Abstract: The present invention relates to an intermediate product for joining and coating by brazing comprising a base metal and a blend of boron and silicon, said base metal having a solidus temperature above 1040° C., and the intermediate product has at least partly a surface layer of the blend on the base metal, wherein the boron in the blend is selected from a boron source, and the silicon in the blend is selected from a silicon source, and wherein the blend comprises boron and silicon in a ratio of boron to silicon within a range from about 3:100 wt/wt to about 100:3 wt/wt. The present invention relates also to a stacked intermediate product, to an assembled intermediate product, to a method of brazing, to a brazed product, to a use of an intermediate product, to a pre-brazed product, to a blend and to paint.

Abstract: A process is disclosed comprising heating a powder mixture (212) with an energy beam (304) to melt only a portion of a first powder (202) of the mixture and to melt all or most of a second powder (204) of the mixture, wherein the second powder includes a gamma prime forming constituent and the first powder includes elements of a desired precipitation strengthened superalloy composition less the gamma prime forming constituent; allowing the melted portions to mix and to cool to form a deposit layer (208) including a beta phase alloy surrounding unmelted first powder of the mixture. The process may further include heat treating the deposit layer to transform it into a gamma plus gamma prime layer (210) of the desired precipitation strengthened superalloy composition.

Abstract: Methods for cleaning a superalloy substrate having engine deposits on its surface are provided. The method may include applying a permanganate solution onto the surface of the superalloy substrate, and applying a ferric chloride based cleaning composition onto the surface of the superalloy substrate. The ferric chloride based cleaning composition includes ferric chloride and at least one of nitric acid and phosphoric acid, such as within a solvent system (e.g., an aqueous solution including water).

Abstract: A method of repairing or, in certain cases, strengthening a metallic substrate at a damage site is provided and includes removing material from the substrate around the damage site to form a recess, and cold spraying particulate material into the recess to form a bead of deposited material.

Abstract: A method is provided for reworking a component. The method includes at least partially filling a cavity in a non-fusion weldable base alloy with a multiple of layers of a multiple of laser powder deposition spots formed of a filler alloy. Each of the multiple of laser powder deposition spots at least partially overlaps at least one of another of the multiple of laser powder deposition spots. The filler alloy may be different than the non-fusion weldable base alloy.

Abstract: A graphene-reinforced polymer matrix composite comprising an essentially uniform distribution in a thermoplastic polymer of about 10% to about 50% of total composite weight of particles selected from graphite microp articles, single-layer graphene nanoparticles, multilayer graphene nanoparticles, and combinations thereof, where at least 50 wt % of the particles consist of single- and/or multi-layer graphene nanoparticles less than 50 nanometers thick along a c-axis direction.

Abstract: A method of repairing an oxidized defect in a superalloy article includes removing substantially all of the oxidized defect to form a cleaned out portion of the superalloy article; filling a portion of the cleaned out portion with a weld by fusion welding; cracking the weld; and filling the cracked weld and a remaining portion of the cleaned out portion with a braze material.

Abstract: A method of reworking an aerospace component includes removing a casting defect from a component manufactured of a non-fusion weldable base alloy to form a cavity. The cavity is then at least partially filled with a multiple of layers of discrete laser powder deposition spots of a filler alloy. A cast component for a gas turbine engine includes a cast component non-fusion weldable base alloy with a cavity filled with a multiple of layers of laser powder deposition spots of a filler alloy. The filler alloy may be different than the non-fusion weldable base alloy. A layer of non-fusion weldable base alloy is at least partially within the cavity and over the filler alloy.

Abstract: A method of remanufacturing a turbine component includes electrical discharge machining a puck via the turbine component to form an electrical discharged machined puck; and brazing the electrical discharged machined puck to the turbine component.

Abstract: The present invention relates to transient liquid phase sinter pastes for electronic interconnects, and sinter paste application and processing methods.

