Friction stir welding and processing of oxide dispersion strengthened (ods) alloys

A method of welding including forming a filler material of a first oxide dispersoid metal, the first oxide dispersoid material having first strengthening particles that compensate for decreases in weld strength of friction stir welded oxide dispersoid metals; positioning the filler material between a first metal structure and a second metal structure each being comprised of at least a second oxide dispersoid metal; and friction welding the filler material, the first metal structure and the second metal structure to provide a weld.

Braze alloy for high-temperature brazing and methods for repairing or producing components using a braze alloy

In a Ni-based, Co-based, or Ni—Co-based braze alloy ( 1 ) for high-temperature brazing of components ( 7 ) of modular structure and for repairing damaged components ( 7 ) which are formed of single crystal or directionally solidified superalloys using said braze alloy ( 1 ), the braze alloy has a first metallic powder component ( 2 ) having particle sizes in the nanometer range and a second metallic powder component ( 3 ) having particle sizes in the micrometer range. The surface of the particles of the second powder component ( 3 ) is thinly coated with particles of the first powder component ( 2 ). The braze alloy ( 1 ) additionally includes grain boundary stabilizing elements as alloying elements. In addition, melting point depressants can be present in the braze alloy ( 1 ) in a commercially common quantity or with a considerably increased proportion. Both the melting temperature of the braze alloy ( 1 ) and the probability of recrystallization are advantageously reduced.

Method of Joining at Least Two Components, a Method for Rendering a Component Resistant to Eroision, and a Turbine Blade

A method of joining at least two components, a method of preventing erosion of a base component and a turbine blade is provided. The method of joining at least two components includes providing a laser cladding apparatus, aligning a first component and second component, and jointing the first and second components by laser cladding. The first component includes a first joining surface adjacent to a seconding joining surface of the second component. The first joining surface and the second joining surface are joined by laser cladding along a joining plane. A joining material from the laser cladding provides at least one joining layer between the first joining surface and the second joining surface. The first and second joining surfaces include a bevel angle. A method for rendering a component resistant to erosion and a turbine blade are also provided.

COBALT-BASED ALLOY COMPRISING GERMANIUM AND METHOD FOR SOLDERING

Cobalt-based solder alloys are proposed. The cobalt-based solder alloys have germanium. The germanium has a higher melting point than nickel-based alloys such that the germanium is used advantageously for repairing or treating components having the nickel-based alloys used at high temperatures. The components are repaired or treated by soldering using the cobalt-based solder alloys. 115.-. (canceled)16. A cobalt-based solder alloy , comprising (in % by weight):7.0% to 9.0% nickel,17% to 21% chromium,5.0% to 6.5% tungsten,2.0% to 4.0% tantalum,0.1% to 0.3% titanium,13% to 27% germanium,optionally 0.3% to 0.7% carbon, andoptionally 0.2% to 0.7% zirconium.17. The solder alloy as claimed in claim 16 , further comprising:7.5% to 8.5% nickel,18.0% to 20.5% chromium,5.1% to 6.1% tungsten,2.5% to 3.2% tantalum,0.2% titanium,14% to 26% germanium,optionally 0.4% to 0.6% carbon, andoptionally 0.3% to 0.6% zirconium.18. The solder alloy as claimed in claim 16 , further comprising 18% to 22% germanium.19. The solder alloy as claimed in claim 16 , wherein the solder alloy comprises zirconium.20. The solder alloy as claimed in claim 16 , wherein the solder alloy comprises carbon.21. The solder alloy as claimed in claim 16 , wherein the germanium is replaced partially or completely by gallium.22. The solder alloy as claimed in claim 16 , wherein the germanium is replaced at most partially by gallium.23. The solder alloy as claimed in claim 16 , wherein the germanium is replaced at most partially by silicon.24. The solder alloy as claimed in claim 16 , wherein the germanium is replaced at most partially by silicon to an extent of 90%.25. The solder alloy as claimed in claim 16 , wherein the cobalt represents the remainder such that no further alloying elements are present.26. The solder alloy as claimed in claim 16 , wherein the solder alloy comprises no molybdenum except for impurities.27. The solder alloy as claimed in claim 16 , wherein the solder alloy contains no manganese and/ ...

Gamma, gamma' cobalt based alloys for additive manufacturing methods or soldering, welding, powder and component

The invention relates to gamma, gamma'-cobalt-based alloys for additive manufacturing methods or soldering, welding, powder and component. By using a cobalt-based alloy based on Co-7W-7 Al-23Ni-2Ti-2Ta-12Cr-0.0IB-0.IC-(0-0.1Si), an alloy that is especially well-suited for additive manufacturing methods or high-temperature soldering is proposed.

Systems and Methods of Fabrication and Use of Wear-Resistant Materials

Discussed herein are systems and methods of forming hardfacing coatings and films containing Q-carbon diamond particles for use in downhole drilling tooling and other tools where wear-resistant coating is desirable. The Q-carbon diamond-containing layers may be coated with matrix material and/or disposed in a matrix to form the coating, or the Q-carbon diamond layer may be formed directly from a diamond-like-carbon on a substrate.

METHOD FOR DEPOSITING A DESIRED SUPERALLOY COMPOSITION

Processes for depositing a desired superalloy composition are provided. An elongated core member (), such as made up of a wrought nickel-base alloy or a wrought cobalt-base alloy, may be drawn in connection with a wire drawing process. Elongated core member () includes at least one strengthening constituent having a reduced concentration to provide a desired level of ductility appropriate for the drawing of elongated core member (). A coating () is applied to elongated core member (). Coating () is configured to introduce a sufficient concentration of the strengthening constituent to form the desired superalloy composition when the coating and the elongated core member are melted together. This melting may occur during a welding process conducive to depositing the desired superalloy composition. The welding process may be performed in the context of repairing, rebuilding, and manufacturing superalloy components, such as for a gas turbine engine. 1. A method for depositing a desired superalloy composition , the method comprising:drawing an elongated core member comprising a wrought nickel-base alloy or a wrought cobalt-base alloy, the elongated core member comprising at least one strengthening constituent having a reduced concentration to provide a desired level of ductility appropriate for the drawing of the elongated core member; andapplying a coating to the elongated core member, the coating introducing a sufficient concentration of said at least one strengthening constituent to form the desired superalloy composition when the coating and the elongated core member are melted together.2. The method of claim 1 , wherein the at least one strengthening constituent is a gamma prime constituent.3. The method of claim 2 , wherein the at least one gamma prime strengthening constituent is titanium claim 2 , and the reduced concentration is in range from zero percent by weight to two percent by weight relative to a total weight of the elongated core member.4. The method of ...

NOVEL HIGH-ENTROPY ALLOY COMPOSITIONS

Novel high-entropy alloy (HEA) compositions are particularly suited to welding applications. The mixtures contain at least the elements nickel, manganese, cobalt, chromium, vanadium, molybdenum, and iron. The % weight of the constituents varies in accordance with the detailed description contained herein, with tolerances in the range of +/−2% and, in some cases, +/−1%. The mixture may also contain a small amount of aluminum with a tolerance in the range of +/−1% or, more preferably, +/−0.5% In accordance with the invention, the compositions above may be integrated into HEA welding products using cored wire and welding electrode manufacturing techniques, preferably starting with vacuum melted rolled alloys. One manufacturing process uses the compositions as an alloyed strip formed around the appropriate ground/crushed alloys to make commercially viable fabricated welding products. 1. A high-entropy alloy for welding applications , comprising: nickel,', 'manganese,', 'cobalt,', 'chromium,', 'vanadium,', 'molybdenum, and', 'iron., 'a mixture containing at least the following elements6. The high-entropy alloy of claim 1 , further including 0.11 to 0.12% aluminum with a tolerance in the range of +/−05%:12. The high-entropy alloy of claim 1 , wherein the welding product is fabricated using a cored-wire manufacturing process.13. The high-entropy alloy of claim 12 , wherein the cored-wire manufacturing process comprises an alloyed strip formed around the high-entropy alloy in ground or crushed form. This application claims the benefit of U.S. Provisional Patent Application Ser. No. 62/703,047, filed Jul. 25, 2019, the entire content of which is incorporated herein by reference.This invention relates generally to high-entropy alloys and, more particularly, to novel alloy compositions applicable to welding and other uses.There is no universally agreed-upon definition of a “high-entropy alloy” or HEA. Basically, a HEA is an alloy with multiple elements (typically 5 or more) ...

EARTH-BORING TOOLS HAVING PARTICLE-MATRIX COMPOSITE BODIES AND METHODS FOR WELDING PARTICLE-MATRIX COMPOSITE BODIES

Methods for welding a particle-matrix composite body to another body and repairing particle-matrix composite bodies are disclosed. Additionally, earth-boring tools having a joint that includes an overlapping root portion and a weld groove having a face portion with a first bevel portion and a second bevel portion are disclosed. In some embodiments, a particle-matrix bit body of an earth-boring tool may be repaired by removing a damaged portion, heating the particle-matrix composite bit body, and forming a built-up metallic structure thereon. In other embodiments, a particle-matrix composite body may be welded to a metallic body by forming a joint, heating the particle-matrix composite body, melting a metallic filler material forming a weld bead and cooling the welded particle-matrix composite body, metallic filler material and metallic body at a controlled rate. 1. A method of joining a particle-matrix composite body of an earth-boring tool to a metallic body , the method comprising: forming a first bevel portion and a second bevel portion in a face portion of a weld groove; and', 'forming an overlapping interface at least proximate a root portion of the weld groove;, 'forming a joint between a particle-matrix composite body of the earth-boring tool and a metallic body of the earth-boring tool, comprisingheating a volume of the particle-matrix composite body within the weld groove to an elevated first temperature below the melting temperature of the matrix material of the particle-matrix composite body;heating at least a portion of the volume of the particle-matrix composite body within the weld groove with a welding torch to a second temperature greater than the melting temperature of the matrix material of the particle-matrix composite body;melting a metallic filler material;forming a weld bead to weld the metallic filler to the particle-matrix composite body and to the metallic body at the joint;providing the welded particle-matrix composite body, metallic filler ...

SYSTEMS AND METHODS FOR WELDING WIRES FOR WELDING ZINC-COATED WORKPIECES

This disclosure relates generally to welding and, more specifically, to electrodes for arc welding, such as Gas Metal Arc Welding (GMAW) or Flux Core Arc Welding (FCAW) of zinc-coated workpieces. In an embodiment, a welding consumable for welding a zinc-coated steel workpiece includes a zinc (Zn) content between approximately 0.01 wt % and approximately 4 wt %, based on the weight of the welding consumable. It is presently recognized that intentionally including Zn in welding wires for welding galvanized workpieces unexpectedly and counterintuitively alleviates spatter and porosity problems that are caused by the Zn coating of the galvanized workpieces. 1. A welding consumable , comprising:between approximately 0.2 wt % and approximately 4 wt % zinc, based on the weight of the welding consumable, wherein the zinc is disposed within a granular core of the welding consumable, alloyed into a metallic portion of the welding consumable, or a combination thereof.2. The welding consumable of claim 1 , wherein the welding consumable comprises between approximately 0.4 wt % and approximately 0.6 wt % zinc claim 1 , based on the weight of the welding consumable.3. The welding consumable of claim 2 , wherein the welding consumable comprises between approximately 0.5 wt % and approximately 0.6 wt % zinc claim 2 , based on the weight of the welding consumable.4. The welding consumable of claim 1 , wherein less than approximately 15 wt % of the welding consumable is converted to spatter when welding a zinc-coated steel workpiece.5. The welding consumable of claim 1 , wherein the welding consumable is configured to form a weld deposit having a length porosity less than approximately 3% when welding a zinc-coated steel workpiece.6. The welding consumable of claim 1 , wherein the welding consumable is configured to form a weld deposit having an area porosity less than approximately 1.5% when welding a zinc-coated steel workpiece.7. The welding consumable of claim 1 , wherein the ...

BRAZE GEL, BRAZING PROCESS, AND BRAZING ARTICLE

A braze gel includes a braze powder, a braze binder, and a viscosity reducer. The braze gel has a gel viscosity sufficiently low to permit dip coating of a component with the braze gel to apply a braze coating of the braze gel to the component. A brazing process includes applying the braze gel to a portion of a component. The brazing process also includes drying the braze gel to form a braze coating on the component to form a braze-coated component. A brazing article includes a component and a braze coating over a portion of the component. The component may have structural features having a spacing of less than about 5 mm and a depth of at least about 1 mm, which may be honeycomb cells. The component may be a turbine component. 1. (canceled)2. (canceled)3. (canceled)4. (canceled)5. (canceled)6. (canceled)7. A process comprising:applying a braze gel having a gel viscosity to a portion of a component comprising an end of the component, the braze gel comprising a braze powder, a braze binder, and a viscosity reducer;drying the braze gel to form a braze coating on the portion of the component to form a braze-coated component comprising the component and the braze coating; andheating the braze coating to a brazing temperature to braze the end of the braze-coated component to a backing member;wherein the gel viscosity is lower than a paste viscosity of a braze paste comprising the braze powder and the braze binder with no viscosity reducer, the gel viscosity permitting dip coating of the component with the braze gel.8. The process of further comprising combining the braze powder claim 7 , the braze binder claim 7 , and the viscosity reducer to form the braze gel having the gel viscosity such that the viscosity reducer reduces the gel viscosity of the braze gel to permit dip coating of the component with the braze gel to apply the braze coating of the braze gel to the portion of the component.9. (canceled)10. The process of claim 9 , wherein the brazing temperature is in ...

