Abstract: A cushioning structure includes a first layer of a three-dimensional structured mat of extruded entangled filaments, the cushioning structure includes a second layer of a three-dimensional structured mat of extruded entangled filaments, and the cushioning structure includes an intermediate layer between the first layer of the three-dimensional structured mat and the second layer of the three-dimensional structured mat.

Abstract: A method is provided involving a fairing for a turbine engine. During this method, a detail is provided. The detail includes a carrier and an exterior layer bonded to the carrier. The carrier is configured from or otherwise includes fiber-reinforced composite material. The exterior layer is configured from or otherwise includes polymer material. The detail is arranged with the fairing. The fairing includes an exterior side and an edge. The detail covers and extends along at least a portion of the exterior side. The detail wraps at least partially around the edge. The carrier and at least a first overhang portion of the exterior layer are bonded to the fairing.

Abstract: A folded core structure formed from an uncut flat body, has a plurality of consecutive 3D-structures and connecting areas each formed by plastic deformation, and includes first and second primary surfaces oriented plane-parallel to each other. The first and second primary surfaces include a first secondary surface extending over the entire width of the folded core structure and extending over a part of the length of the folded core structure. The first secondary surface is oriented parallel to the first primary surface, and the first secondary surface is located at a distance from the first primary surface between the first and second primary surfaces. A channel for fluid flow at least along the width of the folded core structure is provided. The first and/or second primary surface is/are configured to provide dimensional stability under a compression force applied perpendicular to the first primary surface of the folded core structure.

Abstract: A cushioning structure including a first layer of a three-dimensional structured mat of extruded entangled filaments, a second layer of a three-dimensional structured mat of extruded entangled filaments and an intermediate layer between the first layer and the second layer.

Abstract: A method of immobilizing a contaminant within a component includes identifying the contaminant. The component is thermally processed via a specific thermal cycle related to the contaminant. The specific thermal cycle is performed within an inert environment relative to a substrate. The specific thermal cycle is configured to effect a controlled evaporation of volatiles of the contaminant and a controlled coking of remaining contaminant.

Abstract: An annular bushing includes an annular cylindrical portion with a flange that defines a fastener aperture along an axis. A multiple of spacers extend from an outer surface of the annular cylindrical portion and the flange. The multiple of spacers are operable to control a bond line thickness.

Abstract: A non-destructive method for determining an amount of temperature exposure to a Bismaleimide Resin (BMI) matrix substrate, the method includes determining component data of a Bismaleimide Resin (BMI) matrix component via fourier transform infrared (FTIR) spectroscopy; correlating the component data to model data to determine a structural debit from temperature exposure; and bounding a structurally damaged area in response to the correlating.

Abstract: An annular bushing includes an annular cylindrical portion with a flange that defines a fastener aperture along an axis. A multiple of spacers extend from an outer surface of the annular cylindrical portion and the flange. The multiple of spacers are operable to control a bond line thickness.

Abstract: A method of immobilizing a contaminant within a component includes identifying the contaminate; and thermally processing the component via a specific thermal cycle related to the contaminate. A method of repairing a component includes immobilizing a contaminant within the component; and weld repairing the component subsequent to immobilizing the contaminant. An aerospace component includes a honeycomb structure with a thermally decomposed contaminate and a weld repair.

Abstract: A non-destructive method for determining an amount of temperature exposure to a Bismaleimide Resin (BMI) matrix substrate, the method includes determining component data of a Bismaleimide Resin (BMI) matrix component via fourier transform infrared (FTIR) spectroscopy; correlating the component data to model data to determine a structural debit from temperature exposure; and bounding a structurally damaged area in response to the correlating.

Abstract: Use of a liquid composition for lubricating conveyor belts is provided, said liquid composition being suitable for producing a “dry” lubricant film on a surface by discontinuous application thereof, wherein the liquid composition can also be used for continuous application to a conveyor belt surface, with or without further dilution with water, to remove incidental spillages of extraneous material from the conveyor belt surface without loss of the required lubricity. This liquid composition was found to exhibit remarkably good durability.

Abstract: Thermal transfer ribbons which employ a reflective sensor marker of a small size for detecting the end of the ribbon and also thermal transfer ribbons which employ a reflective sensor marker and a transparent sensor marker for detecting the end of the ribbon.

Abstract: Use of a liquid composition for lubricating conveyor belts is provided, said liquid composition being suitable for producing a “dry” lubricant film on a surface by discontinuous application thereof, wherein the liquid composition can also be used for continuous application to a conveyor belt surface, with or without further dilution with water, to remove incidental spillages of extraneous material from the conveyor belt surface without loss of the required lubricity.

Abstract: The high speed melt spinning of synthetic polymer fibers is provided with on-line zone heating and cooling by which the strand emerging from the spinneret is initially cooled to an optimum temperature above the glass transition point of the polymer, the maintained near that temperature for a period of time to promote development of desirable fiber properties such as crystallization and crystal orientation, and then finally cooled below the solidification point for take up.

Abstract: A synergistic aqueous lubricant composition which comprises one or more carboxylated surfactants and one or more non-carboxylated surfactants in combination with a soap lubricant.