Abstract: A clad article is disclosed including an article and a cladding layer. The article includes a surface layer, at least one cavity disposed within the article below the surface layer, and at least one microcrack disposed in the surface layer. The surface layer includes an HTW alloy. The cladding layer is disposed on a surface of the surface layer, and is formed from a PSP brazed to the article. The cladding layer is disposed over the at least one microcrack. A method for forming the clad article is disclosed including disposing the PSP on the article and brazing the PSP to the article. Brazing the PSP to the article forms the cladding layer disposed on the article over the at least one microcrack.

Abstract: Manufactured articles, and methods of manufacturing enhanced surface smoothed components and articles. More particularly, surface smoothed components and articles, such as combustor components of turbine engines, having surface treatment conferring reduced roughness for enhanced performance and reduced wear related reduction in part life.

Abstract: The invention relates to methods and devices for melting furnaces, conveying paths and conveying means for the melt, the melt product and for any type of discharges from a melting furnace and transportation means for the melt, with an extended service life, which in the case of a complete screen, that is to say in the optimum situation, may also be infinite, and/or with increased purity of the melt. This is achieved by the pushing-through or rotating-through of screens, clinkers, coatings, linings, etc., that is to say solid materials which are situated between the melt or melt product or the discharges and the materials situated behind the same which counteract the pressure of the melt, of the melt product or the discharges, for example walls. Here, new pieces of the screens etc. may be added at one free end, and used or worn pieces of the screens can be removed or withdrawn at another free end.

Abstract: A method for applying a coating to a defect area of a reactor component includes forming a patch on the reactor component at the defect area using a plasma-spray coating process. The plasma-spray coating process includes grounding the reactor component and a power supply of a plasma gun to a common ground such that a potential difference exists between the reactor component and a cathode of the plasma gun, and concurrently directing an ion-etching stream and a coating stream towards the region of the reactor component using the plasma gun while maintaining a desired distance between the plasma gun and the region of the reactor component. The directing the ion-etching stream includes heating the region of the reactor component using a plasma stream exiting a spray nozzle of the plasma gun. The coating stream includes droplets of a coating material.

Abstract: A method for repairing a component is provided, where the component has a substrate comprising an outer surface and an inner surface and defining one or more grooves. Each groove extends at least partially along the outer surface of the substrate. The component further includes a structural coating, a bond coating, and a thermal barrier coating. The groove(s) and the structural coating define one or more channels for cooling the component. The repair method includes removing the thermal barrier and bond coatings, removing at least a portion of the structural coating in a vicinity of a damaged portion of the component, performing a repair operation on the damaged portion of the component, applying a structural coating at least in a vicinity of the repaired portion of the component, and applying a bond coating and a thermal barrier coating. Additional repair methods are also provided.

Abstract: The invention is an innovative design/repair methodology for PWR piping nozzles and vessel nozzles that are attached to the piping/vessel base material with a full penetration weld joint geometry. The development of a robust repair methodology for nozzles of this configuration is necessary due to plant aging, potential material degradation in the original materials of construction, potential increased nondestructive examination requirements, and PWSCC phenomena in the susceptible original materials of construction. The purpose/objective of the repair methodology is to provide a means of partially replacing the existing pressure boundary susceptible materials with PWSCC-resistant materials to facilitate the long-term repair life of the plant. The invention may be applied to a plurality of nozzle, piping, and vessel sizes with a full penetration weld joint.

Abstract: A method for transient liquid phase bonding two metallic substrate segments together including the steps of forming a joined component by bringing together the two substrate segments along a bond line with a brazing alloy comprising a melting point depressant disposed between the two segments at the bond line and performing a first thermal treatment including heating the joined component at a brazing temperature of the brazing alloy for a first period of time. The method further includes performing a second thermal treatment including heating the joined component at an intermediate temperature that is above the brazing temperature but below a gamma prime solvus temperature of the substrate segments for a second period of time and performing a third thermal treatment including heating the joined component at a super-solvus temperature that is above the gamma prime solvus temperature of the two metallic substrate segments for a third period of time.

