Abstract: An inductor and a method of forming the same are provided. The inductor includes a patterned wire structure. The patterned wire structure includes a conductive core, a dielectric film and a magnetic shell. The conductive core includes a pair of end surfaces and an outer surface between the pair of end surfaces. The dielectric film covers the outer surface. The magnetic shell covers the dielectric film. The dielectric film is between the conductive core and the magnetic shell.

Abstract: A seal system, for an apparatus that includes a rotatable portion with airfoils coupled thereto and a stationary portion with an inner surface, includes an abradable portion including at least one abradable layer of an abradable material formed over the inner surface. The seal system also includes an abrading portion disposed over at least a portion of a substrate of the airfoil. The abrading portion includes at least one abrading layer formed on at least a portion of the substrate and a plurality of abrasive particles embedded within the abrading layer. The plurality of abrasive particles includes at least one of substantially all of one of tantalum carbide (TaC), aluminum oxide (Al2O3), and ziconia (ZrO2), cubic boron nitride (cBN) and Al2O3 in predetermined ratios, cBN, Al2O3 and ZrO2 in predetermined ratios, Al2O3 and ZrO2 fused together in predetermined ratios, and TaC and Al2O3 in predetermined ratios.

Abstract: A sealing system for a centrifugal compressor includes a stator having a seal, a seal disposed in the seal housing and having an abradable portion along an inner circumference, a rotor having a plurality of rotor teeth configured to rotate within the inner circumference of the seal and configured to create rub grooves within the abradable portion, and a first spring disposed between the stator and the seal and configured to facilitate axial movement of the seal relative to the seal housing.

Abstract: An apparatus includes a cage and a main plug disposed in the cage. The main plug is movable between a main plug closed position and a main plug open position. A seal assembly disposed on the main plug, the seal assembly having a seal that is configured to contact the cage when the main plug is in the main plug closed position, and configured to reduce contact with the cage when a pressure differential across the seal is reduced. The apparatus includes a pressure balancing assembly movable between a closed position, an overtravel position and an open position. The pressure balancing assembly is configured to balance the pressure differential across the seal when in the overtravel and open position.

Abstract: Methods, systems and computer program products for assessing residual life of an airfoil, which would experience high cycle fatigue failure under at- or near-resonance vibration condition, are provided. The method includes receiving, at a processing system, at least one vibration response parameter associated with the airfoil. The method processes at least one cracked airfoil finite element model. Processing the cracked airfoil finite element model includes accessing the cracked airfoil finite element model, computing a modal stress intensity factor (SIF) of the cracked airfoil finite element model using fracture mechanics based finite element analysis, and computing a vibratory SIF based, at least in part, on the modal SIF and the at least one vibration response parameter. The method then computes a residual life indicator of the airfoil based, at least in part, on the vibratory SIF.

Abstract: A seal system, for an apparatus that includes a rotatable portion with airfoils coupled thereto and a stationary portion with an inner surface, includes an abradable portion including at least one abradable layer of an abradable material formed over the inner surface. The seal system also includes an abrading portion disposed over at least a portion of a substrate of the airfoil. The abrading portion includes at least one abrading layer formed on at least a portion of the substrate and a plurality of abrasive particles embedded within the abrading layer. The plurality of abrasive particles includes at least one of substantially all of one of tantalum carbide (TaC), aluminum oxide (Al2O3), and ziconia (ZrO2), cubic boron nitride (cBN) and Al2O3 in predetermined ratios, cBN, Al2O3 and ZrO2 in predetermined ratios, Al2O3 and ZrO2 fused together in predetermined ratios, and TaC and Al2O3 in predetermined ratios.

Abstract: An apparatus includes a cage and a main plug disposed in the cage. The main plug is movable between a main plug closed position and a main plug open position. A seal assembly disposed on the main plug, the seal assembly having a seal that is configured to contact the cage when the main plug is in the main plug closed position, and configured to reduce contact with the cage when a pressure differential across the seal is reduced. The apparatus includes a pressure balancing assembly movable between a closed position, an overtravel position and an open position. The pressure balancing assembly is configured to balance the pressure differential across the seal when in the overtravel and open position.

