Abstract: A blade includes an airfoil having pressure and suction side walls extending in a spanwise direction from a blade root to a blade tip and a hard phaseless metallic coating located at the blade tip. An assembly includes a casing having an inner diameter surface, an abradable coating located on a portion of the inner diameter surface, a blade having a blade tip configured to rotate within the casing where the blade tip and the inner diameter surface of the casing form a seal, and a hard phaseless metallic coating located on the blade tip. A method of making a blade includes forming a blade having a tip and depositing a hard phaseless metallic coating on the blade tip.

Abstract: An abradable seal material comprises: a polyimide foam matrix; and a thermal conductivity-enhancing filler in the matrix.

Abstract: What is described is a wear resistant seal system that is adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine. The system includes an axially rotable member including an abrasive tip having a first tensile strength. The system also includes a stationary structure radially exterior and adjacent to the rotable member and including an abradable material. The abradable material includes a matrix material having a second tensile strength that, at least in a first temperature range, is lower than the first tensile strength and a filler material interspersed with the matrix material.

Abstract: A component for a gas turbine engine is described. The component may comprise a body portion formed from a metallic material. The component may further comprise an abrasive surface forming at least one surface of the body portion, and the abrasive surface may be configured to abrade an abradable material. The abrasive surface may be formed from electrical discharge machining of the metallic material.

Abstract: A fan blade for a gas turbine engine is described. The fan blade may comprise a body portion formed from a metallic material, and it may include a suction side, a pressure side, a leading edge, a trailing edge, and a tip. A coating may be applied to the tip, and the coating may have a thermal conductivity of no more than about 10 watt per meter kelvin. The coating may be a thermal barrier coating comprising yttria-stabilized zirconia.

Abstract: A method for manufacturing a rotor includes manufacturing a hub using a conventional manufacturing process and manufacturing an airfoil on the hub using a layer-by-layer additive manufacturing process. A rotor includes a hub that has been manufactured with a conventional manufacturing process and an airfoil that has been manufactured on the hub with a layer-by-layer additive manufacturing process.

Abstract: A heat exchanger includes a plurality of fins and a plurality of tubes passing a fluid therethrough, extending through the plurality of fins and radially expanded into an interference fit therewith. At least one tube of the plurality of tubes includes an outer diameter, an inner diameter, and a plurality of ridges extending from the inner diameter inwardly into an interior of the tube. A tube internal surface area per unit of length of the tube multiplied by the ratio of the outer diameter and tube wall thickness is equal to or greater than about 30.0.

Abstract: A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.

Abstract: One aspect of the disclosure involves a rub material comprising a polymeric matrix and polymer micro-balloon filler in the matrix. In one or more embodiments of any of the foregoing embodiments, the matrix comprises a silicone. In one or more embodiments of any of the foregoing embodiments, the rub material is at least I.0 mm thick. In one or more embodiments of any of the foregoing embodiments, the silicone is selected from the group consisting of dimethyl- and fluoro-silicone rubbers and their copolymers. In one or more embodiments of any of the foregoing embodiments, the micro-balloons at least locally have a concentration of 5-50% by volume.

Abstract: An abrasive coating for a metal airfoil tip in a gas turbine engine may include a plurality of grit particles coated with a braze alloy material and configured for attachment to the airfoil tip. The braze alloy may be a nickel base, cobalt base or iron base braze alloy or mixtures thereof, or a titanium base braze alloy.

Abstract: A system and methods are provided for electrochemical grinding a workpiece. In one embodiment, a method includes controlling potentials to grinding tool and the workpiece, controlling applying electrolyte, and controlling grinding of the workpiece by the grinding tool. The method may also include determining screen replacement when there is sufficient metal plated.

Abstract: One aspect of the disclosure involves a nib material comprising a polymeric matrix and carbon nanotubes in the matrix. In one or more embodiments of any of the foregoing embodiments, the matrix comprises a silicone. In one or more embodiments of any of the foregoing embodiments, the rub material is at least 1.0 mm thick. In one or more embodiments of any of the foregoing embodiments, the silicone is selected from the group consisting of dimethyl- and fluoro-silicone rubbers and their copolymers. In one or more embodiments of any of the foregoing embodiments, the carbon nanotubes at least locally have a concentration of 1-20% by weight.

Abstract: A disclosed method utilizes virtual representations of gear profiles produced in view of accuracies and capabilities of specific machine and tool combinations to validate profile finishing parameters. The virtual representations are utilized to identify modifications needed to account for process capability and are implemented into the process to change the nominal profile utilized for producing the finished gear profiles. The resulting nominal gear profile accounts for process variations and thereby provides a more accurate and repeatable gear tooth profile.

Abstract: A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing edge, a convex side, a concave side and a distal tip. The leading edge, trailing edge, convex side and concave side of the airfoil is at least partially coated with an erosion resistant coating. The distal tip of the airfoil is coated with a bonded abrasive coating. The bonded abrasive coating engages the abradable coating disposed on the fan liner and, because of its low thermal conductivity, reduces heat transfer to the distal tip of the fan blade. The reduction in heat transfer to the distal tip of the fan blade preserves the integrity of erosion resistant coatings that may be applied to the body or the airfoil of the fan blade.

Abstract: A method for controlled peening includes forming a surface layer on a workpiece by impacting a surface with a tool wherein the tool is under control to form compressive residual stresses in the surface layer. A system for peening a workpiece includes a tool configured to vibrate and an effector operatively connected to control the tool. The tool includes a peening surface. The tool is configured to cause controlled impact between the peening surface and a surface of a workpiece to form a surface layer of the workpiece with compressive residual stresses. The effector is configured to move the tool in multiple axes.

Abstract: A tool is disclosed that has an elongated tool body defining a longitudinal axis and includes a ball-end section having a positive taper angle relative to the longitudinal axis of the tool body, and a relief section that extends rearwardly from the ball-end section and has a negative taper angle relative to the positive taper angle of the ball-end section.

Abstract: The present invention discloses an information processing method and an electronic device so as to address such a technical problem in the convention that data can not be protected from being misappropriated by another person while ensuring a rapid and convenient daily access of the user to the data.

Abstract: A seal for a gas turbine engine component having an airfoil with a radial outward end and a radial inward end, one of which is bare metal. A seal member is adjacent to the bare metal end of the airfoil wherein the seal member is coated with a abrasive layer having a laser engraved surface with the top of the surface has less than about 5% of the surface area of the base of the abrasive layer.

Abstract: An abrasive coating is formed on a rotor shaft that rotates with respect to cantilevered vanes. The coating is formed by thermal spray techniques and comprises a ceramic layer on a metal bond coat. The coating surface is roughened by crush grinding or by grit blasting to increase the abradability of the surface.

Abstract: A method of making a passenger conveyor handrail includes forming a drive member having a plurality of longitudinally spaced drive surfaces. The drive member has a longitudinal stiffness for maintaining a desired spacing between the drive surfaces. The drive member is inserted into a molding device. A gripping surface portion of the handrail is formed using the molding device such that the gripping surface portion and the drive member are secured together. Another method includes forming a belt drive member having a plurality of teeth that establish a plurality of longitudinally spaced drive surfaces. The belt has a longitudinal stiffness for maintaining a desired spacing between the drive surfaces. Each of the teeth extends across an entire width of the belt. The belt is secured to a gripping surface portion of the handrail.