Abstract: A method of making an integrally bladed rotor with hollow blades. A plurality of segmented layers are sequentially placed to form each one of a plurality of blades on a radially outward surface of a hub. This is done using an additive manufacturing process. The placement of the segmented layers also comprises omitting portions of one or more of the plurality of segmented layers to form one or more cavities and intermittently removing a quantity of particles from the one or more cavities using an evacuation tool.

Abstract: The present invention discloses a plasma non-stick pan and manufacturing method thereof. The plasma non-stick pan comprises a pan body and a non-stick layer applied to the pan body; a plasma layer is provided between the non-stick layer and the pan body, and the plasma layer comprises a MCrALY layer sprayed to the surface of the pan body and a mixture layer sprayed outside of the MCrALY layer, and the mixture layer is composed of MCrALY particles and metal oxide particles. The MCrALY layer has good toughness and strong adhesion, and it is easy to bind with the substrate with high fastness after binding, playing a buffering role and laying a foundation for the subsequent spraying of mixture layer.

Abstract: Nickel base superalloys, including in some embodiments 5% to 7% Fe, which were previously developed and used for their corrosion resistance, also possess favorable characteristics for use as a braze filler in repair or joining of superalloy substrates, such as those used to form turbine engine blades and vanes, heat exchangers, vessels, and piping. In particular, such corrosion-resistant nickel base superalloys have favorable characteristics for wide-gap brazing of gaps greater than one millimeter in superalloy substrates that preserves favorable material properties throughout the braze region in the substrate.

Abstract: The present disclosure relates to a flip-chip package with a hollow-cavity and reinforced interconnects, and a process for making the same. The disclosed flip-chip package includes a substrate, a reinforcement layer over an upper surface of the substrate, a flip-chip die attached to the upper surface of the substrate by interconnects through the reinforcement layer, an air cavity formed between the substrate and the flip-chip die, and a protective layer encapsulating the flip-chip die and defining a perimeter of the air cavity. Herein, a first portion of each interconnect is encapsulated by the reinforcement layer and a second portion of each interconnect is exposed to the air cavity. The reinforcement layer provides reinforcement to each interconnect.

Abstract: A method for remanufacturing of a flywheel is provided. The flywheel has a damage area thereon. The method includes removing a portion of a material from a face of the flywheel containing the damage area to form a recessed portion, wherein the recessed portion has a ring shaped profile. The method also includes aligning an insert within the recessed portion of the flywheel, wherein the insert is ring shaped and is configured to fit within the recessed portion of the flywheel. The method further includes coupling the insert within the recessed portion of the flywheel.

Abstract: An electronic package that includes a substrate; an electronic component mounted to a surface of the substrate; and a porous coating that includes grains of metal powder formed onto the electronic component by melting the metal powder onto the electronic component. An electronic package that includes a substrate; an electronic component mounted to a surface of the substrate; and a porous coating that includes grains of metal powder formed onto the substrate by melting the metal powder onto the substrate. An electronic package that includes a substrate; an electronic component mounted to a surface of the substrate; an initial mold covering the electronic component; and a porous coating that includes grains of metal powder formed onto the initial mold by melting the metal powder onto the initial mold.

Abstract: A method including: attaching a plurality of conductive tracks to at least one surface of a substrate, depositing a coating comprising at least one halo-hydrocarbon polymer on the at least one surface of the substrate, and soldering through the coating.

Abstract: There is provided a method for installing a liner plate mounted on an interface surface of a load-bearing portion of mobile earth-moving machinery. There is also provided a liner plate which includes at least two openings and at least one grout strip, with the at least one grout strip being along a perimeter of the liner plate.

Abstract: In a method of improving bump allocation for a semiconductor device and a semiconductor device with improved bump allocation, a predetermined signal bump is surrounded with at least three bumps, each being a ground bump or a paired differential signal bump.