Article and method for making an article

An article and a method for making shaped cooling holes in an article are provided. The method includes the steps of depositing a metal alloy powder to form an initial layer including at least one aperture, melting the metal alloy powder with a focused energy source to transform the powder layer to a sheet of metal alloy, sequentially depositing an additional layer of the metal alloy powder to form a layer including at least one aperture corresponding to the at least one aperture in the initial layer, melting the additional layer of the metal alloy powder with the focused energy source to increase the sheet thickness, and repeating the steps of sequentially depositing and melting the additional layers of metal alloy powder until a structure including at least one aperture having a predetermined profile is obtained. The structure is attached to a substrate to make the article.

PROCESS FOR JOINING TWO METAL PARTS BY BRAZE-WELDING

A process for joining two parts by braze-welding, including forming a joint, between two surfaces to be joined, and a fillet. The composition of the filler metal used to form the fillet is different from that used to form the joint, to provide the joint with a higher ductility. The method can, for example, be applied to production of high-pressure compressor guide-vane sectors for a turbomachine. 19-. (canceled)10. A method for joining two metal parts by brazing , comprising:forming, by a filler metal, a bonding joint between two bonding surfaces and a fillet,wherein the chemical composition of the filler metal for forming the fillet is different from that of the bonding joint, to have greater ductility.11. A method according to claim 10 , wherein the bonding joint is a capillary joint.12. A method according to claim 10 , wherein brazing temperature for the fillet is lower than liquidus temperature of the filler metal of the bonding joint.13. A method according to claim 10 , wherein the two metal parts are made of either a nickel-based or cobalt-based superalloy.14. A method according to claim 13 , wherein the filler metal for forming the bonding joint is either a nickel-based or cobalt-based alloy including at least one flux compound.15. A method according to claim 14 , wherein the flux compound is at least one element from among boron claim 14 , silicon claim 14 , and phosphorus.16. A method according to claim 10 , wherein the filler metal of the fillet is a copper-based alloy claim 10 , or CuMnNi930 claim 10 , or a manganese-based alloy claim 10 , or a precious-metal alloy.17. A method according to claim 10 , wherein one part of the two metal parts is a turbine engine compressor blade and the other part is a collar.18. A method according to claim 17 , wherein the joining forms a stator vane sector. The present invention relates to the brazing of parts made of a nickel-based or cobalt-based superalloy, that is to say made of a refractory alloy having a content by ...

Alloy powder for overlay welding, and weld overlay alloy member and engine valve obtained using the same

According the present invention, an alloy powder for overlay welding that prevents generation of gas defects in a weld overlay alloy in order to improve the toughness and wear resistance of the weld overlay alloy is provided. The alloy powder is an alloy powder for overlay welding on a steel surface containing nitrogen, which is characterized in that it contains 30% to 45% by mass of Mo, 10% to 30% by mass of Ni, 0.2% to 0.6% by mass of C, and 0.30% to 2.0% by mass of Al, with the balance made up of incidental impurities and Co.

BRAZE ALLOY COMPOSITIONS AND BRAZING METHODS FOR SUPERALLOYS

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. 1. A material for the braze repair of a nickel-base superalloy turbine component comprising a MarM509A/B mixture of no less than approximately 70% by weight of MarM509A base alloy and the balance comprising MarM509B braze alloy , including about 10%-15% by volume of a liquid binder to form a paste.2. A material as in wherein the nickel-base superalloy turbine component comprises CM247.3. A material as in claim 1 , wherein the nickel-base superalloy component is a turbine vane or blade.4. A method for brazing an Ni-base superalloy component comprising:placing the Ni-base superalloy component to be brazed and the brazing material into a brazing furnace, properly configured to perform the desired brazing process upon heating; andincreasing the furnace temperature to within about 25 deg. F of 1800 deg. F at a rate of approximately 28 deg. F per minute; andreducing the pressure within the furnace to less than about 0.005 Torr and hold for stabilization; andincreasing the furnace temperature to within about 12 deg. F of 2270 deg. F at a rate no greater than about 10 deg. F per min. and hold at this temperature for about 240 to 255 minutes for combined braze and diffusion cycle time while maintaining the pressure no greater than about 0.005 Torr; andvacuum cooling the furnace temperature to within about 25 deg. F of 1975 deg. F in a time no more than about 3 minutes; andrapid cooling to room temperature by back purging with inert gas; and,wherein the brazing material comprises a MarM509A/B mixture of no less than approximately 70% by ...

WELD FILLER METAL FOR SUPERALLOYS AND METHODS OF MAKING

A method of making a weld filler metal for a superalloy for welding is disclosed. The method includes enclosing a welding rod in a first foil layer and sintering the welding rod and the first foil layer. Related processes and articles are also disclosed. 1. A method of making a weld filler metal for use in a welding process with a superalloy , the method comprising:enclosing a welding rod in a first foil layer; andsintering the welding rod and the first foil layer.2. The method of claim 1 , wherein the welding rod comprises MarM247 claim 1 , IN738 claim 1 , R80 claim 1 , IN939 claim 1 , R142 claim 1 , R195 claim 1 , H188 claim 1 , H25 claim 1 , FSX414 claim 1 , RN2 claim 1 , or GTD111.3. The method of claim 1 , wherein the first foil layer includes an adhesive layer.4. The method of claim 1 , wherein the first foil layer includes at least 1% of at least one of boron claim 1 , silicon claim 1 , and germanium.5. The method of claim 1 , wherein a composition of the weld filler metal includes between approximately 0.1% and approximately 2.0% of at least one of boron claim 1 , silicon claim 1 , and germanium.6. The method of claim 1 , wherein the sintering includes heating to between approximately 1038° C. to approximately 1204° C. for between approximately 2 minutes and approximately 10 minutes.7. The method of claim 1 , the method further comprising:enclosing the welding rod and the first foil layer, prior to the sintering, in at least a second foil layer.8. The method of claim 7 , wherein the second foil layer comprises a second layer having a composition the same as a composition of the first foil layer.9. The method of claim 7 , wherein the second foil layer comprises a second foil having a distinct composition from a composition of the first foil layer.10. The method of claim 9 , wherein the second foil layer includes an adhesive layer.11. The method of claim 9 , wherein the second foil layer includes at least 1% of at least one of boron claim 9 , silicon claim 9 , ...

MAGNETIC NICKEL BASE TERNARY BRAZING MATERIAL AND METHOD OF APPLICATION

A ternary magnetic braze alloy and method for applying the braze alloy in areas having limited access. The magnetic braze alloy is a nickel-based braze alloy from the perminvar region of the Ni, Fe, Co phase diagram. The braze alloy includes, by weight percent 8-45% Fe, 0-78% Co, 2.0-4.0% of an element selected from the group consisting of B and Si and combinations thereof, and the balance Ni. The nickel-based braze alloy is characterized by a brazing temperature in the range of 1850-2100° F. The nickel-based braze alloy is magnetic below its Curie temperature. 1. A ternary braze alloy , comprising: about 8-45% Fe,', '0 to about 78% Co,', 'about 0.5-5.0% of an element selected from the group consisting of boron (B) and silicon (Si) and combinations thereof;', 'the balance Ni,, 'a nickel-based braze alloy from the perminvar region of the nickel (Ni), iron (Fe), cobalt (Co) phase diagram, the braze alloy comprising, by weight percent'}wherein the nickel-based braze alloy is characterized by a brazing temperature in the range of 1850-2100° F., andwherein the nickel-based braze alloy is magnetic below its Curie temperature.2. The ternary braze alloy of further including about 0.01-0.10% aluminum (Al).3. The ternary braze alloy of further including about 0.01-0.10% titanium (Ti).4. The ternary braze alloy of further including about 6-13% chromium (Cr).5. The ternary braze alloy of wherein the element selected from the group consisting of B and Si and combinations thereof are included in the range of about 2.0-4.0%.6. The ternary braze alloy of wherein the element selected from the group consisting of B and Si and combinations thereof are included in the range of about 2.75-3.75%.7. The ternary braze alloy of wherein the braze alloy is characterized by wettability sufficient to flow into porosity having a size of 0.001 inches and larger.8. The ternary braze alloy of wherein the braze alloy is a foil.9. The ternary braze alloy of wherein the foil has a thickness of about 0 ...

BRAZE ALLOY COMPOSITIONS AND BRAZING METHODS FOR SUPERALLOYS

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. 1. A material for the braze repair of a nickel-base superalloy turbine component comprising a CM247/BRB mixture of CM247 base alloy in the range from approximately 60% to 70% by weight and the balance comprises BRB braze alloy.2. A material as in claim 1 , wherein the nickel-base superalloy turbine component comprises CM247.3. A material as in claim 1 , wherein the Ni-base superalloy component is a turbine vane or blade.4. A material as in claim 1 , wherein the CM247/BRB mixture comprises about 80% of CM247 base alloy by weight and the balance comprises the BRB braze alloy wherein the components brazed with the material are not subjected to temperatures exceeding about 2270 deg. F. during the brazing process.5. A material as in claim 4 , wherein the nickel-base superalloy turbine component comprises CM247.6. A material as in claim 4 , wherein the Ni-base superalloy component is a turbine vane or blade.7. An article of manufacture comprising a Ni-base superalloy component wherein the Ni-base superalloy component has a portion thereof repaired by brazing with a brazing material claim 4 , wherein the brazing material comprises a mixture of CM247 base alloy in the range from about 60% to about 70% by weight and the balance comprising a BRB braze alloy.8. An article of manufacture as in claim 7 , wherein the nickel-base superalloy turbine component comprises CM247.9. ...

COMPOSITE WELDING WIRE AND METHOD OF MANUFACTURING

The present invention is a composite welding wire for fusion welding of components manufactured of superalloys. The composite weld wire includes a surface layer applied to the core wire in a green condition and bonded to the core wire. The surface layer includes alloying elements selected from among B and Si, the total bulk content of B and Si representing 0.5 to 4.0 wt. % of the composite welding wire. The boron and silicon alloying elements reduce the melting temperature and increase the solidification range of the weld pool, minimizing the incidence of weld cracking compared to welding without the coating. The green condition surface layer is comprised of more than 80 wt. % of the bulk content of the composite welding wire selected from the combination of B and Si. 1. A composite welding wire for fusion welding of components manufactured of superalloys , the composite weld wire comprises:a) a coated core wire configured for fusion welding of components manufactured of superalloys;b) the coating includes a surface layer applied to the core wire in a green condition and bonded to the core wire;c) the surface layer includes alloying elements which act to depress the melting point of a weld pool during welding, the alloying elements selected from a combination of B and Si in the surface layer, wherein the combination has a total bulk content of B and Si in representing 0.5 to 4.0 wt. % of the composite welding wire, wherein the boron and silicon alloying elements reduce the melting temperature and increase the solidification range of the weld pool and adapted to minimize the incidence of weld cracking compared to welding without the coating; andd) wherein the green condition surface layer comprises more than 80% wt. % of the bulk content of the composite wire of the alloying elements selected from the combination of B and Si.2. The composite welding wire claimed in wherein in a green condition the surface layer consists of at least 50 wt. % of a combination of B and ...

Soldering Structure and Process of Making the same

The invention discloses a soldering structure and process of making the same. The soldering structure comprises: a solder, a Sn—Co—Fe intermetallic compound having a thickness less than 10 μm and a diffusion barrier layer. The process of making the soldering structure is to react the solder containing Sn with an alloy consisting of 85˜95 wt % of Co and 5˜15 wt % of Fe at the temperature between 250 and 300° C. 1. A soldering structure , said soldering structure comprising: a solder , a diffusion barrier layer and a Sn—Co—Fe intermetallic compound between the solder and the diffusion barrier layer , wherein the Sn—Co—Fe intermetallic compound having a thickness less than 10 μm.2. The soldering structure according to claim 1 , wherein the solder is a lead free solder which is selected from the group consisting of Sn metal and Sn alloys.3. The soldering structure according to claim 1 , wherein the diffusion barrier layer is a Co—Fe alloy consisting of 85˜95wt % of Co and 5˜15 wt % of Fe.4. The soldering structure according to claim 3 , wherein the Co—Fe alloy consisting of 90 wt % of Co and 10 wt % of Fe.5. The soldering structure according to claim 1 , wherein the Sn—Co—Fe intermetallic compound is (Co claim 1 ,Fe)Sn.6. The soldering structure according to claim 1 , being part of an integrated circuit.7. The soldering structure according to claim 1 , being part of a liquid crystal display.8. The soldering structure according to claim 1 , being part of a printed circuit board.9. The soldering structure according to claim 1 , being part of a light-emitting diode device.10. The soldering structure according to claim 1 , being part of a portable communication device.11. The soldering structure according to claim 1 , being part of a semiconductor.12. A process for making the soldering structure according to claim 1 , said process comprising:providing a solder which is selected from the group consisting of Sn metal and Sn alloys;providing a diffusion barrier layer which is ...

