path and a combustor arranged downstream of the inlet conduit assembly. The inlet conduit assembly includes a thermoelectric (TE) device configured to convert heat into electrical energy, a gas flow conduit arranged between the gas flow path and the TE device, and a resilient member configured to bias the TE device into contact with the gas flow conduit.

Abstract: High bleed flow muffling systems are disclosed. Example muffling devices according to at least some aspects of the present disclosure may include a first orifice plate and a second orifice plate at least partially defining a plenum arranged to receive the flow of a compressible fluid. The first orifice plate and the second orifice plate may be arranged to produce cross-impinging flow such that flow through the orifices of the first orifice plate into the plenum is directed at the wall of the second orifice plate and such that flow through the orifices of the second orifice plate is directed at the wall of the first orifice plate. Some example embodiments may include an inlet flow restrictor disposed upstream of the first and second orifice plates.

Abstract: A combustor liner is disclosed. The combustor liner includes an upstream portion, a downstream end portion extending from the upstream portion along a generally longitudinal axis, and a cover layer associated with an inner surface of the downstream end portion. The downstream end portion includes the inner surface and an outer surface, the inner surface defining a plurality of microchannels. The downstream end portion further defines a plurality of passages extending between the inner surface and the outer surface. The plurality of microchannels are fluidly connected to the plurality of passages, and are configured to flow a cooling medium therethrough, cooling the combustor liner.

Abstract: A fluid-conveying device including an inner tubular member with a circumferential end portion, a non-elastomeric ring received in a depression of the end portion, and an outer tubular member. The ring has a peripheral surface with a rounded contour defined along a longitudinal direction configured to remain out of the depression to engage the outer tubular member and facilitate sealing thereof.

Abstract: An apparatus includes a thermoelectric (TE) device, a gas flow conduit proximate to one side of the thermoelectric device, a plurality of flexible tubes proximate to a second side of the thermoelectric device, and a spring to control contact force between the flexible tubes and the thermoelectric device. The spring comprises a coil spring at least partially circumscribing the gas flow conduit. The thermoelectric device converts a temperature differential between the flexible tubes and the gas flow conduit into electrical energy.

Abstract: A gas turbine engine arrangement comprises a first gas turbine engine, a second gas turbine engine, a differential gearbox and an electrical generator. The differential gearbox has a first input drive, a second input drive and an output drive. The output drive of the differential gearbox is arranged to drive the electrical generator via an external, accessory, gearbox. The external, accessory, gearbox drives other accessories. The first gas turbine is arranged to drive the first input drive of the differential gearbox and the second gas turbine engine is arranged to drive the second input drive of the differential gearbox. The electrical generator and accessories are driven at a constant frequency speed/frequency.

Abstract: In order to reduce a manufacturing cost and a running cost, casings each housing a combustion oscillation detecting device are attached in an alternating manner to cross-flame tubes by which a plurality of combustors arranged annularly in a combustor casing are connected to each other.