Abstract: A method is provided for repairing a single crystal turbine blade, which includes an airfoil with a tip having a tip cover plate, tip cooling air holes and a tip crown. The method includes removing the tip crown by manual grinding, thereby preserving the underlying tip cover plate; preparing the tip cooling air holes by manual grinding; closing said prepared tip cooling air holes by manual welding; and building-up a new tip crown by a LMF (Laser Metal Forming) process.

Abstract: A pillar structure for a substrate is provided. The pillar structure may have one or more tiers, where each tier may have a conical shape or a spherical shape. In an embodiment, the pillar structure is used in a bump-on-trace (BOT) configuration. The pillar structures may have circular shape or an elongated shape in a plan view. The substrate may be coupled to another substrate. In an embodiment, the another substrate may have raised conductive traces onto which the pillar structure may be coupled.

Abstract: A multi-pass gas metal arc weld (“GMAW”) approach is used for in-situ repair of railhead defects. A defect is removed via machining a perpendicular slot or grove in the railhead leaving the web and base unaltered. A sufficient number of GMAW passes are used to fill the slot using a weld material suitable for the particular type of parent steel, and excess weldment can be removed. Optionally, for pearlitic steel rails post-weld heat treatment can be used to cause austenization and/or quenching of the weld. The weld heat inputs and other parameters are controlled to avoid ductile and brittle fracture related morphologies.

Abstract: A method of repairing a connection between a first nozzle and a closed vessel includes cutting through an entire thickness of the first nozzle at a location adjacent to the mid-wall of the vessel. A portion of the first nozzle is removed. A replacement nozzle is disposed in a void formed by removal of the portion of the first nozzle. A weld is formed between the replacement nozzle and a surface of the mid-wall of the vessel.

Abstract: The present invention relates to a system of real time micro hot cell image control for radiopharmaceutical automatic synthesizing apparatus including at least one CCD camera, a plurality of radioactivity detector, a logic control device, a computer interface control device. The plurality of radioactivity detector are connected to the logic control device, and the logic control device sends a corresponding location code to the computer interface control device when the detected radioactivity value is greater than the threshold value for selecting a nearest CCD camera and sending the taken image of the location to the computer interface control device for monitoring whether the automatic production line of radiopharmaceuticals is kept in normal operation.

Abstract: A method for repairing a bundled tube fuel injector includes removing a portion of a pre-mix tube, aligning a tube tip with the remaining portion pre-mix tube and fixedly connecting the tube tip to the pre-mix tube. The method may further include removing an aft plate and an outer shroud from the bundled tube fuel injector so as to expose the pre-mix tube.

Abstract: A process for repairing combined heavy erosion and thermal fatigue cracks and/or other defects, such as large cracks, in a high temperature superalloy component, such as a vane in a turbine section of a gas turbine engine, that does not require mechanical grinding to prepare the defect site. The process includes depositing a loose finely granulated superalloy powder or a low viscosity superalloy slurry in the crack up to a suitable level and then depositing a superalloy putty layer on the superalloy powder or slurry at the top of the crack A braze putty layer is then deposited over the superalloy putty layer and the component is sintered in a vacuum furnace to harden the superalloy putty and powder or slurry to repair the defect.

Abstract: A radio-frequency (RF) shield pad is “dressed” by automatically removing melted solder from the shield pad by traversing a pattern of the shield pad. After an RF shield has been removed from a shield pad of a printed circuit board (PCB), the PCB is pre-heated to a temperature sufficient to heat solder on the shield pad and to prevent thermally stressing the PCB during the dressing process. The solder is melted, such as by a heated tip of a desoldering tool, and the melted solder is vacuumed while the tip automatically traverses the pattern of the shield pad, until all or a threshold amount of the melted solder has been removed from the shield pad. After the PCB has been reworked, solder paste is automatically disposed on the RF-shield pad, the RF shield is temporarily mounted on the RF-shield pad, and the PCB is processed in a reflow oven, thereby securely attaching the RF shield to the PCB.