Abstract: A sealing system for a centrifugal compressor includes a stator having a seal, a seal disposed in the seal housing and having an abradable portion along an inner circumference, a rotor having a plurality of rotor teeth configured to rotate within the inner circumference of the seal and configured to create rub grooves within the abradable portion, and a first spring disposed between the stator and the seal and configured to facilitate axial movement of the seal relative to the seal housing.

Abstract: An abradable honeycomb is integrally formed in a turbine nozzle sealing flange for engagement with a bucket angel wing to reduce the leakage of air into the turbine's hot gas path. The honeycomb is integrally formed in a turbine nozzle sealing flange using a sinker EDM method to directly sink the honeycomb into the sealing flange itself, so that the honeycomb is an integral part of the flange. For repair, an entirely new honeycomb flange can be made and welded or brazed on to the turbine nozzle.

Abstract: A machine having a fixed part including a portion with a smooth surface is provided. The machine also includes a rotating part configured to rotate relative to the fixed part, the rotating part directly facing the portion of the fixed part, and plural ridges formed on the portion of the fixed part directly facing the rotating part, the plural ridges comprising an abradable material, wherein the abradable material is configured to be inoperable at temperatures above about 1000° C.

Abstract: A method and composition are provided for coating honeycomb seals and, more specifically, to a method and slurry for applying an aluminide coating onto honeycomb seals. The method includes preparing a slurry of a powder containing a metallic aluminum alloy having a melting temperature higher than aluminum, an activator capable of forming a reactive halide vapor with the metallic aluminum, and a binder containing an organic polymer. The slurry is applied to surfaces of the honeycomb seal, which is then heated to remove or burn off the binder, vaporize and react the activator with the metallic aluminum to form the halide vapor, react the halide vapor at the substrate surfaces to deposit aluminum on the surfaces of the seal, and diffuse the deposited aluminum into the surfaces to form a diffusion aluminide coating.

Abstract: A system and method to eliminate hard rub and optimize a purge flow in a gas turbine is provided. The gas turbine includes a stator configured to guide a flow of an incoming gas. The gas turbine also includes a rotor configured to expand the incoming gas and extract kinetic energy from the incoming gas. The gas turbine further includes a purge flow bled from a compressor and configured to reduce a temperature of a wheel space by limiting ingestion of the incoming gas. The gas turbine also includes an angel wing disposed between the rotor and the stator and configured to act as a sealing surface between the rotor and the stator. The gas turbine further includes a fan blade disposed on a surface of the angel wing at an axial position and configured to generate a recirculation zone of the purge flow, wherein the recirculation zone is reduces a volume of successive purge flows entering the wheel space.

Abstract: Methods, systems and computer program products for assessing residual life of an airfoil, which would experience high cycle fatigue failure under at- or near-resonance vibration condition, are provided. The method includes receiving, at a processing system, at least one vibration response parameter associated with the airfoil. The method processes at least one cracked airfoil finite element model. Processing the cracked airfoil finite element model includes accessing the cracked airfoil finite element model, computing a modal stress intensity factor (SIF) of the cracked airfoil finite element model using fracture mechanics based finite element analysis, and computing a vibratory SIF based, at least in part, on the modal SIF and the at least one vibration response parameter. The method then computes a residual life indicator of the airfoil based, at least in part, on the vibratory SIF.

Abstract: A method and composition are provided for coating honeycomb seals and, more specifically, to a method and slurry for applying an aluminide coating onto honeycomb seals. The method includes preparing a slurry of a powder containing a metallic aluminum alloy having a melting temperature higher than aluminum, an activator capable of forming a reactive halide vapor with the metallic aluminum, and a binder containing an organic polymer. The slurry is applied to surfaces of the honeycomb seal, which is then heated to remove or burn off the binder, vaporize and react the activator with the metallic aluminum to form the halide vapor, react the halide vapor at the substrate surfaces to deposit aluminum on the surfaces of the seal, and diffuse the deposited aluminum into the surfaces to form a diffusion aluminide coating.

Abstract: A method of forming a coating comprises depositing a first coating layer on a surface of a substrate, wherein the coating comprises a ceramic or metal, a lubricant, and a fugitive material. At least a portion of the fugitive material is decomposed, transformed or volatized by heating the first coating layer with a localized heat source.