Embodiments of the invention are directed to a rotor for use in molten metal and devices including the rotor. The rotor has a rotor body and blades, wherein each blade includes a tip that is at least twice as hard as the rotor body.

Methods for forming a sintered bond coat (64) on a silicon-based substrate (14) and articles (50) formed by the methods are disclosed. The methods include applying a bond coat slurry on the silicon-based substrate (14), drying the bond coat slurry on the silicon-based substrate to form a dried bond coat (44), and sintering the dried bond coat (44) in an oxidizing atmosphere to form a sintered bond coat (64) on the silicon-based substrate (14). The bond coat slurry includes a bond coat patching material in a bond coat fluid carrier. The articles (50) include a silicon-based substrate (14), a sintered bond coat (64) formed on the silicon-based substrate (14), and a sintered environmental barrier coating (EBC) (66) formed on the sintered bond coat (64). The sintered bond coat (64) includes a silicon-based phase and an oxide of the silicon-based phase.

In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.

System (10) and methods (1000) for structural braze repair of high gamma prime nickel base gas turbine components (1). The system may include a controller (200) operably connected to a heating system (100), e.g., a vacuum furnace, for controlling heat temperatures of the furnace for a specified or predetermined time period. A damaged component is placed in the furnace and heated to a first temperature, which is held for the specified time period before being cooled to about room temperature. The component is then heated to a second temperature higher than the first temperature, which is held for a second time period before being cooled again to about room temperature. After cooling the component may be braze repaired at a third temperature equal to or higher than the previous temperatures for a third time period.

This fan motor includes a motor, an impeller arranged to rotate together with a rotating portion of the motor, a housing arranged to house the motor and the impeller therein, and a lead wire connected to the motor and arranged to extend outwardly of the housing. The housing includes a tubular portion, a bottom plate portion fixed below the motor, and a support portion arranged to extend from at least a portion of the tubular portion toward the bottom plate portion, and joined to at least a portion of the bottom plate portion. The support portion includes a groove portion recessed upward. The tubular portion includes a cut portion defined at a portion thereof continuous with the groove portion. The lead wire is drawn out of the housing through the groove portion and the cut portion. At least one of the groove portion and the cut portion has a thermosetting resin arranged therein.

A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.

The invention relates to a method for manufacturing a cellular structure comprising the following steps: a) providing a plurality of metal sheets (126) each having, in a first direction, undulations formed by a succession of vertex areas (28) alternately arranged with junction areas (30); b) juxtaposing the sheets (126) so as to form cells; c) placing a first (26a) end of each sheet (126) in contact with a support plate; d) arranging a soldering element between the support plate (34) and the first ends (26a) of the sheets (126) and heating the assembly in a furnace.

According to the invention, the method consists, prior to step d), in adding a means for blocking the diffusion of solder from said first ends (26a) of the sheets (126) to the second free ends (26b) of the sheets (126).

A turbocharger includes a variable vane mechanism includes a unison ring and at least one bearing member that is fixed to the unison ring. The bearing member includes a bearing surface that supports rotation of the unison ring within the variable vane mechanism. The unison ring and the at least one bearing member have independent material characteristics.

A process for manufacturing a turbomachine blade of the type having at least one 3D cavity, wherein the blade is produced by a succession of depositions and selective consolidations of layers of a metal additive manufacturing powder based on an alloy of copper and nickel, the alloy including from 2% to 7% of nickel. It also relates to a turbomachine blade, wherein it is manufactured by metal additive manufacturing using the process.

Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (T.sub.DISK.sub._.sub.PROCESS.sub._.sub.MIN) for the hub disk and a maximum critical temperature for the rotor blades (T.sub.BLADE.sub._.sub.MAX) is established such that T.sub.BLADE.sub._.sub.MAX is less than T.sub.DISK.sub._.sub.PROCESS.sub._.sub.MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than T.sub.DISK.sub._.sub.PROCESS.sub._.sub.MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below T.sub.BLADE.sub._.sub.MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.