Abstract: A turbine repair process, a repaired coating, and a repaired turbine component are disclosed. The turbine repair process includes providing a turbine component having a higher-pressure region and a lower-pressure region, introducing particles into the higher-pressure region, and at least partially repairing an opening between the higher-pressure region and the lower-pressure region with at least one of the particles to form a repaired turbine component. The repaired coating includes a silicon material, a ceramic matrix composite material, and a repaired region having the silicon material deposited on and surrounded by the ceramic matrix composite material. The repaired turbine component a ceramic matrix composite layer and a repaired region having silicon material deposited on and surrounded by the ceramic matrix composite material.

Abstract: The use of pre-sintered soldering plates, referred to as PSPs, frequently proceeds without a continuous, cohesive soldering connection between individual grains in the sinter material and between the sinter and base material. A process soldering of prefabricated, perforated, porous or drilled plates or porous, spongy, laminar material that, can be laid full-surfaced on a base element as a plurality of tiles or as individual porous, drilled or perforated inlay elements designed contour-close on a recess in the base material is provided. To this end, the selected plate materials can be mechanically equal to the base material or otherwise set off for the particular requirements of the component insert. The solder can be offset by specific diffusible, melting-point-lowering components. A mold that has an open, continuous porosity so that melted or fluid solder can flow through from the one surface to the other surface is also provided.

Abstract: Embodiments of a method for controllably reducing of the flow area of a turbine nozzle component are provided, as are embodiments of turbine nozzle components having reduced flow areas. In one embodiment, the method includes the steps of obtaining a turbine nozzle component having a plurality of turbine nozzle flow paths therethrough, positioning braze preforms in the plurality of turbine nozzle flow paths and against a surface of the turbine nozzle component, and bonding the braze preforms to the turbine nozzle component to achieve a controlled reduction in the flow area of the turbine nozzle flow paths.

Abstract: The invention provides a holding jig for supporting a solid material capable of being foamed by application of heat in a cavity of a hollow structure. The holding jig may be provided with a plate-like base body made smaller in diameter than the cavity of the hollow structure, a holding part that is provided in a predetermined width in the form of a ring on the periphery of one side of said base body and supports one side of the foamable material, a step part with predetermined height, which is projected in the form of a ring at the inner peripheral end of said holding part and supports the inner peripheral surface of the foamable material, and an attaching means with which the base body can be freely attached to or detached from the hollow structure.

Abstract: A method of depositing a multi-layer cladding (40) of superalloy material and an apparatus so formed. A first layer of material (20) is deposited on a substrate (22) such as by laser cladding of superalloy powder (54). The deposited material includes a directionally solidified region (24) and a topmost equiaxed region (26). The topmost region is removed such as by grinding to expose a flat surface (28) of directionally solidified material. A second layer of material (32) deposited onto the exposed flat surface will again have a directionally solidified region (34) and a topmost equiaxed region (36). The process is repeated until a desired thickness of cladding material is achieved, the multi-layer cladding having no equiaxed material between its layers throughout its thickness.

Abstract: A composite composition that includes an MCrAlX alloy and a nano-oxide ceramic is disclosed. In the formula, M includes nickel, cobalt, iron, or a combination thereof, and X includes yttrium, hafnium, or a combination thereof, from about 0.001 percent to about 2 percent by weight of the alloy. The amount of the nano-oxide ceramic is greater than about 40 percent, by volume of the composition. A protective covering that includes the composite composition is also disclosed. The protective covering can be attached to a tip portion of a blade with a braze material. A method for joining a protective covering to a tip portion of a blade, and a method for repair of a blade, are also provided.

Abstract: A multi-component braze filler alloy comprising at least 70% by weight MarM509A superalloy with the remainder MarM509B superalloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. It is shown that generally higher braze temperatures lead to improved results including the possibility of re-welding such a brazed component, resulting in a re-repaired brazed component capable of continued commercial service.

