Abstract: A solid rocket propellant includes a hydroxy-terminated caprolactone ether binder and an oxidizer. The propellant may be disposed of by contacting it with an aqueous solution of 12 N NaOH or 6 N HCl at a temperature of about 140° F. for about 24 hours to decompose the binder. Solids remaining in the solution after the binder decomposes are removed.

Abstract: An ignitor that energizes a hydrogen fuel into a high temperature plasma which is then injected into a mixture of fuel and oxidizer within a combustion chamber.

Abstract: A solid rocket propellant includes a binder that is a linear block co-polymer of caprolatone and tetramethylene ether and an oxidizer. The propellant may be disposed of by contacting it with an aqueous solution of 12 N NaOH or 6 N HCl at a temperature of about 140° F. for about 24 hours to decompose the binder. Solids remaining in the solution after the binder decomposes are removed.

Abstract: A gas turbine engine seal system includes a rotating member having an abrasive tip disposed in rub relationship to a stationary, abradable seal surface. The abrasive tip comprises a zirconium oxide abrasive coat having a columnar structure that is harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface.

Abstract: A thermal barrier coating may be applied by depositing a MCrAIY bond coat onto a superalloy substrate, wherein M stands for Ni, Co, Fe, or a mixture of Ni and Co. Undesired oxides and contaminants are removed from the MCrAIY bond coat with an ionized gas stream cleaning process, such as a reverse transfer arc process. An adherent aluminum oxide scale is formed on the MCrAIY bond coat and a ceramic layer is deposited on the aluminum oxide scale by physical vapor deposition to form a columnar structure.

Abstract: A gas turbine engine component coated with a thermal barrier coating that includes a metallic bond coat and a ceramic top coat is repaired by removing the ceramic top coat from an engine-run gas turbine engine component and inspecting the component. A metallic flash coat is applied to at least a portion of the component. A ceramic top coat is then applied over predetermined portions of the component, including the portion to which the metallic flash coat was applied.

Abstract: A corrosion inhibited fuel mixture includes a hydrocarbon fuel, at least one vanadium composition, and a yttrium composition. The concentration of the yttrium composition in the mixture provides at least a stoichiometric amount of yttrium for a substantially complete reaction between the yttrium and V.sub.2 O.sub.5 formed from the vanadium composition when the mixture is burned. The yttrium and V.sub.2 O.sub.5 react to form YVO.sub.4. One particular yttrium composition useful as a hydrocarbon fuel soluble, water stable vanadium corrosion inhibitor incorporates a yttrium ester having at least four carbon atoms and a hydrocarbon fuel soluble chelating agent that includes 2,4-pentanediene. The complex has a molar ratio of 2,4-pentanediene to yttrium of up to 5:1.

Abstract: A fiber reinforced glass matrix composite has a glass matrix or glass ceramic and a plurality of primary and secondary reinforcing fibers dispersed in the matrix. The primary fibers may be continuous or discontinuous. The secondary fibers are discontinuous. The secondary reinforcing fibers which are shorter than the primary fibers fill regions of the matrix not filled with the primary reinforcing fibers. The composite may be made by uniformly distributing the secondary reinforcing fibers in a dispersant. A glass powder is mixed in a carrier liquid to create a slurry and the secondary reinforcing fibers and dispersant are slowly added to the slurry so the fibers uniformly disperse as they are added. A binder is also added to the slurry. A continuous fiber is impregnated with the slurry and the impregnated fiber is dried to remove the carrier liquid. The impregnated yarn is cut to a suitable length and molded by a suitable molding method to form a fiber reinforced glass matrix composite.

Abstract: A method of joining adjacent, non-coplanar, fiber reinforced composite structures includes machining a plurality of serrations (4) into an edge (6) of a consolidated first fiber reinforced composite structure (2) such that reinforcing fibers continue from a main body (14) of the first fiber reinforced composite structure (2) into the serrations (4). One or more reinforcing fiber plies (16) are then laid up around the serrations (4) to form an unconsolidated second structure such that the serrations (4) protrude through at least one reinforcing fiber ply (16). In addition to the one or more reinforcing fiber plies (16), the unconsolidated second structure also includes a matrix precursor. Sufficient heat and pressure are applied to the unconsolidated second structure and the serrations (4) to consolidate the second structure into a fiber reinforced composite structure (8).

Abstract: A superconductor magnetic bearing includes a shaft (10) that is subject to a load (L) and rotatable around an axis of rotation, a magnet (12) mounted to the shaft, and a stator (14) in proximity to the shaft. The stator (14) has a superconductor thin film assembly (16) positioned to interact with the magnet (12) to produce a levitation force on the shaft (10) that supports the load (L). The thin film assembly (16) includes at least two superconductor thin films (18) and at least one substrate (20). Each thin film (18) is positioned on a substrate (20) and all the thin films are positioned such that an applied magnetic field from the magnet (12) passes through all the thin films. A similar bearing in which the thin film assembly (16) is mounted on the shaft (10) and the magnet (12) is part of the stator (14) also can be constructed.

Abstract: A method of joining adjacent, non-coplanar, fiber reinforced composite structures includes machining a plurality of serrations (4) into an edge (6) of a consolidated first fiber reinforced composite structure (2) such that reinforcing fibers continue from a main body (14) of the first fiber reinforced composite structure (2) into the serrations (4). One or more reinforcing fiber plies (16) are then laid up around the serrations (4) to form an unconsolidated second structure such that the serrations (4) protrude through at least one reinforcing fiber ply (16). In addition to the one or more reinforcing fiber plies (16), the unconsolidated second structure also includes a matrix precursor. Sufficient heat and pressure are applied to the unconsolidated second structure and the serrations (4) to consolidate the second structure into a fiber reinforced composite structure (8).