WELD FILLER FOR SUPERALLOYS

A weld filler metal for a superalloy for welding is disclosed. The weld filler metal includes a preformed article that contains a first material with a melting point of approximately 2300 to 2500° F., and a second material with a melting point of approximately 1800 to 2200° F., wherein a ratio of the first material and the second material is variable. Related processes and articles are also disclosed. 1. A weld filler metal for a superalloy for welding , the weld filler metal comprising:a preformed article including:a first material with a melting point of approximately 2300 to 2500° F.; anda second material with a melting point of approximately 1800 to 2200° F., wherein a ratio of the first material and the second material is variable.2. The weld filler metal of claim 1 , wherein at least one of the first and second materials includes at least one of a cobalt based system and a nickel based system.3. The weld filler metal of claim 1 , wherein the ratio of the first material and the second material is chosen based on at least one of: a material content of the superalloy and a melting point of the superalloy being welded.4. The weld filler metal of claim 3 , wherein the first material includes a material chosen from a group comprising: a list of materials in Table 1.5. The weld filler metal of claim 3 , wherein the second material includes a material chosen from a group comprising: a list of materials in Table 2.6. The weld filler metal of claim 1 , wherein a shape of the preformed article comprises a wire shape.7. The weld filler metal of claim 1 , wherein a shape of the preformed article comprises a shape matching an area of the superalloy to be welded.8. A method of welding a superalloy claim 1 , the method comprising:applying a preformed article to an area of the superalloy, the preformed article including: a first material with a melting point of approximately 2300 to 2500° F.; and a second material with a melting point of approximately 1800 to 2200° F., wherein ...

ALLOY, WELDED ARTICLE AND WELDING PROCESS

An alloy is disclosed, including, by weight, about 13% to about 17% chromium, about 16% to about 20% molybdenum, about 1.5% to about 4% silicon, about 0.7% to about 2% boron, about 0.9% to about 2% aluminum, about 23% to about 27% nickel, about 0.8% to about 1.2% tantalum, and a balance of cobalt. The alloy includes a reduced occurrence of molybdenum silicide Laves phase relative to T800. A welded article is disclosed, including an article and a weld filler deposit joined to the article. The weld filler deposit includes a weld filler material including the alloy. A welding process is disclosed, including applying the weld filler material to the article and forming the weld filler deposit. 1. An alloy , comprising , by weight:about 13% to about 17% chromium;about 16% to about 20% molybdenum;about 1.5% to about 4% silicon;about 0.7% to about 2% boron;about 0.9% to about 2% aluminum;about 23% to about 27% nickel;about 0.8% to about 1.2% tantalum; anda balance of cobalt;wherein the alloy includes a reduced occurrence of molybdenum silicide Laves phase relative to T800.2. The alloy of claim 1 , further comprising claim 1 , by weight claim 1 , less than about 2.5% iron.3. The alloy of claim 1 , further comprising claim 1 , by weight claim 1 , less than about 2.5% incidental impurities.4. The alloy of claim 1 , wherein the alloy comprises claim 1 , by weight:about 15% chromium;about 18% molybdenum;about 2.5% silicon;about 1.2% boron;about 1.2% aluminum;about 25% nickel; andabout 1% tantalum.5. The alloy of claim 1 , consisting of:about 13% to about 17% chromium;about 16% to about 20% molybdenum;about 1.5% to about 4% silicon;about 0.7% to about 2% boron;about 0.9% to about 2% aluminum;about 23% to about 27% nickel;about 0.8% to about 1.2% tantalum;less than about 2.5% iron;less than about 2.5% incidental impurities; anda balance of cobalt.6. The alloy of claim 5 , consisting of:about 15% chromium;about 18% molybdenum;about 2.5% silicon;about 1.2% boron;about 1.2% aluminum; ...

ARTICLE

An article includes a substrate and a structure of additive manufacturing material of predetermined thickness attached to the substrate, the structure of additive manufacturing material formed by providing a metal alloy powder, forming an initial layer having a preselected thickness and a preselected shape including at least one aperture, with the metal alloy powder, sequentially forming an additional layer with the metal alloy powder over the initial layer, each of additional layers having an additional preselected thickness and an additional preselected shape including an aperture corresponding to the aperture in the initial layer, and joining each of the additional layers to the initial layer or any previously joined additional layers, forming a structure having a predetermined thickness and shape, and an aperture having a predetermined profile. The article includes a passageway through the structure including the aperture and a corresponding metering hole. 1. An article comprising:a substrate; and providing a metal alloy powder;', 'forming an initial layer with the metal alloy powder, the initial layer having a preselected thickness and a preselected shape including at least one aperture;', 'sequentially forming at least one additional layer with the metal alloy powder over the initial layer, each of the at least one additional layers having an additional preselected thickness and an additional preselected shape, the additional preselected shape including at least one aperture corresponding to the at least one aperture in the initial layer; and', 'joining each of the at least one additional layers to the initial layer or any previously joined additional layers, forming a structure having a predetermined thickness, a predetermined shape, and at least one aperture having a predetermined profile., 'a structure of additive manufacturing material of predetermined thickness attached to the substrate, the structure of additive manufacturing material being formed ...

COATING STRUCTURE MATERIAL

The invention is to provide a coating structure material excellent in Mg corrosion resistance, which has resistance to corrosion caused by molten Mg and molten Mg alloys. The invention relates to a coating structure material including an Ni—Co-base alloy substrate and a Co-base alloy coating layer formed on the Ni—Co-base alloy substrate, wherein the Co-base alloy coating layer contains, in terms of % by mass, Ni: 20% or less, Co: 42% or more, Si: 2.8% or less, and Fe: 3.5% or less. 1. A coating structure material comprising an Ni—Co-base alloy substrate and a Co-base alloy coating layer formed on the Ni—Co-base alloy substrate ,wherein the Co-base alloy coating layer contains, in terms of % by mass, Ni: 20% or less, Co: 42% or more, Si: 2.8% or less, and Fe: 3.5% or less.2. The coating structure material according to claim 1 , wherein the Co-base alloy coating layer further contains at least one element selected from the group consisting of claim 1 , in terms of % by mass claim 1 , C: 1.5% or less claim 1 , Mn: 1.0% or less claim 1 , Cr: 30% or less claim 1 , Mo: 20% or less claim 1 , W: 9.0% or less claim 1 , Ti: 0.3% or less claim 1 , and Al: 0.4% or less claim 1 , the remainder being unavoidable impurities.3. The coating structure material according to claim 1 , wherein the Ni—Co-base alloy contains claim 1 , in terms of % by mass claim 1 , C: 0.005 to 0.15% claim 1 , Cr: 8 to 22% claim 1 , Co: 5 to 30% claim 1 , Mo: 1 to less than 9% claim 1 , W: 5 to 20% claim 1 , Al: 0.1 to 2.0% claim 1 , and Ti: 0.3 to 2.5% claim 1 , the remainder being Ni and unavoidable impurities.4. The coating structure material according to claim 3 , wherein the Ni—Co-base alloy further contains at least one element selected from the group consisting of claim 3 , in terms of % by mass claim 3 , Si: 0.3% or less claim 3 , B: 0.015% or less claim 3 , Mg: 0.01% or less claim 3 , Zr: 0.2% or less claim 3 , and Hf: 0.8% or less.5. The coating structure material according to claim 3 , wherein ...

Structure braze of hard-to-weld superalloy components using diffusion alloy insert

A method for treating a component and a treated component are provided. The method includes the steps of machining a tapered slot in the component. The tapered slot is measured to determine dimensions. An insert is formed to have a corresponding geometry to the tapered slot with a braze gap between an outer surface of the insert and an inner surface of the tapered slot. A layer of a braze material is deposited on the outer surface of the insert, where a thickness of the layer corresponds to the braze gap. The layer of the braze material on the outer surface of the insert is sintered to fabricate a diffusion layer. The insert is positioned into the tapered slot. The diffusion layer is brazed to join the insert to the taper slot. The treated component includes a surface having a tapered slot, an insert, and a braze joint.

REPAIR MATERIAL PREFORM

A structural element and method for repairing a damaged portion of a metal component utilizes a preform configured to engage with the metal component and receive a repair material. The preform may be made of a material having a first melting point, and the repair material may be made of a material having a second melting point that is lower than the first melting point. The preform may be a mold configured to reconstruct the shape of the damaged portion of the metal component. The repair material may include a first material and an additive material, such as boron. The repair material may have a melting point that is approximately 40 degrees Fahrenheit lower than the melting point of the metal component. 1. A structural element for repairing a metal component comprising:a preform configured to receive repair material and repair a damaged portion of the metal component, wherein the metal component melts at a first temperature and the repair material melts at a second temperature that is lower than the first temperature, and wherein the preform has at least one of a preform wear resistance and a preform oxidation resistance that is greater than at least one of a repair material wear resistance and a repair material oxidation resistance of the repair material.2. The structural element of claim 1 , wherein the repair material comprises an additive material.3. The structural element of claim 1 , wherein the preform comprises a mold configured to reconstruct a shape of the damaged portion of the metal component.4. The structural element of claim 1 , wherein the preform comprises an alloy including cobalt or nickel.5. The structural element of claim 2 , wherein the repair material comprises a cobalt- or nickel-boron composition.6. The structural element of claim 1 , wherein the repair material has a melting point that is approximately 40 degrees Fahrenheit lower than a melting point of the metal component. This application is a divisional application of, and claims ...

ASSEMBLY, TREATED ARTICLE, AND PROCESS OF TREATING A TURBINE COMPONENT

In some embodiments, a process treats a turbine component. The turbine component includes an article and a wear component brazed to the article. The process includes applying a braze tape on at least a portion of the wear component and thermal processing the turbine component while the braze tape is on the at least a portion of the wear component to treat the turbine component. In some embodiments, an assembly includes a turbine component. The turbine component includes an article and a pre-sintered preform brazed to a surface of the article. The assembly also includes a braze tape on at least a portion of the pre-sintered preform. In some embodiments, a treated turbine component includes a treated article and a pre-sintered preform brazed to a surface of the treated article. The treated turbine component has been thermally processed with the pre-sintered preform being substantially free of re-flow. 1. A process of treating a turbine component comprising an article and a wear component brazed to the article , the process comprising:applying a braze tape on at least a portion of the wear component; andthermal processing the turbine component while the braze tape is on the at least a portion of the wear component to treat the turbine component.2. The process of claim 1 , wherein the wear component is a pre-sintered preform.3. The process of claim 2 , wherein the thermal processing comprises thermally cycling the turbine component and hot isostatic pressing the turbine component.4. The process of claim 3 , wherein the braze tape reduces or eliminates re-flow of the pre-sintered preform during the thermal cycling and during the hot isostatic pressing.5. The process of claim 2 , wherein the pre-sintered preform is a hardface chiclet.6. The process of further comprising returning the turbine component to service without removing or replacing the hardface chiclet.7. The process of claim 2 , wherein the braze tape reduces or eliminates re-flow of the pre-sintered preform ...

Ag BALL, Ag CORE BALL, FLUX-COATED Ag BALL, FLUX-COATED Ag CORE BALL, SOLDER JOINT, FORMED SOLDER, SOLDER PASTE AND Ag PASTE

Providing an Ag ball having a low alpha dose and a high sphericity regardless of impurity elements having an amount equal to or more than a predetermined value except for Ag. In order to suppress a soft error and reduce an connection fault, a content of U is equal to or less than 5 ppb, a content of Th is equal to or less than 5 ppb, a purity is equal to or more than 99.9% but equal to or less than 99.9995%, an alpha dose is equal to or less than 0.0200 cph/cm, a content of either Pb or Bi or a total content of both Pb and Bi is equal to or more than 1 ppm, and a sphericity is equal to or more than 0.90. 1: An Ag ball , comprising:an element U, a content thereof being equal to or less than 5 ppb; andan element Th, a content thereof being equal to or less than 5 ppb;wherein a purity of said Ag ball is equal to or more than 99.9% but equal to or less than 99.9995%;{'sup': '2', 'an alpha dose of said Ag ball is equal to or less than 0.0200 cph/cm;'}a content of either Pb or Bi or a total content of both Pb and Bi is equal to or more than 1 ppm; anda sphericity of said Ag ball is equal to or more than 0.90.2: The Ag ball as recited in claim 1 , wherein the alpha dose is equal to or less than 0.0010 cph/cm.3: The Ag ball as recited in claim 1 , wherein a diameter of said Ag ball is 1-1 claim 1 ,000 μm.4: A formed solder characterized in that a plurality of said Ag balls as recited in are dispersed in said solder.5: A solder paste claim 1 , containing said Ag ball as recited in .6: An Ag paste claim 1 , containing said Ag ball as recited in .7: A solder joint claim 1 , using said Ag ball as recited in .8: A flux-coated Ag ball claim 1 , comprising:{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'said Ag ball as recited in ; and'}a flux layer coating said Ag ball.9: A formed solder characterized in that a plurality of said flux-coated Ag balls as recited in are dispersed in the solder.10: A solder paste claim 8 , containing a plurality of said flux-coated Ag balls as ...