Abstract: A multi-component braze filler alloy comprising 60-70% by weight CM247 superalloy and BRB braze alloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. The substrate/braze interface may be subsequently weld-repaired without de-melting and migrating the braze alloy from the interface. The weld zone and surrounding area are solidification crack resistant. After the alloy composition is brazed to the base substrate the component may be returned to service. Thereafter the component remains repairable by welding or re-brazing, if needed to correct future in-service defects.

Abstract: The invention relates to a method for producing a plating (5) of a vane tip. Said method consists of the following steps: a) a vane having a vane tip which is arranged opposite the base of the vane (2) and which comprises a surface which points radially outwards is provided, and b) a porous layer (7) is applied to at least the surface (4) of the vane tip and/or c) a bulge (8) which increases the surface of the vane tip is applied to at least one part of the flanks of the vane tip, said flanks surrounding the surface of the vane tip, and d) the plating (5) is applied to the porous layer and/or the bulge. The invention also relates to corresponding vanes or gas turbines with corresponding vanes.

Abstract: A process for closing an opening in a surface of a component, and components formed thereby. The process entails forming a channel in the component surface so that the channel at least partially surrounds an opening at the component surface. An alloy is then deposited in the channel to form a crack-free deposit in the channel. A step is then machined that intersects the opening and is at least partially formed in the deposit. The step defines a recess that is at least partially surrounded by a peripheral portion of the deposit and has a surface recessed into the component surface. A cap is placed in the recess and welded to the peripheral portion of the deposit to define a weld joint that completely closes the opening. The surface of the weld joint is then machined to form a machined surface that is substantially flush with the component surface.

Abstract: A method for making a cellular seal member for a turbine is disclosed. The method includes, in sequence, forming a diffusion aluminide coating on a surface of a cellular seal to form a coated cellular seal. The method also includes brazing the coated cellular seal to a seal substrate.

Abstract: A component and a method of processing a component are disclosed. The method includes providing a base metal having a feature, removing the feature to form a processed region, applying a first layer to the processed region, and applying a second layer to the first layer. The base metal, the first layer, and the second layer each have predetermined thermal expansion coefficients, yield strengths, and elongations. The processed component includes the first layer applied to a processed region of the base metal and a second layer applied to the first layer.

Abstract: Various embodiments include apparatuses adapted to be used as a replacement oil cartridge tip. In some embodiments apparatuses include a replacement swirler ring for an oil cartridge tip, the replacement swirler ring having an annular main body including an inner diameter surface sized to be joined to an outer diameter surface of the oil cartridge tip by a metal joining process including one of brazing, welding temperature or mechanical interference and an outer diameter surface including channels evenly spaced about a primary axis of the annular main body, wherein the annular ring includes a material that is at least as wear-resistant as a material of the oil cartridge tip.

Abstract: The invention relates to a method for producing a nickel aluminide coating on a metal substrate. Said method includes the following steps: a) coating the substrate with a nickel deposit; b) applying an aluminum sheet onto the nickel deposit from step a) so as to form an assembly made up of the substrate coated with the nickel deposit and the aluminum sheet; and c) subjecting said assembly to heat treatment at a temperature that is lower than the melting point of aluminum, and at a low pressure so as to induce a reaction between the aluminum and the nickel and thus form a ?-NiAl nickel aluminide layer mounted on a nickel layer. The invention is particularly of use for protecting the materials used in turbines of aircraft engines.

Abstract: A gas turbine vane containment cap is attached to an inboard surface of the vane inner shroud by penetrating flat weld filler, formed in a root gap between the cap and inner shroud. A semi-circular bead weld filler is formed outboard the penetrating weld filler closer to the vane exterior. Vane containment caps so welded are more resistant to in-service cracking along weldments.

Abstract: A brazing method includes fixing a padding plate on a base material such that the padding plate is arranged in a lower position from a groove formed in a repair region of the base material, and heating the base material such that a base material powder is melt, after a paste that base material 1 contains the base material powder which is formed from a same material as the base material is filled into the groove. The base material powder filled into groove can be prevented from flowing out from the groove even if being fused since the padding plate is arranged for the base material. Thus, a repair region can be repaired more appropriately.