Abstract: A seal for bridging an interface between an aircraft exhaust deck and a trailing edge of an aircraft exhaust system includes a sheet, a spacing element, and a tensioning element. The sheet has a fixed end, a cover portion, a movable portion, and a free end. The fixed end is anchored to the trailing edge. The cover portion extends upstream from the fixed end and across the interface. The movable portion is located adjacent the aircraft exhaust deck. The spacing element engages the movable portion and defines a gap for cooling air between the movable portion and the aircraft exhaust deck. The tensioning element is attached to the free end and provides tensioning force keep the cover portion taut.

Abstract: An integrated additive manufacturing cell (IAMC) that combines conventional manufacturing technologies with additive manufacturing processes is disclosed. Individual IAMCs may be configured and optimized for specific part families of complex components, or other industrial applications. The IAMCs incorporate features that reduce hardware cost and time and allow for local alloy tailoring for material properties optimization in complex components.

Abstract: An integrated additive manufacturing cell (IAMC) that combines conventional manufacturing technologies with additive manufacturing processes is disclosed. Individual IAMCs may be configured and optimized for specific part families of complex components, or other industrial applications. The IAMCs incorporate features that reduce hardware cost and time and allow for local alloy tailoring for material properties optimization in complex components.

Abstract: An integrated additive manufacturing cell (IAMC) that combines conventional manufacturing technologies with additive manufacturing processes is disclosed. Individual IAMCs may be configured and optimized for specific part families of complex components, or other industrial applications. The IAMCs incorporate features that reduce hardware cost and time and allow for local alloy tailoring for material properties optimization in complex components.

Abstract: An engine cooling system includes a combustion chamber assembly configured to generate detonation waves and a first vapor cooling assembly. The combustion chamber assembly defines a flowpath between an inner liner and an outer liner. The first vapor cooling assembly includes a vaporization section located adjacent to the flowpath and a condenser section spaced from the flowpath, and is configured to transport thermal energy from the vaporization section to the condenser section through cyclical evaporation and condensation of a working medium sealed within the first vapor cooling assembly.

Abstract: A process for solid state deposition of a material onto a workpiece includes the steps of providing a rod of metallic deposition material, exerting pressure at one end of the rod to move the metallic deposition material into a deposition zone, rotating the rod while the pressure is being exerted to generate frictional heat when the rod contacts a surface of the workpiece, and raising the temperature of the metallic deposition material to reduce the amount of frictional heat which needs to be generated during the rotating step and to produce a microstructure which is substantially free of porosity and which has a fine grain size.

Abstract: A pulsed combustion apparatus includes a conduit having an outer wall and an inner wall. The inner wall has a number of apertures. An interior space is separated from the outer wall by the inner wall. An induction system is positioned to cyclicly admit charges to the interior space. An ignition system is positioned to ignite the charges. Flow directing surfaces are positioned to at least cyclicly direct cooling air through the apertures.

Abstract: A pulsed combustion device includes a support structure and a combustor carousel supported by the support structure and rotating relative thereto about an axis. The carousel has a number of combustion conduits in a circumferential array. Each conduit cyclically receives a charge and discharges combustion products of the charge.

Abstract: Distributed initiation (e.g., multipoint or continuous) is utilized to obtain constant volume-like combustion performance in a pulse combustion device in the absence of detonation. A number of such devices may be utilized as turbine engine combustors.

Abstract: A turbine engine has a circumferential array of combustion chamber conduits downstream of the compressor and upstream of the turbine. Means are provided for directing oxygen-containing gas from the compressor to the conduits so as to cyclically feed a gas charge into each conduit through its first port and permit discharge of combustion products of the charge and fuel through both the first and second ports.

Abstract: A pulsed combustion device includes a support structure and a combustor carousel supported by the support structure and rotating relative thereto about an axis. The carousel has a number of combustion conduits in a circumferential array. Each conduit cyclically receives a charge and discharges combustion products of the charge. A venturi effect may help control fuel/air charge leakage from a flowpath spanning the carousel and a stationary manifold.

Abstract: A pulse detonation engine (10) is provided with an aerovalve (14) for controlling the pressure of injected propellants (Ox, Fuel) in an open-ended detonation chamber (26). The propellants are injected at such pressure and velocity, and in a direction generally toward a forward thrust wall end (16) of the detonation chamber (26), an aerovalve (14) is formed which effectively inhibits or prevents egress of the propellant from the detonation chamber (26). A shock wave (34) formed by the injected propellant acts, after reflection by the thrust wall end (16) and in combination with the aerovalve (14), to compress and conserve, or increase, the pressure of the injected propellant. Carefully timed ignition (28) effects a detonation pulse under desired conditions of maintained, or increased, pressure. Termination of the propellant injection serves to “open” the aerovalve (14), and exhaust of the combusted propellants occurs to produce thrust.

Abstract: A pulse detonation engine (10) is provided with an aerovalve (14) for controlling the pressure of injected propellants (Ox, Fuel) in an open-ended detonation chamber (26). The propellants are injected at such pressure and velocity, and in a direction generally toward a forward thrust wall end (16) of the detonation chamber (26), an aerovalve (14) is formed which effectively inhibits or prevents egress of the propellant from the detonation chamber (26). A shock wave (34) formed by the injected propellant acts, after reflection by the thrust wall end (16) and in combination with the aerovalve (14), to compress and conserve, or increase, the pressure of the injected propellant. Carefully timed ignition (28) effects a detonation pulse under desired conditions of maintained, or increased, pressure. Termination of the propellant injection serves to “open” the aerovalve (14), and exhaust of the combusted propellants occurs to produce thrust.

Abstract: A compressor blade that has a blade root, an airfoil having a first end, and a second end opposite the first end, the second end having at least one edge, and the airfoil is made of a first material having a first modulus of elasticity. A blade platform connects the blade root to the first end of the airfoil, and a flexible seal is connected to the airfoil adjacent the second end, and the seal is made of a second material having a modulus of elasticity that is substantially less than the first modulus of elasticity.