BRAZE SYSTEM, BRAZED ARTICLE, AND METHOD FOR FORMING A BRAZED ARTICLE

A braze system is disclosed, including a first surface, a second surface, a gap disposed between the first surface and the second surface, a capillary matrix disposed in the gap, and a braze material disposed in contact with the capillary matrix. The capillary matrix includes a matrix structure forming a plurality of capillaries. A brazed article is disclosed in which the braze material is disposed within the plurality of capillaries and contacts the first surface and the second surface. The braze material, the capillary matrix, the first surface, the second surface, and the gap form a brazed portion including less than about 20% voiding. A method for forming a brazed article includes disposing the capillary matrix into the gap, and infusing a braze material into the plurality of capillaries and in contact with the first surface and the second surface, forming the brazed portion. 1. A braze system , comprising:a first surface;a second surface;a gap disposed between the first surface and the second surface;a capillary matrix disposed in the gap, the capillary matrix including a matrix structure forming a plurality of capillaries; anda braze material disposed in contact with the capillary matrix.2. The braze system of claim 1 , wherein the matrix structure includes a cross-linked metallic matrix.3. The braze system of claim 2 , wherein the matrix structure includes up to a 100 μm pore size.4. The braze system of claim 3 , wherein the matrix structure includes between about a 20 μm to about a 60 μm pore size.5. The braze system of claim 2 , wherein the capillary matrix includes a material selected from the group consisting of superalloys claim 2 , nickel-based superalloys claim 2 , cobalt-based superalloys claim 2 , iron-based superalloys claim 2 , hard-to-weld alloys claim 2 , non-weldable alloys claim 2 , refractory alloys claim 2 , iron-based alloys claim 2 , steel alloys claim 2 , stainless steel alloys claim 2 , cobalt-based alloys claim 2 , nickel-based alloys ...

BRAZE ALLOY COMPOSITIONS AND BRAZING METHODS FOR SUPERALLOYS

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. 1. A material for the braze repair of a nickel-base superalloy turbine component comprising:a MarM509A/B mixture of no less than approximately 70% by weight of MarM509A base alloy and the balance comprising MarM509B braze alloy, including about 10%-15% by volume of a liquid binder to form a paste.2. A material as in wherein the nickel-base superalloy turbine component comprises CM247.3. A material as in claim 1 , wherein the nickel-base superalloy component is a turbine vane or blade.4. An article of manufacture comprising a Ni-base superalloy component wherein the Ni-base superalloy component has a portion thereof repaired by brazing with a brazing material according to .5. An article of manufacture as in claim 4 , wherein the Ni-base superalloy turbine component comprises CM247.6. An article of manufacture as in claim 4 , wherein the Ni-base superalloy component is a turbine vane or blade.7. An article of manufacture as in claim 4 , wherein the Ni-base superalloy component has a portion thereof re-repaired by post braze welding and is suitable for continued service.8. An article of manufacture as in claim 7 , wherein the Ni-base superalloy turbine component comprises CM247.9. An article of manufacture as in claim 7 , wherein the Ni-base superalloy component is a turbine vane or blade.10. An article of manufacture as in claim 4 , wherein the Ni-base superalloy component is post-braze heat treated and is suitable for continued service.11. An article of manufacture as in claim 10 , wherein the Ni-base superalloy turbine ...

New product and use thereof

A new pre-alloyed metal based powder, intended to be used in surface coating of metal parts. The powder is deposited using e.g. laser cladding or plasma transfer arc welding (PTA), or thermal spray (e.g. HVOF). The powder is useful for reducing friction and improving wear reducing properties of the deposited coating. Such coatings may also improve machinability. As friction or wear reducing component, inclusions of manganese sulphide or tungsten sulphide in the pre-alloyed powder may be used.

NOVEL WELD FILLER METAL

An alloy includes a matrix that includes an amount of high-melting-temperature superalloy between about 30% and 95% by weight and an amount of low-melting-temperature superalloy between about 0% and 70% by weight. The alloy also includes an amount of a ceramic reinforcement material between about 2% and 50% by volume, dispersed in the matrix. 1. An alloy comprising: an amount of high-melting-temperature superalloy between about 30% and 95% by weight; and', 'an amount of low-melting-temperature superalloy between about 0% and 70% by weight; and, 'a matrix comprisingan amount of a ceramic reinforcement material between about 2% and 50% by volume, dispersed in the matrix.2. The alloy of claim 1 , wherein the amount of the low-melting-temperature superalloy is between about 1% and 70% by weight.3. The alloy of claim 1 , wherein the high-melting-temperature superalloy has a melting temperature greater than about 1315 degrees Celsius (° C.) claim 1 , and the low-melting-temperature superalloy has a melting temperature in a range below about 1290° C.4. The alloy of claim 1 , wherein the high-melting-temperature superalloy comprises iron-based claim 1 , cobalt-based claim 1 , and/or nickel-based superalloys.5. The alloy of claim 1 , wherein the low-melting-temperature superalloy comprises iron-based claim 1 , cobalt-based claim 1 , and/or nickel-based braze alloys.6. The alloy of claim 1 , wherein the ceramic reinforcement material comprises silicon carbide fibers claim 1 , titanium nitride fibers claim 1 , titanium nanotubes claim 1 , titanium carbide fibers claim 1 , or titanium carbide nanotubes.7. The alloy of claim 1 , wherein the amount of high-melting-temperature superalloy is between about 50% to 95% by weight claim 1 , the amount of the low-melting-temperature superalloy between about 2% and 50% by weight claim 1 , and the amount of the ceramic reinforcement material is 5% to 50%.8. The alloy of claim 1 , wherein the amount of high-melting-temperature superalloy is ...

Process for joining by diffusion welding a part made of steel having a high carbon content with a part made of steel or nickel alloy having a low carbon content: corresponding assembly

Process for joining by diffusion welding a part made of steel having a high carbon content and low carbide-forming elements content with a part made of steel or of nickel alloy having a low carbon content and a high carbide-forming elements content, each of the parts comprising a surface to be joined in which process an intermediate material is placed between the surfaces to be joined, then diffusion welding is carried out to join the two parts, and the assembly obtained is cooled, characterised in that the intermediate material is an alloy, with a matrix made of nickel and optionally of iron and/or cobalt, having an austenitic micro-structure at the welding temperature, and comprising 2 to 25% by mass of molybdenum. Also disclosed is an assembly obtained by this process.

COMPONENT HAVING WEAR-PROTECTED OPENINGS AND RECESSES AND PROCESS FOR THE PRODUCTION THEREOF

The present invention relates to a method for producing and/or repairing wear-stressed recesses or openings on components () of a turbomachine, especially of elements of a flow passage boundary, and also to corresponding components, wherein the method comprises: 114-. (canceled)15. A method for producing and/or repairing a wear-stressed recess or opening of a component of a turbomachine , wherein the method comprises:inserting into the recess or opening to be repaired an at least two-layered molded repair part, a first layer of which is formed by an Ni-solder and a second layer of which is formed from a mixture of an Ni-solder and hard material particles of hard alloys based on cobalt or nickel and which at least partially has an outer shape which is complementary to an inner shape of the recess or opening, andat least partially heat-treating the component to solder the molded repair part onto the component.16. The method of claim 15 , wherein producing of the molded repair part is carried out such that the Ni-solder layer at least partially constitutes an outer edge of the molded repair part which comes into contact with an inner surface of the recess or opening when inserted into the recess or opening.17. The method of claim 15 , wherein producing of the molded repair part is carried out by deep drawing or pressing an at least two-layered tape or two-layered plate comprising the first layer and the second layer into a die in order to at least partially obtain an outer shape which is complementary to an inner shape of the recess or opening.18. The method of claim 15 , wherein the method further comprises preparing the recess or opening by material removal prior to insertion of the molded repair part.19. The method of claim 15 , wherein the second layer of the molded repair part comprises 20 to 60 wt. % of hard material particles.20. The method of claim 15 , wherein the second layer of the molded repair part comprises 35 to 45 wt. % of hard material particles.21. ...

METHOD AND FILLER MATERIAL STRUCTURE OF HIGH TEMPERATURE BRAZE REPAIR FOR DAMAGES OF BASE ALLOY COMPONENTS

A method of braze repair of a base alloy component that includes a braze thermal cycle including a specially chosen peak braze temperature holding time segment and a purposely selected subsequent diffusion heat treatment segment. A multi-layer braze filler material structure used for the braze repair of a base alloy component including at least a first superalloy layer and a single mixture layer. The single mixture layer including at least a braze alloy and a second superalloy. 1. A multi-layer braze filler material structure for the braze repair of a base alloy component comprising at least a first superalloy layer and a single mixture layer , wherein the single mixture layer comprises a braze alloy and a second superalloy.2. The multi-layer braze filler material structure of claim 1 , wherein the braze alloy material is a Nickel base braze alloy comprising at least one melting point depressing element.3. The multi-layer braze filler material structure of claim 1 , wherein the braze alloy material is a Cobalt base braze alloy comprising at least one melting point depressing element.4. The multi-layer braze filler material structure of claim 1 , wherein the braze alloy is non-eutectic.5. The multi-layer braze filler material structure of claim 1 , wherein the second superalloy material is a Nickel base superalloy compatible with both the braze alloy and the cast grade superalloy component.6. The multi-layer braze filler material structure of claim 1 , wherein the second superalloy material is a Cobalt base superalloy compatible with both the braze alloy and the cast grade superalloy component.7. The multi-layer braze filler material structure of claim 1 , wherein the mixture has a braze alloy to second superalloy mixing ratio range of approximately 95 braze alloy/5 second superalloy to approximately 60 braze alloy/40 second superalloy.8. The multi-layer braze filler material structure of claim 1 , wherein the multi-layer braze filler material structure comprises a ...

IMPARTING WEAR RESISTANCE TO SUPERALLOY ARTICLES

In one aspect, composite preforms are provided for imparting wear resistance to superalloy articles. The composite preforms can be employed for metallurgically bonding alloy wear plates or pads to superalloy articles. A composite preform, in some embodiments, comprises a powder alloy composition comprising 1-30 wt. % nickel, 0.05-2 wt. % iron, 15-25 wt. % chromium, 10-30 wt. % molybdenum, 0-1 wt. % carbon, 1-5 wt. % silicon, 0.05-2 wt. % boron, 0-5 wt. % tungsten, 0-3 wt. % tantalum, 0-0.1 wt % manganese, 0-3 wt. % aluminum, 0-0.1 wt % yttrium and the balance cobalt. 1. A composite preform comprising:a powder alloy composition comprising 1-30 wt. % nickel, 0.05-2 wt. % iron, 15-25 wt. % chromium, 10-30 wt. % molybdenum, 0-1 wt. % carbon, 1-5 wt. % silicon, 0.05-2 wt. % boron, 0-5 wt. % tungsten, 0-3 wt. % tantalum, 0-0.1 wt % manganese, 0-3 wt. % aluminum, 0-0.1 wt % yttrium and the balance cobalt.2. The composite preform of claim 1 , wherein the powder alloy composition comprises 1-10 wt. % nickel claim 1 , 0.05-2 wt. % iron claim 1 , 15-25 wt. % chromium claim 1 , 10-30 wt. % molybdenum claim 1 , 0-1 wt. % carbon claim 1 , 1-5 wt. % silicon claim 1 , 0.05-2 wt. % boron claim 1 , 0.5-5 wt. % tungsten claim 1 , 0-2 wt. % tantalum and the balance cobalt.3. The composite preform of claim 1 , wherein the powder alloy composition comprises 4.5-7 wt. % nickel claim 1 , 0.3-0.9 wt. % iron claim 1 , 20-24 wt. % chromium claim 1 , 12-18 wt. % molybdenum claim 1 , 0.1-1 wt. % carbon claim 1 , 1-2.2 wt. % silicon claim 1 , 0.9-2 wt. % boron claim 1 , 2.5-5 wt. % tungsten claim 1 , 1.5-2 wt. % tantalum and the balance cobalt.4. The composite preform of claim 1 , wherein the powder alloy composition comprises 3-5 wt. % nickel claim 1 , 0.7-1.1 wt. % iron claim 1 , 18-22 wt. % chromium claim 1 , 16-20 wt. % molybdenum claim 1 , 0.1-0.5 wt. % carbon claim 1 , 1.9-2.5 wt. % silicon claim 1 , 0.7-1 wt. % boron claim 1 , 1-3 wt. % tungsten claim 1 , 1-1.5 wt. % tantalum and the ...

PREFORMS FOR BRAZING

A method for producing brazing preforms including the steps of providing an iron-, iron and chromium-, nickel- or cobalt-based spherical brazing powder. Converting the brazing powder into an agglomerated coarser powder suitable to be compacted into desired preforms and ejecting the preforms from the compaction die, the preforms having integrity and strength enough to let them be handled in an automated brazing line. Optionally, after ejecting from the compaction die, the preforms may be heat treated or subjecting to a sintering process if higher strength is desired. Also, the preform per se and a brazing process utilising the brazing preform. 1. A method for producing a brazing preform comprising the steps of:providing an iron-, iron and chromium-, nickel- or cobalt-based brazing powder having a particle size below 355 μm,mixing the powder with 0.1-5% by weight of a water soluble binder chosen from the group of polyvinyl alcohol, polyethylene glycol having a molecular weight between 1500 and 35000, carboxymethylcellulose, methylcellulose, ethylcellulose, acrylates or gelatine and optionally adding and mixing in a non-water soluble binder chosen from the group of polyamides, amide oligomers and polyethylenes, the total amount of binders being 0.1-5%subjecting the mixed powder to an agglomeration process resulting in an agglomerated powder having an agglomerated particle size below 1 mm,optionally adding a non-water soluble binder chosen from the group of polyamides, amide oligomers and polyethylenes, the total amount of binders being 0.1-5%, preferably between 0.5-3%,{'sup': '3', 'compacting the obtained agglomerated powder at a pressure of at least 300 MPa in an uniaxial compaction process to a density of at least 3.5 g/cm'}optionally heat treating or sintering the compact,recovering compacted preform.2. The method according to wherein the iron- claim 1 , iron-chromium- claim 1 , nickel or cobalt-based powder has a particle size below 212 μm.3. The method according ...

