Abstract: A method repairs welding of an aircraft turbine engine blade that has a lower surface and an upper surface connected by a leading edge and a trailing edge. The blade further includes a free end referred to as the tip. The method includes the repair welding of the tip and including the steps of: securing a first stop to the leading edge at the tip and a second stop to the trailing edge at the tip, depositing a repair weld bead on the tip, from the first stop to the second stop, and removing the first and second stops. The first and second stops are secured solely by squeezing same on the leading and trailing edges.

Abstract: This blade repair method has: a first welding step in which overlay welding in which a first welding material is used is performed to form a notched part and a bury a first region positioned on a blade-body side with a first welding material; and a second welding step in which, after the first welding step, overlay welding in which a second welding material is used is performed to form a notched part and bury a second region positioned on a front-surface side of a platform with the second welding material. The high-temperature strength of the second welding material is higher than the high-temperature strength of the first welding material, the weldability of the first welding material is higher than the weldability of the second welding material, and the second region is located in a range from 1.0 mm to 3.0 mm (inclusive) from the front surface of the platform toward the blade body.

Abstract: A method for repairing damage on a non-friction surface of a carbon brake disc of an aircraft, includes: removal of a damaged region, cutting of a repair material, anti-oxidation modification of the repair material, bonding and curing, and high-temperature heat treatment. The anti-oxidation modification is performed on the repair material without affecting the mechanical properties of the repair material, which improves the anti-oxidation ability of the repair zone and avoids the preparation of an anti-oxidation coating. In this way, only the damage on the non-friction surface is repaired, and there is little effect on the mechanical properties, friction and wear properties and thermal conductivity of the carbon-carbon composite material.

Abstract: A tooling holds a blade during friction welding to a rotor element. The tooling includes a fixed jaw having a central part; two arms separated by a distance d for receiving at least one portion of the blade; and a fixed jaw body with bearing surfaces and a bore for receiving at least one portion of the blade. The bearing surfaces are configured to come into contact with the blade. A movable jaw includes a movable bearing surface that comes into contact with the blade, and pressure means that moves the movable jaw towards the fixed jaw body to press the blade.

Abstract: An airfoil component for attaching to a cropped airfoil is provided. The cropped airfoil comprises a cropped airfoil attachment section and a cropped first side opposite a cropped second side, which each extend axially between a cropped first edge and a cropped second edge to define a cropped chord length. The airfoil component comprises a body having a component first side opposite a component second side. The body defines an attachment section for attaching the airfoil component to the cropped airfoil at the cropped airfoil attachment section. The attachment section extends axially between a component first edge and a component second edge to define a component chord length, and the attachment section is oversized with respect to the cropped airfoil attachment section such that the component chord length is longer than the cropped chord length. Systems and methods also are provided.

Abstract: Disclosed is a braze putty composition including a sacrificial binder, a first nickel alloy and a second nickel alloy, a method of making the putty, and a method for using this putty to repair castings.

Abstract: A method of repairing a tip for an airfoil is disclosed herein. In various embodiments, the method comprises: removing a portion of the airfoil that reduces a radial height of the airfoil and at least partially removes a defect of the airfoil; removing a remainder of the defect; joining, via gas tungsten arc welding, a filler material to the airfoil to repair the defect; and joining a first mating surface of the airfoil to a second mating surface of a blade tip body via a solid-state joining process.

Abstract: Some implementations of the disclosure are directed to a thermal interface material. In some implementations, a method comprises: applying a solder paste between a surface of a heat generating device and a surface of a heat transferring device to form an assembly; and reflow soldering the assembly to form a solder composite, wherein the solder composite provides a thermal interface between the heat generating device and the heat transferring device, wherein the solder paste comprises: a solder powder; particles having a higher melting temperature than a soldering temperature of the solder paste, wherein the solder paste has a volume ratio of solder powder to high melting temperature particles between 5:1 and 1:1.5; and flux.

Abstract: A method for repairing a part and the resulting is disclosed. The method includes positioning a plug having an inner braze element coupled thereto into a cavity defined by an internal surface of a component. The cavity has a circular cross-section at the external surface of the component. The plug completely fills the circular cross-section and the inner braze element is within the cavity. A braze paste is positioned at least partially around the plug at the external surface. The component is positioned such that the inner braze element is above the plug. The component is subjected to a thermal cycle to melt the inner braze element around the plug, completely sealing the cavity by forming a metallurgical bond with the plug and the internal surface of the component. During the thermal cycle the braze paste is melted to form a metallurgical bond with the plug and external surface.

Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

Abstract: A process of repairing a component includes identifying a void in a component; determining at least one approximate physical configuration of the void; inserting borescope into the component in order to view the void; providing a repair rod approximately equivalent to at least one of the least one approximate physical configuration of the void; inserting the repair rod into component; confirming insertion of the repair rod in the void; separating the repair rod to leave a repair plug in the void; and depositing braze paste over the repair plug in the void.

Abstract: A method for assessing a thermal path associated with an integrated circuit includes identifying a heat application mode based on a design type of the integrated circuit. The method also includes measuring a first temperature of at least one thermal sensing device associated with the integrated circuit. The method also includes applying heat to at least a portion of the integrated circuit according to the heat application mode. The method also includes measuring a second temperature of the at least one thermal sensing device. The method also includes determining a difference between the first temperature and the second temperature. The method also includes determining whether a thermal path between the integrated circuit and an associated substrate is sufficient based on a comparison of the difference between the first temperature and the second temperature with a predetermined difference between an initial temperature and a subsequent temperature of the at least one thermal sensing device.

Abstract: A method of repairing an active leak in embodiments of the present invention may include one or more of the following steps: (a) identifying the active leak on a pipe structure, tank or pressure vessel, (b) setting cold spray system settings to repair the pipe structure, (c) administering pressurized gas and metal powder to an active pipe leak, (d) identifying any potential hazards surrounding the active pipe leak, (e) eliminating and/or reducing the potential hazards surround the active pipe leak, (f) inserting a wedge within an active leak pipe hole, (g) ceasing administration of pressurized gas and metal powder to the active pipe leak when it appears sealed, (h) verifying the active pipe leak is sealed, and (i) re-administering the pressurized gas and the metal powder to the active leak is the active leak is not fully sealed.

Abstract: A method includes producing a preform of a guide rail from steel, putting the preform in a holding device so that the preform is held fixed in position, analyzing the preform held in the holding device, a deviation from a straight shape being measured at a plurality of locations along the longitudinal axis. The method further includes irradiating the preform held in the holding device with a laser beam, a surface section being irradiated with the laser beam along the longitudinal axis at a plurality of locations, respectively on one of two side surfaces facing in opposite directions in relation to the first transverse axis, in such a way that it is heated into the plastic range.

Abstract: A projection forming method forming a projection on the surface of a work and includes: forming a first bank by LMD such that the first bank surrounds a projection forming region on the surface of the work; forming a first layer on the projection forming region by the LMD such that the first layer covers the first bank; laminating at least one first height raising layer on the first layer by the LMD; forming a second bank by the LMD along a peripheral edge of the at least one first height raising layer; forming an intermediate base layer on the at least one first height raising layer by the LMD such that the intermediate base layer covers the second bank; and laminating at least one second height raising layer on the intermediate base layer by the LMD.

Abstract: A method of manufacturing a fabricated object includes forming the fabricated object by laminating metal powder, the fabricated object including an opening portion that communicates with a hollow internal space, mounting a plug in the opening portion, and welding the plug mounted in the opening portion to the fabricated object.

Abstract: Disclosed is a Hot Isostatic Pressed ferritic-austenitic steel alloy, as well objects thereof. The elementary composition of the alloy comprises, in percentages by weight: C ?0-0.05; Si 0-0.8; Mn 0-4.0; Cr more than 29-35; Ni 3.0-10;? Mo 0-4.0; N 0.30-0.55;?? Cu 0-0.8; W 0-3.0; S ?0-0.03; Ce 0-0.2; the balance being Fe and unavoidable impurities. The objects can be particularly useful in making components for a urea production plant that require processing such as machining or drilling. A preferred use is in making, or replacing, liquid distributors as used in a stripper as is typically present in the high-pressure synthesis section of a urea plant.

Abstract: A process for forming an electric heater comprising the steps: (a) providing a heater element and a power supply, (b) applying a layer of a copper paste onto the heater element and/or the power supply and drying the applied layer of copper paste, (c1) applying a solder agent onto the dried copper paste and appropriately arranging the heater element and the power supply such that the heater element and the power supply contact each other by means of the dried copper paste and the solder agent or (c2) appropriately arranging the heater element and the power supply such that the heater element and the power supply contact each other by means of the dried copper paste, and applying a solder agent next to the dried copper paste or (c3) if in step (b) the copper paste has been applied only onto the heater element and then dried, applying a solder agent onto the power supply and appropriately arranging the heater element and the power supply such that the heater element and the power supply contact each other by me

Abstract: A method of brazing a treatment area of a load-bearing component includes applying a repair material over the treatment area of the component and positioning an induction brazing coil having a geometry corresponding to the treatment area over the repair material and the treatment area. The method further includes heating the repair material utilizing the induction brazing coil to a temperature sufficient to cause at least partial melting of the repair material, thereby effecting a brazed joint between the treatment area and the repair material.