Abstract: Directionally Solidified Eutectic Reinforcing FibersEutectic reinforcing fibers for high temperature composites include eutectic mixtures such as Al.sub.2 O.sub.3 --Y.sub.2 O.sub.3, Cr.sub.2 O.sub.3 --SiO.sub.2, MgO--Y.sub.2 O.sub.3, CaO--NiO, and CaO--MgO. The fibers may be made by several solidification processes. The edge defined film fed growth process (EFG), however, may be especially appropriate. In this process, a seed having a known composition contacts the surface of a eutectic melt in a crucible and forms a molten film. In the present invention, the composition of the seed may be equal to the composition of the eutectic melt. As the seed is pulled upward, the molten film solidifies to form a eutectic fiber. Directional solidification occurs toward the melt.

Abstract: The energy storage flywheel device (6) includes a plurality of annular shaped composite sections (8) and an annular shaped insert (10). The insert (10) has a specific radial strength substantially greater than the composite sections' specific radial strength. The composite sections (8) and the insert (10) are alternately stacked such that they have a common axis of rotation. They are bonded to each other such that shear stress is transferred between the composite sections (8) and insert (10). In some applications, the flywheel (6) may comprise at least one annular shaped metal matrix composite section (8).

Abstract: A fiber is coated with boron carbide by contacting the fiber with a reaction mixture of a boron source and a carbon source at a temperature of at least about 1050.degree. C. such that the boron source and carbon source react with each other to produce a boron carbide coating on the fiber. The fiber comprises aluminum oxide, SiC, or Si.sub.3 N.sub.4 and the boron carbide coating comprises up to about 40 atomic percent boron.

Abstract: A stream of hydrocarbon fuel is catalytically decomposed to produce hydrogen and lower molecular weight fuel fragments, which may separated by molecular size. The hydrogen and low molecular weight fuel fragments are introduced along with a stream of nondecomposed hydrocarbon fuel into the combustor of a high speed propulsion unit. The method results in a wider combustor operating range, with higher combustion rates and increased flame stability, achieved through more rapid diffusional mixing. The process effectively extends the operating limits of gas turbines, and especially ramjet and scramjet combustors.

Abstract: A metal nitride powder can be made by heating a reactant powder that includes an oxide or hydroxide of Al, Ti, or Zr to a reaction temperature in a nonreactive atmosphere. The heated reactant powder is contacted with a gaseous reactant mixture comprising a nitrogen source and a carbon source. The molar ratio of nitrogen to carbon in the gaseous reactant mixture is at least about 15. The reactant powder is maintained at the reaction temperature for a sufficient time to convert a portion of it to metal nitride powder.

Abstract: The flywheel containment device (2) includes a shaft (4), defining an axis of rotation, and a flywheel (6) having an annular shaped cross-section perpendicular to the axis of rotation. The flywheel (6) is connected to the shaft (4) and has an outer diameter (5) and an inner diameter (3). The containment device (2) also comprises an annular shaped honeycomb structure (8) with an annular shaped honeycomb layer (10) having an outer diameter and an inner diameter greater than the outer diameter of the flywheel (6). The honeycomb layer (10) comprises a plurality of pores (11) that are open on the inner diameter of the honeycomb layer (10) to trap dust created if the flywheel (6) fails. The honeycomb layer (10) is positioned around the outer diameter of the flywheel (6) such that the honeycomb structure (8) is independent from the flywheel (6).

Abstract: A polymeric skin can be molded by heating a mold surface to a temperature sufficient to melt a casting material and controllably projecting particles of the casting material toward the heated mold surface. Particles of the casting material that impinge on the mold surface melt and adhere to the mold surface. The mold surface is cooled to a temperature at which the casting material solidifies to form a skin. By varying the amount or type of material projected toward the heated mold surface, the method can make multilayer skins, skins from more than one material with a graded transition between materials, multicolor skins, and skim having a controlled, nonuniform thickness.

Abstract: A hydrogen storage device (2) includes a vessel (4) and a hydrogen storage bed (6) disposed in the vessel (4). The hydrogen storage bed (6) includes a polymeric material (8) having a plurality of micropores less than about 1 nm in diameter and at least one hydride forming metal (10) imbedded within the polymeric material (8). The device also includes means for optically and thermally decomposing the metal hydride to release hydrogen and means for conveying hydrogen into and out of the storage device (2). The hydrogen storage bed (6) may be made by distributing a hydride forming metal (10) within the polymeric material (8) while the polymeric material (8) is in an uncured state. A metal hydride may be formed in the presence of hydrogen at a pressure such that the hydrogen bonds to the hydride forming metal (10) to form a metal hydride within the polymeric material (8).

Abstract: A heat pump that includes organic hydride (12) and metal hydride (2) systems cools a conditioned space (6) by transferring heat from the conditioned space to a metal hydride bed (4), thereby decomposing a metal hydride in the bed to form H.sub.2. The H.sub.2 flows to a vapor space (14) in the liquid hydride system (12) and reacts with a dehydrogenation product at a catalytic surface (32) in the vapor space to form an organic hydride and an exothermic heat of reaction. The heat pump also may be used to upgrade waste heat by transferring heat from a relatively low temperature heat source to decompose the metal hydride. The exothermic heat of reaction may then be removed from the vapor space and used for space heating. In both embodiments, the metal hydride bed (4) may be regenerated by supplying an endothermic heat of reaction to the catalytic surface (32), thereby dehydrogenating the organic hydride to form H.sub.2. The H.sub.