REPAIRING A PART HAVING CRACKS, AND PART

Components having cracks can be repaired more simply by the localized deposition of braze material onto a region that is to be repaired, and surrounding weld filler material. A method is disclosed for repairing a damaged component. The component has a substrate with cracks, wherein material is to be deposited at least in a region of a build-up region having the cracks. The method includes a braze material deposited at least in the region of the cracks and a weld filler material is deposited in the other regions of the build-up region, wherein the melting point of the braze material is at least 10K lower than that of the material of the substrate and the weld filler material, in which the braze material is always surrounded by a weld filler material in a plane, in particular completely surrounded. 19-. (canceled)10. A methodfor repairing a damaged component,wherein the component has a substrate with cracks,wherein material is to be depositedat least in a region of a build-up regionhaving the cracks,said method comprising:depositing a braze material at least in the region of the cracks anddepositing a weld filler material in the other regions of the build-up region,wherein the melting point of the braze material is at least 10K lower than that of the material of the substrate and the weld filler material,in which the braze material is always surrounded by a weld filler material in a plane, in particular completely surrounded.11. A component ,comprising a braze material and a weld filler material are present in a build-up region,wherein the braze material is present at least in cracks,wherein the melting point of the braze material is at least 10K lower than that of the material of the substrate and/or the weld filler material,in which the braze material is always surrounded by a weld filler material in a plane.12. The method as claimed in claim 10 , in which the material of the substrate claim 10 , of the weld filler material and of the braze material are based on a ...

Composite welding wire and method of manufacturing

The present invention is a composite welding wire for fusion welding of components manufactured of superalloys. The composite weld wire includes an inner core wire and a surface layer applied and bonded to the inner core wire. The surface layer includes alloying elements selected from among B and Si with a total bulk content of B and Si in the composite welding wire of 0.1 to 10 wt. %. Preferably the total bulk content of B is less than 4 wt. % and the surface layer comprises from 5 to 95 wt. % of the alloying elements selected from among B and Si.

FCC MATERIALS OF ALUMINUM, COBALT, CHROMIUM, AND NICKEL, AND PRODUCTS MADE THEREFROM

The present disclosure relates to new materials comprising Al, Co, Cr, and Ni. The new materials may realize a single phase field of a face-centered cubic (fcc) solid solution structure immediately below the solidus temperature of the material. The new materials may include at least one precipitate phase and have a solvus temperature of at least 1000° C. The new materials may include 2.2-8.6 wt. % Al, 4.9-65.0 wt. % Co, 4.3-42.0 wt. % Cr, and 4.8-88.6 wt. % Ni. In one embodiment, the precipitate is selected from the group consisting of the L1phase, the B2 phase, the sigma phase, the bcc phase, and combinations thereof. The new alloys may realize improved high temperature properties. 1. A composition of matter comprising:2.2-8.6 wt. % Al;4.9-65.0 wt. % Co;4.3-42.0 wt. % Cr; and4.8-88.6 wt. % Ni;the balance being any optional incidental elements and impurities.2. The composition of matter of claim 1 , wherein the incidental elements comprise up to 0.15 wt. % C claim 1 , up to 0.15 wt. % B claim 1 , up to 0.5 wt. % Hf and up to 0.5 wt. % Zr.3. The composition of matter of claim 1 , wherein the composition of matter includes 2.4-7.8 wt. % Al claim 1 , 5.5-59.1 wt. % Co claim 1 , 4.8-38.2 wt. % Cr claim 1 , and 5.3-82.2 wt. % Ni.4. The composition of matter of claim 1 , wherein the composition of matter includes 6.7-8.5 wt. % Al claim 1 , 4.9-24.4 wt. % Co claim 1 , 4.3-16.2 wt. % Cr claim 1 , and 54.4-84.1 wt. % Ni.5. The composition of matter of claim 1 , wherein the composition of matter includes 6.8-8.5 wt. % Al claim 1 , 4.9-24.4 wt. % Co claim 1 , 8.7-16.2 wt. % Cr claim 1 , and 54.4-79.6 wt. % Ni.6. The composition of matter of claim 5 , wherein the composition of matter includes 5.0-12.3 wt. % Co claim 5 , 13.2-16.2 wt. % Cr claim 5 , and 59.8-75.0 wt. % Ni.7. The composition of matter of claim 1 , wherein the composition of matter includes 7.5-7.7 wt. % Al claim 1 , 5.5-22.2 wt. % Co claim 1 , 4.8-14.8 wt. % Cr claim 1 , and 60.5-82.2 wt. % Ni.8. The composition ...

REPAIR MATERIAL PREFORM

A structural element and method for repairing a damaged portion of a metal component utilizes a preform configured to engage with the metal component and receive a repair material. The preform may be made of a material having a first melting point, and the repair material may be made of a material having a second melting point that is lower than the first melting point. The preform may be a mold configured to reconstruct the shape of the damaged portion of the metal component. The repair material may include a first material and an additive material, such as boron. The repair material may have a melting point that is approximately 40 degrees Fahrenheit lower than the melting point of the metal component. 1. A method for repairing a metal component comprising:surrounding a damaged portion of the metal component with a preform, wherein the metal component comprises a first metal material;applying a repair material comprising an additive material into the preform;heating the part and preform to bond the repair material to the metal component;removing a portion of the preform from the metal component; andleaving a layer of material with enhanced properties including one of an improved oxidation resistance and an improved wear resistance.2. The method of claim 1 , wherein the preform comprises a preform metal material that contains at least one metal species that is also present in the first metal material of the metal component.3. The method of claim 1 , wherein the preform comprises cobalt or nickel.4. The method of claim 1 , wherein the additive material of the repair material comprises a material capable of lowering a melting point of the repair material between about 10 to 60 degrees Fahrenheit.5. The method of claim 1 , wherein the additive material of the repair material comprises boron.6. The method of claim 1 , wherein the repair material comprises a repair metal material that contains at least one metal species that is also present in the first metal material.7 ...

MANGANESE-CONTAINING, COBALT-BASED HIGH-TEMPERATURE SOLDER ALLOY, POWDER, COMPONENT AND SOLDERING METHOD

A manganese-containing, cobalt-based alloy with zirconium, tantalum and carbon, and good cohesive joint connections, is provided. 19-. (canceled)10. A cobalt-based solder alloy comprising:8% by weight-16% by weight of zirconium (Zr);6% by weight-10% by weight of tantalum (Ta);0.5% by weight-1.5% by weight of carbon (C),8% by weight-12% by weight of manganese (Mn);at least 0.5% by weight of titanium (Ti); andhaving no boron (B), no silicon (Si), no germanium (Ge) and no gallium (Ga).11. The alloy as claimed in claim 10 , including 15% by weight of zirconium (Zr).12. The alloy as claimed in claim 10 , including 8% by weight of tantalum (Ta).13. The alloy as claimed in claim 10 , including 1% by weight of carbon (C).14. The alloy as claimed in claim 10 , including 10% by weight of manganese (Mn).15. The alloy as claimed in claim 10 , including 1% by weight of titanium (Ti).16. The alloy as claimed in claim 10 , consisting of zirconium (Zr) claim 10 , tantalum (Ta) claim 10 , carbon (C) claim 10 , manganese (Mn) claim 10 , cobalt (Co) and optionally titanium (Ti).17. The alloy as claimed in claim 10 , consisting of zirconium (Zr) claim 10 , tantalum (Ta) claim 10 , carbon (C) claim 10 , manganese (Mn) claim 10 , cobalt (Co) and titanium (Ti).18. The alloy as claimed in claim 10 , having at most 5% by weight of titanium (Ti).19. A powder having an alloy as claimed in .20. A component comprising claim 10 , in particular consisting of an alloy claim 10 , as claimed in .21. A soldering method using an alloy as claimed in .22. The method as claimed in claim 16 , for soldering cobalt-based alloys which is carried out with heat treatment according to the prior art for a cobalt alloy that differs markedly from the alloy in particular that has no manganese. This application claims priority to PCT Application No. PCT/EP2014/078169, having a filing date of Dec. 17, 2014, based on DE Application No. 102014200121.8, having a filing date of Jan. 8, 2014, the entire contents of which ...

LOW AND EXTRA LOW SULFUR ALLOYS FOR REPAIR

A method for repairing, refurbishing, or replacing a turbine engine component or sub-component includes the steps of providing a turbine engine component or sub-component having a site to be repaired, refurbished, or replaced providing a repair or replacement material having a sulfur content, which sulfur content is less than 10 ppm, and applying the repair or replacement material to the site on the turbine engine component to effect the repair, the refurbishment, or the replacement. 117-. (canceled)18. A method for repairing or refurbishing a turbine engine component comprising the steps of:providing a turbine engine component having a site to be repaired;providing a repair/refurbishment material having a sulfur content, which sulfur content is less than 10 ppm; andapplying the repair/refurbishment material to the site on the turbine engine component to the site on the turbine engine component to effect said repair/refurbishment.191. The method of claim , wherein said step of providing said repair/refurbishment material comprises providing a nickel based repair material having said sulfur content.201. The method of claim , wherein said step of providing said repair/refurbishment material comprises providing a cobalt based repair material having said sulfur content.211. The method of claim , wherein said step of providing said repair/refurbishment material comprises providing a repair/refurbishment material having said sulfur content below 7.0 ppm.221. The method of claim , wherein said step of providing said repair/refurbishment material comprises providing a repair/refurbishment material having said sulfur content below 1.0 ppm.231. The method of claim , wherein said step of providing said repair/refurbishment material comprises providing a repair/refurbishment material having said sulfur content in the range of from 0.5 ppm to 1.0 ppm.241. The method of claim , wherein said step of providing said repair/refurbishment material comprises providing a repair/ ...

ADDITIVE MANUFACTURING METHOD USING FOCUSED LIGHT HEATING SOURCE

The present invention relates to a method of manufacturing a component by additive manufacturing. The method comprises providing a work surface on which the component is to be manufactured, and providing at least one deposition material from which the component is to be composed. The deposition material, typically in the form of wire, is advanced to a localized deposition area where it is added to the component being manufactured. The method further comprises focusing at least one light beam of incoherent light emitted from at least one heating source in the deposition area so that the deposition material is deposited for building up the component . At least one light focusing mirror and/or lens is used to focus the incoherent light in the deposition area . The invention further relates to the use of such a method in space, such as on a space station, on a space craft or on parabolic flights for testing.

METHOD FOR PRODUCING A TURBINE ENGINE PART

The production method comprises the steps for producing a preform by selective melting, the preform comprising an assembly surface to be brazed to the part to be repaired and containing a brazing material, and then assembling the preform to the turbine engine part by diffusion brazing. The thermal amplitude of the main transformation peak (A) of the brazing material used to make the preform must at least be twice that of each of the respective thermal amplitudes of the secondary transformation peaks (A, A) of this brazing material. 1. A method for repairing a turbine engine part , characterized in that it comprises the steps of:producing a preform, layer by layer, by selectively melting a powder containing a base material identical or similar to that of the part, the preform having an assembly surface intended to be brazed to the part to be repaired and containing for this purpose a brazing material mixed with the base material, the brazing material being an alloy based on nickel, cobalt: 18 to 22%, silicon: 4 to 5%, boron: 2.7 to 3.15%, and carbon: 0 to 0.06%, all in percent by weight, said powder containing the mixture, upon heating to fusion generating heat fluxes, having a main transformation peak of the brazing material, with the greatest amplitude of heat flux, and secondary transformation peaks of the brazing material, with a lesser amplitude of heat flux;assembling the preform to the turbine engine part by diffusion brazing,wherein the amplitude of the heat flux of said main transformation peak of the brazing material used to make the preform is at least twice the amplitudes of the respective heat fluxes of the secondary transformation peaks of the brazing material, the brazing material further comprising chromium so as to limit the cracking of the parts when they are cooled.2. The method of claim 1 , wherein the quantity of chromium added ranges from 9% to 19% in percent by weight.3. The method of claim 1 , wherein the quantity of chromium added is equal to ...