Abstract: A repair method that includes covering a damaged part of a member to be repaired with a repair material, and heating the repair material to a predetermined temperature to form an alloy layer. At least the surface of the member to be repaired is a first metal such as Cu. The repair material includes a second metal such as Sn. By the heating, the surface of the member to be repaired is integrally joined with a layer of an intermetallic compound and an alloy having a melting point higher than a melting point of either of the first metal or the second metal.

Abstract: Methods of superalloy article repair are provided. In some embodiments, a method for repairing a nickel-based superalloy article comprises providing a layered assembly over a damaged region of the nickel-based superalloy article, the layered assembly comprising a nickel-based superalloy preform, an infiltration alloy preform and a melting point depressant component. The layered assembly is heated to form a nickel-based filler alloy metallurgically bonded to the damaged region, wherein primary carbide and secondary carbide phases are present in the nickel-based filler alloy in a combined amount of 0.5 to 10 vol. %.

Abstract: A tubular member includes a tube body, a tube end, an exterior surface, an interior surface, a nominal wall thickness, a longitudinal axis, a welded seam, and a patch of material. The welded seam forms an arcuate portion of the interior surface, and the patch covers a portion of the interior surface that includes a portion of the welded seam, extending from the tube end to an axially spaced first location. The resulting interior surface from the tube end to the axially spaced first location has a uniform inside diameter.

Abstract: The disclosure describes techniques for joining a first component comprising a first metal or alloy and a second component comprising a second metal or alloy to each other. The techniques may include positioning the first and second component adjacent to each other to define a joint region between adjacent portions of the first component and the second component. The techniques also may include positioning a pre-sintered preform (PSP) braze material in the joint region, heating the PSP braze material to form a molten braze alloy, and cooling the molten braze alloy to join the first and second components. The PSP braze material may include a wide gap braze material.

Abstract: A high temperature alloy is disclosed. The high temperature alloy may have on a weight basis: about 9.0-10.0 weight % of Co, about 0.25 weight % maximum of Fe, about 8.0-9.0 weight % of Cr, about 4.75-5.50 weight % of Al, about 1.0-1.5 weight % of Ti, about 0-2.0 weight % of Mo, about 6.0-9.0 weight %, of W, about 0.12-0.18 weight % of C, about 0.01-0.03 weight % of Zr, about 0.005-0.015 weight % of B, about 0.5-1.5 weight % of Ta, a balance of Ni, and incidental impurities.

Abstract: A process of fabricating a shield, a process of preparing a component, and an erosion shield are disclosed. The process of fabricating the shield includes forming a near-net shape shield. The near-net shape shield includes a nickel-based layer and an erosion-resistant alloy layer. The nickel-based layer is configured to facilitate secure attachment of the near-net shaped to a component. The process of preparing the component includes securing a near-net shape shield to a substrate of a component.

Abstract: An embodiment is a method including bonding a first package to a first set of conductive pads of a second package with a first set of solder joints, testing the first package for defects, heating the first set of solder joints by directing a laser beam at a surface of the first package based on testing the first package for defects, after the first set of solder joints are heated, removing the first package, and bonding a third package to the first set of conductive pads of the second package.

Abstract: The present invention relates to a method for producing and/or repairing wear-stressed recesses or openings on components (22) of a turbomachine, especially of elements of a flow passage boundary, and also to corresponding components, wherein the method comprises: producing an at least two-layer molded repair part (15), one layer (2) of which is formed by an Ni-solder and a further layer (3) of which is formed from a mixture of an Ni-solder (4) and hard material particles (5) of hard alloys on a base of cobalt or nickel and which at least partially has an outer shape which is complementary to the inner shape of the recess (20) or opening which is to be repaired, inserting the molded repair part (15) into the recess (20) or opening and at least partially heat-treating the component (22) for soldering the molded repair part (15) onto the component.

Abstract: There is provided a method for manufacturing a piston, including: a piston assembling step of forming a piston assembly by assembling a first piston part, a bonding member and a second piston part, wherein the first piston part has two or more bonding surfaces separate from each other and extending in a circumferential direction, and the second piston part has two or more bonding surfaces separate from each other and extending in the circumferential direction; a piston diffusion brazing step of diffusion brazing the first piston part, the bonding member and the second piston part under an open atmosphere by heating the formed piston assembly; and a piston cooling step of cooling a piston unit formed by diffusion brazing the first piston part, the bonding member and the second piston part.

