Abstract: An assembly for a turbine engine includes a nozzle structure, a septum and a plurality of cooling vanes. The nozzle structure includes a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis. The septum axially and circumferentially overlaps the first platform with a cooling cavity formed by and radially between the septum and the first platform. The septum includes a plurality of cooling apertures aligned with the nozzle vanes. Each of the cooling apertures extends radially through the septum to the cooling cavity. The cooling cavity includes a cavity outlet fluidly coupled to a flowpath. The cooling vanes are arranged circumferentially about the axis and project from the first platform into the cooling cavity. The cooling vanes are located between the cooling apertures and the cavity outlet along the cooling cavity.

Abstract: An auxiliary power unit air bleed system with an expansion valve including a compressor having a bleed air discharge line; and an expansion valve fluidly coupled to the bleed air discharge line, wherein the expansion valve is configured to reduce a pressure of bleed air flowing through the bleed air discharge line and reduce a temperature of the bleed air.

Abstract: A system and method for relieving pressure from a passenger cabin of an aircraft during a decompression event with a resettable decompression system. The system includes a resettable decompression retainer having a swing arm pivotably connected to a base. The swing arm has a bias relative to the base provided by a spring connected to both the swing arm and the base. The swing arm engages a slip fitting that is attached to a ceiling panel of the aircraft. The resettable decompression system allows the ceiling panel to move thus allowing air pressures between a passenger cabin and a crown space to equalize. After a decompression event, the resettable decompression retainer can be manually reset without the use of tools and without repairing or replacing the resettable decompression retainer.

Abstract: A powerplant is provided that includes an electric machine, a turbine engine and a fluid circuit. The turbine engine is operatively coupled to the electric machine. The turbine engine includes a flowpath, a compressor section, a combustor section and a turbine section. The flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath. The compressor section includes a shroud forming a peripheral boundary of the flowpath. The fluid circuit includes a passage, a port and a conduit. The passage is within the electric machine. The port extends through the shroud to the flowpath. The conduit fluidly couples the passage to the port.

Abstract: A method of operation is provided during which a heating fluid is directed through a first passage into a combustor section to heat a component within the combustor section when an aircraft engine is in a first standby mode. The aircraft engine includes a flowpath, a compressor section, the combustor section, a turbine section and an exhaust section. The flowpath extends through the compressor section, the combustor section, the turbine section and the exhaust section from an inlet into the flowpath to an exhaust from the flowpath. The heating fluid is directed through a second passage into the exhaust section when the aircraft engine is in a second mode. The heating fluid is directed through the second passage bypasses the turbine section.

Abstract: A support box apparatus includes longitudinal members that span forward to aft and transverse members that span inboard to outboard between the longitudinal members. The longitudinal members and the transverse members are formed of composite honeycomb sandwich panels. The support box apparatus also includes attachment components configured to couple the longitudinal members or the transverse members to structural components of an aircraft, electrical wiring attached to the longitudinal members or the transverse members, environmental control system (ECS) ducting attached to the longitudinal members or the transverse members, and life support lines attached to the longitudinal members or the transverse members.

Abstract: A system and method for relieving pressure from a passenger cabin of an aircraft during a decompression event with a resettable decompression system. The system includes a resettable decompression retainer having a swing arm pivotably connected to a base. The swing arm has a bias relative to the base provided by a spring connected to both the swing arm and the base. The swing arm engages a slip fitting that is attached to a ceiling panel of the aircraft. The resettable decompression system allows the ceiling panel to move thus allowing air pressures between a passenger cabin and a crown space to equalize. After a decompression event, the resettable decompression retainer can be manually reset without the use of tools and without repairing or replacing the resettable decompression retainer.

Abstract: A manufacturing method is provided that includes forming a radial flow turbine blade of a radial flow turbine rotor for a gas turbine engine. The radial flow turbine blade includes an internal cooling passage. At least a portion of the internal cooling passage has a passage thickness of less than 20 mils.

Abstract: An assembly to connect a panel to a support member. The assembly may include a saddle fitting configured to connect to the support member and including first and second plates. A back fitting may be positioned between the second plate of the saddle fitting and a second face of the panel. An index fitting includes a flange that may be positioned between the first plate of the saddle fitting and a first face of the panel, and a boss that extends outward from the flange and through the opening in the panel. The index fitting is wider than the panel and sized to fit within the gap of the saddle fitting with a first end of the index fitting contacting against the first plate and a second end of the index fitting contacting against the second plate. One or more fasteners may connect the saddle fitting to the index fitting.

Abstract: An assembly to connect a panel to a support member. The assembly may include a saddle fitting configured to connect to the support member and including first and second plates. A back fitting may be positioned between the second plate of the saddle fitting and a second face of the panel. An index fitting includes a flange that may be positioned between the first plate of the saddle fitting and a first face of the panel, and a boss that extends outward from the flange and through the opening in the panel. The index fitting is wider than the panel and sized to fit within the gap of the saddle fitting with a first end of the index fitting contacting against the first plate and a second end of the index fitting contacting against the second plate. One or more fasteners may connect the saddle fitting to the index fitting.