FILLER ADDITIVES TO AVOID WELD CRACKING

There is provided a feed material, wherein the feed material has an elongated body that includes an amount of an alloy filler material and an amount of one or more elemental metal additives effective to scavenge at least one tramp element upon melting of the feed material. 1. A welding feed material comprising:an alloy filler material and an amount of one or more elemental metal additives effective to scavenge at least one tramp element upon melting of the welding feed material.2. The welding feed material of claim 1 , wherein the welding feed material comprises a powder cored filled wire or strip.3. The welding feed material of claim 2 , wherein the powder cored filled wire or strip comprises an outer shell surrounding an inner core of a powder material claim 2 , and wherein the inner core of powder material comprises at least the alloy filler material.4. The welding feed material of claim 3 , wherein the inner core consists of the alloy filler material and the outer shell consists of the one or more elemental metal additives.5. The welding feed material of claim 3 , wherein the inner core comprises a powder mixture of the alloy filler material and the one or more elemental metal additives.6. The welding feed material of claim 1 , wherein welding feed material comprises a coated wire or strip claim 1 , and wherein the one or more elemental metal additives are present as a coating on an elongated body of the wire or strip.7. The welding feed material of claim 1 , wherein the alloy filler material comprises a member selected from the group consisting of a nickel-based superalloy material claim 1 , a stainless steel material claim 1 , a cobalt-based alloy claim 1 , an iron-based alloy claim 1 , and a titanium-based alloy.8. The welding feed material of claim 1 , wherein the one or more elemental metal additives comprise a member selected from the group consisting of aluminum claim 1 , calcium claim 1 , cadmium claim 1 , magnesium claim 1 , titanium claim 1 , zinc ...

BORON-FREE SOLDER WITH MANGANESE AND GERMANIUM, POWDER AND REPAIR METHOD

A nickel-based alloy that includes at least nickel, manganese, and either germanium or both germanium and gallium, the alloy being free of boron or silicon, a solder based on the alloy, a powder based on the alloy, and a method of repairing a component with the alloy. 1. A nickel-based alloywhich comprises as alloying elementsat least nickel (Ni), manganese (Mn), and germanium (Ge) or both germanium (Ge) and gallium (Ga) and includes no melting point reducers.2. The alloy as claimed in claim 1 , wherein the alloy does not include gallium (Ga).3. The alloy as claimed in claim 1 , wherein the alloy further comprises gallium (Ga).4. The alloy as claimed in claim 1 , which comprises 1 at % to 60 at % manganese (Mn).5. The alloy as claimed in claim 1 , which comprises at least 2 at % manganese (Mn).6. The alloy as claimed in claim 1 , which comprises 1 at % to 15 at % germanium (Ge).7. The alloy as claimed in claim 1 , which comprises at least 2 at % germanium (Ge).8. The alloy as claimed in claim 1 , which comprises 1 at % to 23 at % gallium (Ga).9. (canceled)10. The alloy as claimed in claim 1 , which comprises no boron (B) and/or no silicon (Si).11. The alloy as claimed in claim 1 , which further comprises at least one element selected from the group consisting of molybdenum (Mo) claim 1 , titanium (Ti) claim 1 , tantalum (Ta) claim 1 , and tungsten (W).1214.-. (canceled)15. A powder which comprises an alloy as claimed in .16. A method for repairing a component claim 1 , comprising repairing the component with an alloy as claimed in .17. The method as claimed in claim 16 , in which an isothermal soldering method is carried out.18. The method as claimed in claim 17 , in which a temperature gradient method is employed during the soldering.19. The alloy as claimed in claim 1 , further comprising an alloying element in the amount of at least 1 at % selected from a group consisting of aluminum (AL) and chromium (Cr).20. The alloy as claimed in claim 4 , which comprises 1 ...

METHOD OF LASER PROCESSING A COMPONENT WITHIN AN ASSEMBLED APPARATUS USING A BOROSCOPE

A method of laser processing a component within an assembled apparatus using a boroscope, which includes a working head having first and second ends. A first optical fibre extends through the boroscope to a position between the first and second ends. A second optical fibre extends through the boroscope to the second end. A laser optical fibre extends through the boroscope. At least one lens is arranged between the first and second ends of the working head and a mirror is gimballed to the second end. The laser optical fibre directs laser light transmitted through the laser optical fibre onto the lens and then onto the mirror. A first LED is arranged at a position between the first and second ends of the working head and a second LED is arranged at the second end and an actuator device adjust the position of the mirror. 1. A method of laser processing a component within an assembled apparatus , the apparatus comprising a casing enclosing the component , the casing having at least one aperture extending there-through , the method comprising:a) inserting a boroscope through the aperture, the boroscope comprising a working head, the working head having a first end and a second end, a first optical fiber extending through the boroscope to a position between the first end and the second end of the working head, a second optical fiber extending through the boroscope to the second end of the working head, a laser optical fiber extending through the boroscope, a mirror adjustably mounted on the working head, the laser optical fiber being arranged to direct laser light transmitted through the laser optical fiber onto the mirror on the working head, a first light source arranged at a position between the first end and the second end of the working head, a second light source arranged at the second end of the working head and an actuator device to adjust the position of the mirror,b) viewing the assembled apparatus within the casing using the second optical fiber,c) viewing the ...

SUPPRESSORS AND THEIR METHODS OF MANUFACTURE

A suppressor having a body and a first connector half coupled to the body, wherein the first connector half includes a first component that includes at least one channel and a first surface; and wherein the body provides a second surface, wherein a gap between the first surface and the second surface defines at least one track; wherein the gun includes a second connector half comprising at least one protrusion, wherein the protrusion and channel have corresponding shapes that allow the protrusion to be inserted through the channel and into alignment with the track, wherein the first component may be rotated with respect to the protrusion and the body to bring the protrusion out of alignment with the channel so that the first and second surfaces clamp the protrusion to thereby secure the first connector half and second connector half with respect to each other. 128-. (canceled)29. A method of manufacturing at least a part of a suppressor using selective metal melting , wherein the suppressor includes at least one sidewall defining a cavity , and at least one baffle within the cavity , a. depositing a starter material onto a substrate;', 'b. melting the starter material to form a part of the suppressor;', 'c. repeating steps (a) and (b) so as to substantially form the at least one sidewall and the at least one baffle within the cavity with the at least one side wall and the at least one baffle monolithically formed together., 'wherein the method includes the steps of30. The method as claimed in claim 29 , wherein step c includes forming the at least one baffle within the cavity monolithically attached to an inner surface of the at least one sidewall by an integral join.31. The method as claimed in claim 30 , wherein the method forms the at least one baffle monolithically attached substantially about an inner circumference of the inner surface of the at least one sidewall.32. The method as claimed in claim 29 , wherein the suppressor comprises an end wall ...

Process for Laser-Assisted Tool Build and Repair

A tool for forming a shaped product has a support body that is fabricated from a first material, such as for instance cast iron. The first material defines a first portion of a forming surface of the tool and has a feature supported thereon. The feature has a layer of a second material that is supported on the first material of the support body, a layer of a third material that is supported on the layer of the second material and a layer of a fourth material that is supported on the layer of the third material. The layer of the fourth material, such as for instance a tool steel alloy, defines a second portion of the forming surface of the tool. During use the first portion of the forming surface and the second portion of the forming surface cooperate to form a desired shape of the shaped product. 1. A process for building a tool , comprising:providing a support body fabricated from a first material;machining a portion of the first material from the support body so as to define a first portion of a forming surface of the tool; anddepositing onto the support body a feature defining a second portion of the forming surface of the tool, comprising:depositing a layer of a second material onto the first material of the support body;depositing a layer of a third material onto the layer of the second material; anddepositing a layer of a fourth material onto the layer of the third material, the layer of the fourth material defining a second portion of the forming surface of the tool.2. The process of wherein the second material is metallurgically compatible with the first material claim 1 , the fourth material is metallurgically incompatible with the first material claim 1 , and the third material is metallurgically compatible with both the second material and the fourth material.3. The process of wherein the first material is cast iron.4. The process of wherein the second material is a cobalt-based alloy claim 1 , the third material is an iron-based alloy with high toughness ...

METHOD FOR PRODUCING A SEALING COMPONENT WITH A BODY MADE OF BORON-CONTAINING SUPERALLOY AND COATED

The invention relates to a method for producing a sealing component comprising a body (I I) made of superalloy covered by a coating () to be placed in contact with a gas turbine blade tip (). Steps are carried out in which: —a) the said new coating is produced by moulding from an alloy of the cobalt-nickel-chromium-aluminium-yttrium (CoNiCrAlY) type further containing between 0.5 and 5% by mass (wt %) of boron, —b) and the superalloy body and the said new coating () are brazed together in order to obtain the said sealing component. 1. A method for producing a sealing component comprising a body made of a superalloy covered with a new coating formed of a mixture of an alloy and boron , which can be so positioned as to contact a blade end of a gas turbine , wherein the method comprises the following steps:a) said new coating is obtained by moulding, with the alloy in the mixture being of a Cobalt-Nickel-Chrome-Aluminium-Yttrium (CoNiCrAlY) type and boron being contained in a quantity by weight (wt %) from 1.7% to 2.5%, andb) the body made of superalloy and said new coating are brazed together so as to obtain said sealing component.2. The method according to claim 1 , wherein the sealing component produced in step b) is a repaired part obtained after executing the following steps:c) prior to step b), a damaged coating is removed from a previously used sealing component which had been newly produced with a body made of a superalloy coated with a damaged coating made of an alloy of the Cobalt-Nickel-Chromium-Aluminum-Yttrium (CoNiCrAlY) type, andd) step b) is then executed, wherein the body made of a superalloy and said new coating containing boron are brazed together, instead of the removed damaged coating.3. The method according to claim 1 , wherein the sealing component produced in step b) is a repaired part obtained after executing the following steps:c) prior to such step b) said damaged coating is removed from a previously used sealing component having a body made ...

ADDITIVE MANUFACTURING METHODS AND HYBRID ARTICLES USING BRAZEABLE ADDITIVE STRUCTURES

Additive manufacturing methods include iteratively fusing together a plurality of layers of additive material to build a brazeable additive structure. The additive material comprises a mixture comprising a base alloy and a second alloy and the second alloy comprises a sufficient amount of melting point depressant to have a lower melting temperature than the base alloy. 1. An additive manufacturing method comprising:iteratively fusing together a plurality of layers of additive material to build a brazeable additive structure;wherein, the additive material comprises a mixture comprising a base alloy and a second alloy; and,wherein the second alloy comprises a sufficient amount of melting point depressant to have a lower melting temperature than the base alloy.2. The additive manufacturing method of claim 1 , further comprising joining the brazeable additive structure to a surface of a base structure to form a hybrid article.3. The additive manufacturing method of claim 2 , wherein joining comprises applying a heat sufficient to at least partially melt the second alloy without melting the base alloy.4. The additive manufacturing method of claim 2 , wherein the surface of the base structure comprises one or more surface features claim 2 , and wherein the brazeable additive structure at least partially encloses the one or more surface features when joined to the base structure.5. The additive manufacturing method of claim 1 , wherein the brazeable additive structure comprises a contoured profile that substantially matches a surface profile of the base structure.6. The additive manufacturing method of claim 1 , wherein the base alloy comprises a nickel claim 1 , cobalt or iron based superalloy.7. The additive manufacturing method of claim 1 , wherein the second alloy comprises a melting point depressant comprising boron claim 1 , silicon claim 1 , germanium and/or manganese.8. The additive manufacturing method of claim 1 , wherein the additive material comprises claim 1 , ...

COMPOSITE WELDING RODS AND ASSOCIATED CLADDED ARTICLES

Welding rods and associated cladded articles are described herein. Briefly, a welding rod comprises a hard particle component dispersed in a nickel-based alloy matrix or cobalt-based alloy matrix, the hard particle component comprising tungsten carbide particles having an average size of less than 45 μm, and the nickel-based alloy matrix or the cobalt-based alloy matrix comprising at least one metal carbide forming element. 1. A welding rod comprising:a hard particle component dispersed in a continuous nickel-based alloy matrix or cobalt-based alloy matrix of the welding rod, the hard particle component comprising tungsten carbide particles having an average size less than 45 μm, and the nickel-based alloy matrix or cobalt-based alloy matrix comprising at least one metal carbide forming element.2. The welding rod of claim 1 , wherein the at least one metal carbide forming element is selected from the group consisting of chromium claim 1 , molybdenum claim 1 , titanium claim 1 , silicon claim 1 , and boron.3. The welding rod of claim 2 , wherein the at least one metal carbide forming element is present in the nickel-based alloy matrix or cobalt-based alloy matrix in an amount less than 10 weight percent.4. The welding rod of claim 2 , wherein the at least one metal carbide forming element is present in the nickel-based alloy matrix or cobalt-based alloy matrix in an amount less than 5 weight percent.5. The welding rod of claim 1 , wherein the tungsten carbide particles comprise macrocrystalline tungsten carbide claim 1 , cast tungsten carbide claim 1 , sintered cemented carbide claim 1 , or mixtures thereof.6. The welding rod of claim 5 , wherein the sintered cemented carbide particles comprise metallic binder in an amount of 3 to 20 weight percent.7. The welding rod of claim 1 , wherein the hard particle component further comprises particles selected from the group consisting of metal carbides claim 1 , metal nitrides claim 1 , and metal carbonitrides.8. The welding ...