Abstract: Disclosed is a Hot Isostatic Pressed ferritic-austenitic steel alloy, as well objects thereof. The elementary composition of the alloy comprises, in percentages by weight: C ?0-0.05; Si 0-0.8; Mn 0-4.0; Cr more than 29-35; Ni 3.0-10;? Mo 0-4.0; N 0.30-0.55:? Cu 0-0.8; W 0-3.0; S ?0-0.03; Ce 0-0.2; the balance being Fe and unavoidable impurities. The objects can be particularly useful in making components for a urea production plant that require processing such as machining or drilling. A preferred use is in making, or replacing, liquid distributors as used in a stripper as is typically present in the high-pressure synthesis section of a urea plant.

Abstract: Aspects include supplying a plurality of nickel-enriched braze powder particles to a cold spray system through a particle supply inlet. The nickel-enriched braze powder particles are accelerated through a transfer tube and out an exit in the transfer tube towards a substrate to produce a braze cold-sprayed substrate. A component surface is positioned proximate to the braze cold-sprayed substrate. The braze cold-sprayed substrate is heated to bond the braze cold-sprayed substrate to the component surface.

Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub with a through hole extending therethrough. The method comprises welding the aerofoil to the stub such that the open end of the hollow cavity of the aerofoil is aligned with the through hole of the stub so as to define a hollow region extending through the support member and stub to the cavity of the aerofoil. During welding a tool is positioned within the through hole and cavity and is aligned with an interface between the stub and aerofoil, the tool being configured to prevent weld splatter onto a surface of the cavity or through hole.

Abstract: A method of remanufacturing a prechamber assembly includes determining a width W of an original circumferential weld bead that extends around and joins a proximal end of an outer peripheral wall of a prechamber housing and a distal end of an outer peripheral wall of a body assembly, cutting through the weld bead in order to separate the prechamber housing from the body assembly, and removing material from an outer peripheral portion of a distal end portion of the body assembly. The method includes removing the material in an axial direction parallel to the central axis of the prechamber assembly for a distance that is from 2.5-3 times the width W.

Abstract: An apron upper member of a vehicle extends from a front pillar to a front side of the vehicle, and includes: a rear half portion having a sheet metal structure and having a vehicle rear end connected to the front pillar; and a front half portion formed of a casting product, the front half portion being connected to the rear half portion, extending to the front side of the vehicle, and having a vehicle front end connected to a crash box. The front half portion has a strength lowering portion immediately ahead of a connecting portion connected to the rear half portion. This suppresses significant approach of an occupant to a vehicle body at the time of collision.

Abstract: C-notch systems and methods for providing additional clearance or travel between the frame rail and the axle of a vehicle. Exemplary C-notch systems include a bottom brace, an outer brace, an inner brace, an outer fastener, an inner fastener, a front bottom fastener, and a rear bottom fastener. The outer brace and the inner brace can each have a notch that receives at least a portion of a vehicle bed rail.

Abstract: Disclosed is a method of making an integrally bladed rotor. According to the method, a titanium alloy rotor disk with 15-50% by volume of primary alpha grains with a grain size less than 10 ?m and secondary alpha grains comprising widmanstatten grains with a grain size less than 1.0 ?m is subjected to thermal processing. After thermal processing, a blade having an airfoil and a base is positioned such that a base surface is in contact with an outer rim surface of the disk. Heat, pressure, and motion are applied between the blade and the disk to friction weld the base surface to the disk outer rim surface.

Abstract: A method of reworking or repairing a component includes removing a casting defect from a component manufactured of a non-fusion weldable base alloy to form a cavity that results in a through hole; sealing the through hole with a backing; and at least partially filling the cavity with a multiple of layers of a multiple of laser powder deposition spots, each of the multiple of laser powder deposition spots formed of a filler alloy, a first layer of the multiple of layers includes a perimeter of the multiple of laser powder deposition spots that overlap a wall of the cavity and the backing.

Abstract: A method for braze repair of tight cracks in a superalloy component is provided. The method includes directing energy, e.g., from an acoustic energy source, towards surfaces of the tight crack to break up one or more contaminants, corrosion products, or oxides at the surface. The directed energy may cause opposed walls of the tight crack to vibrate to break up the oxides, and to generate a modest heat for allowing infiltration of the tight crack with a braze material. The braze material is then melted at a melt temperature of the braze material but below the melt temperature of the component. The braze material is then solidified to repair the tight crack.

Abstract: A monolithic substrate comprises a porous base material body, a first support portion, a first cell seal portion, a second support portion, and a second cell seal portion. The base material body includes a plurality of cells respectively passing from a first end surface to a second end surface. The first support portion contains ceramics as an aggregate material, and is packed into the first end portion of a seal target cell. The first cell seal portion contains glass, and is disposed on an outer surface of the first support portion. The second support portion contains ceramics as an aggregate material, and is packed into the second end surface of the seal target cell. The second cell seal portion contains glass, and is disposed on an outer surface of the second support portion.

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

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.