Abstract: An apparatus adapted for hanging an article on a fence rail is provided and comprised of a rod having a proximate end and a distal end. The rod has three bends bounded by four portions. The first bend forms a substantially 90 degree angle between the first portion and the second portion. The second bend is a substantially 90 degree angle between the second portion and the third portion. The first portion, the second portion, and third portion being substantially in a first plane. The third bend forms a substantially 90 degree angle between the third portion and the fourth portion. The fourth portion initially extends parallel to the second portion and subsequently forming a radius. The fourth portion is in a second plane substantially perpendicular to the first plane.

Abstract: A bifurcation assembly for a gas turbine engine is disclosed and includes a housing defining an inner cavity. A first partition and a second partition extend across the inner cavity and define a buffer area therebetween. Openings through the first and second partitions define passageway for supply conduits. A control device governs the flow of a purge gas into the buffer area for blocking the spread of fire. The purge gas provides a barrier to the spread of fire and heat through the bifurcation assembly.

Abstract: A pulse detonation combustor may include a valve and a tubular combustor wall, which forms an airflow inlet and a combustion chamber. The valve may be configured to selectively fluidly couple the airflow inlet with the combustion chamber. The valve may include a center body and an annular projection. The center body and the projection may be configured to sealingly engage with one another.

Abstract: A rocket engine system with a fuel conversion system in communication with a gas generator.

Abstract: A bifurcation assembly for a gas turbine engine is disclosed and includes a housing defining an inner cavity. A first partition and a second partition extend across the inner cavity and define a buffer area therebetween. Openings through the first and second partitions define passageway for supply conduits. A control device governs the flow of a purge gas into the buffer area for blocking the spread of fire. The purge gas provides a barrier to the spread of fire and heat through the bifurcation assembly.

Abstract: A rocket engine system with a fuel conversion system in communication with a gas generator.

Abstract: A fuel conditioning system includes a fuel supply, cracking vessel, heat source and fuel delivery line. The cracking vessel breaks carbon-carbon bonds of hydrocarbons present in the fuel. The heat source provides thermal energy to the cracking vessel for breaking the carbon-carbon bonds. The fuel delivery line delivers cracked fuel to an internal combustion engine. An internal combustion engine system includes an engine having a combustion chamber and fuel injection system, a fuel supply, a fuel conditioning system and a fuel delivery line. The fuel conditioning system includes a heat loop that receives thermal energy and a cracking vessel that breaks carbon-carbon bonds of fuel hydrocarbons using the thermal energy. The fuel delivery line delivers cracked fuel to the engine. A method for operating an internal combustion engine includes delivering fuel to a cracking vessel, thermally cracking the fuel, delivering cracked fuel to an engine and combusting the cracked fuel.

Abstract: A fence hanger apparatus is generally comprised of two vertical hanging support brackets. The two vertical hanging support brackets each have an upper portion terminating in a U-shaped hook for hanging the apparatus over the top rail of a fence, and a lower portion. A vertical member has an upper end and a lower end and is positioned approximately midway between the two vertical hanging support brackets and is substantially parallel to the upper portions of the two vertical hanging brackets. The upper end of the vertical member extends substantially to the same height as the U-shaped hooks. The vertical member has a front face, a rear face and two side faces. The front face of the vertical member is provided with means for attaching hanging members. A U-shaped latch is pivotally mounted to the lower end of the vertical member for attaching the apparatus to a vertical post of a fence. The lower portions of the two hanging support brackets are secured to the lower end of the vertical member with securing means.

Abstract: A fence hanger apparatus is generally comprised of two vertical hanging support brackets. The two vertical hanging support brackets each have an upper portion terminating in a U-shaped hook for hanging the apparatus over the top rail of a fence, and a lower portion. A vertical member has an upper end and a lower end and is positioned approximately midway between the two vertical hanging support brackets and is substantially parallel to the upper portions of the two vertical hanging brackets. The upper end of the vertical member extends substantially to the same height as the U-shaped hooks. The vertical member has a front face, a rear face and two side faces. The front face of the vertical member is provided with means for attaching hanging members. A U-shaped latch is pivotally mounted to the lower end of the vertical member for attaching the apparatus to a vertical post of a fence. The lower portions of the two hanging support brackets are secured to the lower end of the vertical member with securing means.

Abstract: A rocket engine system includes a combustion chamber defining a centerline axis, an oxidizer supply, a first fuel delivery circuit connected to a fuel supply, a second fuel delivery circuit connected to the fuel supply, and an injector assembly positioned at the combustion chamber. The injector assembly includes a faceplate having a plurality of openings therethrough, a first injector element connected to the first fuel delivery circuit and extending into one of the openings in the faceplate, and a second injector element connected to the second fuel delivery circuit and extending into another of the openings in the faceplate. Annular oxidizer outlets are formed at the openings in the faceplate and connected to the oxidizer supply to deliver oxidizer to the combustion chamber.