BRAZE METHODS AND COMPONENTS WITH HEAT RESISTANT MATERIALS

Braze methods include providing a substrate comprising a pre-sintered preform disposed thereon, wherein the pre-sintered preform comprises a mixture comprising a base alloy comprising about 30 weight percent to about 90 weight percent of the mixture and a second alloy comprising a sufficient amount of melting point depressant to have a lower melting temperature than the base alloy. Braze methods further include at least partially covering the pre-sintered preform with a heat resistant material, wherein a melt temperature of the heat resistant material is higher than a melt temperature of the pre-sintered preform, and heating the pre-sintered preform on the substrate. 1. A braze method comprising:providing a substrate comprising a pre-sintered preform disposed thereon, wherein the pre-sintered preform comprises a mixture comprising a base alloy comprising about 30 weight percent to about 90 weight percent of the mixture and a second alloy comprising a sufficient amount of melting point depressant to have a lower melting temperature than the base alloy;at least partially covering the pre-sintered preform with a heat resistant material, wherein a melt temperature of the heat resistant material is higher than a melt temperature of the pre-sintered preform; and,heating the pre-sintered preform on the substrate.2. The braze method of claim 1 , wherein the heat resistant material comprises a separate pre-sintered preform.3. The braze method of claim 2 , wherein the separate pre-sintered preform comprises a base alloy and a second alloy claim 2 , wherein the base alloy comprises a compositional range of claim 2 , by weight claim 2 , about 27.0 to 30.0% molybdenum claim 2 , 16.5 to 18.5% chromium claim 2 , 3.0 to 3.8% silicon claim 2 , up to 1.5% iron claim 2 , up to 1.5% nickel claim 2 , up to 0.15% oxygen claim 2 , up to 0.08% carbon claim 2 , up to 0.03% phosphorus claim 2 , up to 0.03% sulfur claim 2 , and the balance cobalt claim 2 , and wherein the second alloy ...

BRAZE METHODS AND COMPONENTS FOR TURBINE BUCKETS

Braze methods for turbine buckets include providing the turbine bucket comprising a modification surface, wherein the modification surface comprises a non-z-notch contact surface, disposing a pre-sintered preform on the modification surface and, heating the pre-sintered preform on the modification surface to bond the pre-sintered preform to the turbine bucket at the modification surface. 1. A braze method for a turbine bucket , the braze method comprising:providing the turbine bucket comprising a modification surface, wherein the modification surface comprises a non-z-notch contact surface;disposing a pre-sintered preform on the modification surface; and,heating the pre-sintered preform on the modification surface to bond the pre-sintered preform to the turbine bucket at the modification surface.2. The braze method of claim 1 , wherein the non-z-notch contact surface comprises one or more seal rails.3. The braze method of claim 1 , wherein the non-z-notch contact surface comprises one or more z-notch adjacent surfaces.4. The braze method of claim 1 , wherein the non-z-notch contact surface comprises at least a portion of an angel wing.5. The braze method of claim 1 , wherein the pre-sintered preform comprises a shape matching the modification surface it is disposed on.6. The braze method of claim 1 , wherein the pre-sintered preform comprises a base alloy and a second alloy claim 1 , wherein the base alloy comprises a compositional range of claim 1 , by weight claim 1 , about 27.0 to 30.0% molybdenum claim 1 , 16.5 to 18.5% chromium claim 1 , 3.0 to 3.8% silicon claim 1 , up to 1.5% iron claim 1 , up to 1.5% nickel claim 1 , up to 0.15% oxygen claim 1 , up to 0.08% carbon claim 1 , up to 0.03% phosphorus claim 1 , up to 0.03% sulfur claim 1 , and the balance cobalt.7. The braze method of claim 6 , wherein the second alloy comprises a compositional range of claim 6 , by weight claim 6 , about 22.9 to 24.75% chromium claim 6 , 9.0 to 11.0% nickel claim 6 , 6.5 to 7.6% ...

SUPPRESSORS AND THEIR METHODS OF MANUFACTURE

A suppressor having a body and a first connector half coupled to the body, wherein the first connector half includes a first component that includes at least one channel and a first surface; and wherein the body provides a second surface, wherein a gap between the first surface and the second surface defines at least one track; wherein the gun includes a second connector half comprising at least one protrusion, wherein the protrusion and channel have corresponding shapes that allow the protrusion to be inserted through the channel and into alignment with the track, wherein the first component may be rotated with respect to the protrusion and the body to bring the protrusion out of alignment with the channel so that the first and second surfaces clamp the protrusion to thereby secure the first connector half and second connector half with respect to each other. 1. A method of manufacturing at least a part of a suppressor , wherein the at least one part of the suppressor includes an end wall and at least one sidewall defining an outer housing with an internal cavity , an outlet in the end wall for a bullet to exit the suppressor , and at least one baffle within the cavity , a. depositing a starter material onto a substrate;', 'b. melting the starter material to form a layer of the part of the suppressor; and', 'c. repeating steps (a) and (b) in a build direction from an end of the outer housing so as to form the outer housing and the at least one baffle within the cavity, with the outer housing and the at least one baffle monolithically formed together in a monocoque structure., 'wherein the method comprises manufacturing the part of the suppressor using selective metal melting by2. The method as claimed in claim 1 , wherein the build direction is from the end wall of the outer housing so as to form the end wall and the at least one side wall extending from the end wall.3. The method as claimed in claim 1 , wherein the build direction to parallel to the side wall.4. ...

一种球形自熔性合金钎料的制造方法

一种球形自熔性合金钎料的制造方法，包括如下步骤：准备自熔性合金粉末；准备自熔性合金粉末与碳材料粉末或与陶瓷材料粉末的均匀混合粉末；高温热处理使自熔性合金熔融并凝固成金属球；高温热处理的温度是达到所述合金熔融的温度，优选是自熔性合金熔点温度以上40到100℃的范围内；分离碳材料粉末或陶瓷材料粉末获得微米、纳米球形自熔性合金粉末。方法简单，可规模化生产，无需特殊精密喷射设备，成本较低，而且制造的球形合金粉表面光洁，流动性好，有利于热喷涂送粉和堆焊填料。

Quaternary pb-free solder composition incorporating sn-ag-cu-in

A Sn-Ag-Cu-In quaternary Pb-free solder composition is provided to suppress an increase in the cost of the Pb-free solder composition and sufficiently secure processability and mechanical properties of the Pb-free solder composition as a solder material by adding a proper amount of indium(In) and optimizing the content of silver(Ag). A Sn-Ag-Cu-In quaternary Pb-free solder composition comprises not less than 0.3% to less than 2.5% by weight of silver(Ag), not less than 0.2% to less than 2% by weight of copper(Cu), not less than 0.2% to less than 0.8% by weight of indium(In), and the balance of tin(Sn). The Sn-Ag-Cu-In quaternary Pb-free solder composition further comprises not less than 0.0001% to less than 1% by weight of one element or a mixture of at least two elements selected from phosphorous(P), germanium(Ge), gallium(Ga), aluminum(Al), and silicon(Si). to improve oxidation resistance of the Pb-free solder composition. The Sn-Ag-Cu-In quaternary Pb-free solder composition further comprises not less than 0.0001% to less than 2% by weight of one element or a mixture of at least two elements selected from zinc(Zn) and arsenic(As) to improve interfacial reaction characteristics of the Pb-free solder composition.

Cellular structure, abradable seat and method of its forming

FIELD: mechanical engineering; turbines. SUBSTANCE: proposed abradable seal is designed for turbines. It contains new cellular made of metal foil or sheet of high manufacturability facilitating process of soldering and featuring high resistance to oxidation and high structural integrity after soldering to metal support structure. Foil or sheets of alloy MCrAIY (where M-Ni, Fe, Co or their combinations) are good manufacturing of such cellular structure. Such making of abradable seal provides high and long-time dimensional stability at high temperature. EFFECT: improved quality of seal. 13 cl, 4 dwg ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß RU (19) (11) 2 277 637 (13) C2 (51) ÌÏÊ F01D 11/08 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2003115879/06, 26.11.2001 (24) Äàòà íà÷àëà îòñ÷åòà ñðîêà äåéñòâè ïàòåíòà: 26.11.2001 (72) Àâòîð(û): ÕÝÌÌÅÐÑËÈ Ðè÷àðä ×àðëç (GB), ØÏÎÐÅÐ Äèòåð Ðóäîëüô (AT) (73) Ïàòåíòîîáëàäàòåëü(è): ÍÅÎÌÅÒ ËÈÌÈÒÅÄ (GB) R U (30) Êîíâåíöèîííûé ïðèîðèòåò: 27.11.2000 US 09/722,060 (43) Äàòà ïóáëèêàöèè çà âêè: 20.11.2004 (45) Îïóáëèêîâàíî: 10.06.2006 Áþë. ¹ 16 2 2 7 7 6 3 7 (56) Ñïèñîê äîêóìåíòîâ, öèòèðîâàííûõ â îò÷åòå î ïîèñêå: US 4063742 A, 20.12.1977. US 2902589 A, 01.09.1959. US 3867061 A, 18.02.1975. US 5096376 A, 17.03.1992. US 3365172 A, 23.01.1968. SU 1799429 A3, 28.02.1992. RU 2153112 C2, 20.07.2000. SU 1749496 A, 23.07.1992. (86) Çà âêà PCT: CA 01/01676 (26.11.2001) C 2 C 2 (85) Äàòà ïåðåâîäà çà âêè PCT íà íàöèîíàëüíóþ ôàçó: 26.05.2003 R U 2 2 7 7 6 3 7 (87) Ïóáëèêàöè PCT: WO 02/42610 (30.05.2002) Àäðåñ äë ïåðåïèñêè: 119034, Ìîñêâà, Ïðå÷èñòåíñêèé ïåð., ä.14, ñòð.1, Ãîóëèíãç Èíòåðíýøíë Èíê., ïàò.ïîâ. Â.Í.Äåìåíòüåâó (54) ÑÎÒÎÂÀß ÑÒÐÓÊÒÓÐÀ, ÈÑÒÈÐÀÅÌÎÅ ÓÏËÎÒÍÅÍÈÅ È ÑÏÎÑÎÁ ÅÃÎ ÎÁÐÀÇÎÂÀÍÈß (57) Ðåôåðàò: Èñòèðàåìîå óïëîòíåíèå ïðåäíàçíà÷åíî äë òóðáèí. Îíî ñîäåðæèò íîâóþ ñîòîâóþ ÷åèñòóþ ñòðóêòóðó, èçãîòîâëåííóþ èç ìåòàëëè÷åñêîé ôîëüãè èëè ëèñòà, îáëàäàþùóþ õîðîøåé ...

Pb FREE SOLDERING MATERIALS FOR MOUNTING ELECTRONIC COMPONENT

본 발명은 인쇄회로기판에 전자부품을 실장하는 방법 및 전자부품의 접합 공정을 단축하고 보다 신뢰성이 있는 접합을 가능하게 하는 무연 납땜 재료를 제공하는 것을 그 목적으로 한다. 이를 위하여 저융점 납땜 합금분말과 고융점 납땜 합금분말을 혼합한 땜납을 제조하여 땜납의 융점을 낮게 하는 동시에 납땜이 불규칙하게 되는 현상을 방지하고자 하는 것이다. 이러한 납땜 재료로 인하여 납땜의 용융온도를 손쉽게 제어할 수 있고 고융점 납땜 후 저융점 납땜을 하는 두 개의 공정을 하나로 단축하여 생산성을 향상시키는 동시에 부품의 수율을 획기적으로 향상시킬 수 있다. 이와 더불어 저융점 납땜 분말을 65~95wt%, 고융점 땜납 분말 5~35 wt%를 포함하여 전자부품의 접합속도 및 온도를 획기적으로 낮추고 접합 신뢰성을 향상시킨 땜납 분말을 제공하고자 하는 것이다. It is an object of the present invention to provide a method for mounting electronic components on a printed circuit board and a lead-free soldering material for shortening the bonding process of electronic components and enabling more reliable bonding. For this purpose, a solder in which a low-melting-point braze alloy powder and a high-melting-point braze alloy powder are mixed to reduce the melting point of the solder and prevent irregular soldering. The melting temperature of the solder can be easily controlled by the soldering material, and the two processes of performing the low melting point soldering after the high melting point soldering can be shortened to improve the productivity, and the yield of the parts can be remarkably improved. In addition, it is intended to provide a solder powder including 65 to 95 wt% of a low melting point solder powder and 5 to 35 wt% of a high melting point solder powder, drastically lowering the bonding speed and temperature of electronic components and improving bonding reliability.

Pre-sintered billet for repair of gas turbine service starting components

FIELD: gas turbine component repairing methods. SUBSTANCE: inventions group discloses a pre-sintered billet (114) and a method (100) for repairing a gas turbine component (102) made of a superalloy to obtain a connecting layer of a brazed assembly (116), which provides the component with additional thermal protection. The pre-sintered workpiece (114) is applied to the repair surface (110) of the turbine component (102) and heated to form a brazed assembly (116) containing a replacement protective coating (118) on the repair surface (110) while cooling the workpiece (114) and component (102) turbines. The preform (114) is formed from a mixture of tie layer powder and braze powder. EFFECT: protective coating (118) exhibits excellent temperature and oxidation resistance, high adhesion to superalloy surfaces, and low wear over the life of the corresponding component (102). 10 cl, 8 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 763 527 C1 (51) МПК B23P 6/00 (2006.01) B23K 1/00 (2006.01) B23K 35/30 (2006.01) C22C 19/07 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК B23P 6/00 (2021.05); B23K 1/00 (2021.05); B23K 35/30 (2021.05); C22C 19/07 (2021.05) (21)(22) Заявка: 2021105650, 06.08.2019 (24) Дата начала отсчета срока действия патента: Дата регистрации: (73) Патентообладатель(и): СИМЕНС ЭНЕРДЖИ, ИНК. (US) 30.12.2021 (56) Список документов, цитированных в отчете о поиске: RU 2281845 С1, 20.08.2006. RU 2240214 С1, 20.11.2004. RU 2310555 C2, 20.11.2007. FR 2978070 A1,25.01.2013. US 6670046 B1, 30.12.2003. 09.08.2018 US 16/059,490; 16.07.2019 US 16/512,433 (45) Опубликовано: 30.12.2021 Бюл. № 1 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 09.03.2021 (86) Заявка PCT: 2 7 6 3 5 2 7 Приоритет(ы): (30) Конвенционный приоритет: R U 06.08.2019 (72) Автор(ы): ГХУНАКИКАР, Сомеш Дж. (US), ЯРБРО, Джеймс А. (US), ГАРСИЯ, Марк А. (US) 2 7 6 3 5 2 7 R U C 1 C 1 US 2019/045262 (06.08.2019) (87) Публикация заявки ...

Gas tungsten arc welding using flux coated electrodes

본 발명은 가스 텅스텐 아크 용접 절차를 사용하여 용접물을 적용하기 위한 방법에 관한 것이다. 필러 요소가 용접 위치에 제공된다. 필러 요소(14)는 용접물의 형성중 사용되는 제 1 재료 및 재료의 용융 시 슬래그를 발생시킬 수 있는 제 2 재료를 포함한다. 용접 아크(30)는 용탕을 형성하도록 용접 위치(42)에 가까운 제 1 및 제 2 부품(16, 18)들 및 필러 요소의 부분들을 용융하는 열을 제공한다. 제 2 재료는 용융하여 슬래그를 형성하며, 이 슬래그는 용탕의 외부면으로 유동하고 대기 중의 반응성 원소들로의 노출로부터 용탕을 차폐한다. 용탕의 냉각 시, 용탕은 제 1 부품과 제 2 부품 사이에 용접물을 형성하도록 응고된다.

Manufacturing method for functionally gradient material capable of reinforcing tuyere

本发明涉及一种风口强化功能梯度材料的制造方法，先清理铜基体风口内壁和小端油污、灰尘，预热到500℃左右；在铜基体风口上堆焊Ni202过渡层；在过渡层上堆焊CoGrW强化层；对强化层进行喷砂毛化处理使表面平整，整个堆焊层厚3mm左右；为了防止CoGrW强化层在使用中应导热系数不同而出现裂纹，对CoGrW强化层预热后，再等离子喷涂厚0.5mm的ZrO 2 热障涂层。本发明堆焊有过渡层、强化层，等离子喷涂热障涂层，堆焊层可达到使用所需要的厚度和冶金结合强度，保证使用时不脱落，又能使铜基体风口工作时受热障涂层保护，减小强化层因热应力的开裂或脱落，硬度高、耐磨性好、成本低、生产效率高。使用寿命达到10个月。

Cobalt-based alloy with germanium and soldering method

A cobalt-based alloy comprises (in wt.%) nickel (7.0-9.0, preferably 7.5-8.5), chromium (17-21, preferably 18.0-20.5), tungsten (5.0-6.5, preferably 5.1-6.1), tantalum (2.0-4.0, preferably 2.5-3.2), titanium (0.1-0.3, preferably 0.2), germanium (13-27, preferably 14-26), carbon (18-22, preferably 0.4-0.6) and zirconium (0.2-0.7, preferably 0.3-0.6). The alloy optionally contains molybdenum, iron or manganese as impurities. An independent claim is included for method for repairing a substrate, in particular a nickel-based substrate.

Remelting method and subsequent filling and resulting component

Remelting and filling a defect (7) of a surface (19) of a substrate (4), comprises remelting the defect to form a depression (28), and filling the formed depression. An independent claim is also included for a component comprising a remelted region and a solder region above the remelted region.

Cobalt-based alloy comprising germanium and method for soldering

The invention relates to cobalt-based alloys comprising germanium having a higher melting point than nickel-based alloys, such that they are used advantageously for repairing or treating components used at high temperatures.

Cobalt-based alloy comprising germanium and method for soldering

Cobalt-based solder alloys are proposed. The cobalt-based solder alloys have germanium. The germanium has a higher melting point than nickel-based alloys such that the germanium is used advantageously for repairing or treating components having the nickel-based alloys used at high temperatures. The components are repaired or treated by soldering using the cobalt-based solder alloys.

Remelting method and subsequent refilling and component

The invention relates to a method for remelting and refilling a defect (7) in a surface (19) of a substrate (4), wherein the defect (7) is remelted and wherein a hollow (28) is produced and wherein the hollow (28) that has been produced is refilled, and also to a component having a remelted region (25) and a solder region (31) thereover. In particular, a nickel- or cobalt-based substrate (4) is remelted by a laser remelting method, and subsequently the hollow (28) that is produced is refilled by a laser application method, in particular by soldering.

Super alloy material with improved weldability

Method for manufacturing single crystal structures

Method of producing single crystal superalloy structures, parts or workpieces on single crystal substrates involves: (a) melting the substrate surface with an energy beam; (b) supplying the molten region with material which is to be formed as a single crystal structure; (c) completely melting the supplied material; and (d) regulating and/or controlling the energy supply such that the solidification velocity and the temperature gradient in the shown GV diagram lies in the dendritic crystalline region outside the globular region. Preferably, the substrate and/or the supplied material consists of a Co base, Fe base or Ni base superalloy such as CMSX-4.

Cobalt-base composition

An improved cobalt-base braze alloy composition and method for diffusion brazing are provided for use in repairing superalloy articles, such as gas turbine engines, power generation turbines, refinery equipment, and heat exchangers. The improved cobalt-base braze alloy composition includes nickel; at least one element selected from the group of rhenium, palladium, and platinum; at least one element selected from the group of boron and silicon; and the remaining balance consists of cobalt. This composition may also include aluminum, and the composition may be combined with one or more powdered base metal superalloy compositions to form an improved diffusion braze alloy mixture. In the improved method for repairing superalloy articles, the foregoing mixture is applied to a region of the superalloy article to be repaired. The mixture is then heated to melt the cobalt-base braze alloy, thereby joining the base metal superalloy powder particles together, and joining the entire mixture to the region being repaired. The molten mixture is next subjected to a diffusion braze heat treatment cycle in order to break down undesirable boride and silicide phases and to diffuse the melting point depressants into the mixture. In a preferred embodiment, the long term diffusion heat treatment cycle consists of heating the repaired article to 2000° F., holding that temperature for 2 hours, heating the repaired article to 2100° F., holding that temperature for 22 hours, and cooling the article to 250° F. After cooling, an environmental coating is applied to the final repair composite, and this composite significantly improves the cyclic oxidation resistance of the coating compared to the properties of the superalloy base metal.

Welding wire

(57)【要約】本公報は電子出願前の出願データであるた め要約のデータは記録されません。

Composition welding wire

FIELD: metallurgy. SUBSTANCE: composition welding wire for repair by fusible welding of the gas turbine engine parts made of heat-resisting alloys based on nickel, cobalt or iron, comprises a core and a surface layer applied and connected to it, containing boron and/or silicon. The total content of boron and/or silicon in the composition welding wire is calculated by formula where C ∑ is the total content of boron and/or silicon in the welding wire; D' is the diameter of the welding wire; C SL is the content of boron and/or silicon in the surface layer; T is the thickness of the surface layer, wherein C ∑ is 0.1-10 wt %. EFFECT: prevention of the cracking in the heat affected zone due to the fusible welding and argonarc welding of the dispersion-hardened heat-resisting alloys. 17 cl, 13 dwg, 1 tbl, 6 ex РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 613 006 C2 (51) МПК B23K 35/22 (2006.01) B23K 35/40 (2006.01) B32B 1/08 (2006.01) C23C 30/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ 2015108666, 24.10.2012 (24) Дата начала отсчета срока действия патента: 24.10.2012 Дата регистрации: (73) Патентообладатель(и): ЛИБУРДИ ИНЖИНИРИНГ ЛИМИТЕД (CA) Приоритет(ы): (22) Дата подачи заявки: 24.10.2012 (43) Дата публикации заявки: 27.09.2016 Бюл. № 27 5332628 A, 26.07.1994. RU 2415742 C2, 10.01.2011. RU 2294272 C1, 27.02.2007. US 5156321 A, 20.10.1992. (85) Дата начала рассмотрения заявки PCT на национальной фазе: 12.03.2015 (86) Заявка PCT: CA 2012/000980 (24.10.2012) (87) Публикация заявки PCT: Адрес для переписки: 129327, Москва, а/я 64, Туленинову А.Н. C 2 C 2 WO 2014/063222 (01.05.2014) 2 6 1 3 0 0 6 (54) КОМПОЗИЦИОННАЯ СВАРОЧНАЯ ПРОВОЛОКА R U 2 6 1 3 0 0 6 (45) Опубликовано: 14.03.2017 Бюл. № 8 (56) Список документов, цитированных в отчете о поиске: US 4185136 A, 22.01.1980. US R U 14.03.2017 (72) Автор(ы): ГОНЧАРОВ, Александр Б. (CA), ЛИБУРДИ, Джозеф (CA), ЛОУДЕН, Пол (CA), ХЭСТИ, ...

Method for forming alloy layer upon aluminum alloy substrate by irradiating with a CO2 laser, on substrate surface, alloy powder containing substance for alloying and titanium or manganese

In this method forforming an alloy layer on the surface of an aluminum alloy substrate, a powder for alloying, containing a substance to be alloyed with the substrate and an element selected from the group consisting of titanium and manganese, is disposed upon the surface of the aluminum alloy substrate. This powder is then irradiated with C0 2 laser, so asto be melted and fused together with a surface portion of the aluminum alloy substrate, so that these two are alloyed together. The powder for alloying may be a powder of an alloy of the substance to be alloyed with the aluminum alloy substrate and the element selected from the group consisting of titanium and manganese. or alternatively may be a mixture of a powder of the substance to be alloyed with the aluminum alloy substrate and a powder of the element selected from the group consisting of titanium and manganese.

Method for forming alloy layer upon aluminum alloy substrate by irradiating with a co2 laser, on substrate surface, alloy powder containing substance for alloying and titanium or manganese

In this method for forming an alloy layer on the surface of an aluminum alloy substrate, a powder for alloying, contain­ ing a substance to be alloyed with the substrate and an el­ ement selected from the group consisting of titanium and manganese, is disposed upon the surface of the aluminum alloy substrate. This powder is then irradiated with CO₂ laser, so as to be melted and fused together with a surface portion of the aluminum alloy substrate, so that these two are alloyed together. The powder for alloying may be a powder of an alloy of the substance to be alloyed with the aluminum alloy sub­ strate and the element selected from the group consisting of titanium and manganese, or alternatively may be a mixture of a powder of the substance to be alloyed with the aluminum alloy substrate and a powder of the element selected from the group consisting of titanium and manganese.

Slide component and method for production of cladding on a substrate

This invention refers to a slide component (100), used in internal combustion engines, provided with a metal-based substrate material (1) and a protective liner (R), with the slide component (100) comprising at least two main elements (2, 3), the first one (2) composed by an element with high resistance to corrosion, and the second element (3) providing increase of the resistance to wear and/or presenting lower friction than the substrate material, both of them covering at least one of the surfaces of the slide component (100).

Method for welding super-alloy articles

FIELD: welding processes and equipment, namely welding hard-to-weld products of super-alloys, possibly in different branches of machine engineering. SUBSTANCE: method comprises steps of preliminarily heating the whole zone of welded seam and region near said zone till yielding temperature higher than aging temperature and lower than initial melting temperature of super-alloy; sustaining such temperature during welding process and at solidifying of welded seam; increasing temperature of welded article till temperature of releasing mechanical stresses; cooling welded article till temperature lower than temperature range of dispersed solidification of primary gamma-phase at rate lowering separation of primary gamma-phase. EFFECT: possibility for making welded articles having no cracking in welded seam and in base alloy. 12 cl, 3 dwg, 1 tbl, 2 ex ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß (19) RU (51) ÌÏÊ 7 (11) 2 265 505 (13) C2 B 23 K 9/23, 28/02//B 23 K 103:08 ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2002127808/02, 21.02.2001 (72) Àâòîð(û): ÔÎÑÒÅÐ Ìàéêë (US), ÀÏÄÅÃÐÎÓ Êåâèí (US) (24) Äàòà íà÷àëà äåéñòâè ïàòåíòà: 21.02.2001 (30) Ïðèîðèòåò: 17.03.2000 US 09/527,362 (43) Äàòà ïóáëèêàöèè çà âêè: 10.04.2004 (45) Îïóáëèêîâàíî: 10.12.2005 Áþë. ¹ 34 2 2 6 5 5 0 5 (56) Ñïèñîê äîêóìåíòîâ, öèòèðîâàííûõ â îò÷åòå î ïîèñêå: US 5106010 À, 21.04.1992. SU 1362583 A, 30.12.1987. RU 2058871 C1, 27.04.1996. RU 2129166 C1, 20.04.1999. US 4465224 À, 14.08.1984. JP 11104882 À, 20.04.1999. JP 63026279 À, 03.02.1988. Ñïðàâî÷íèê «Ñâàðêà â ìàøèíîñòðîåíèè» ïîä ðåä. ÀÊÓËÎÂÀ À.È. Ò.2. Ì.: Ìàøèíîñòðîåíèå, 1978, ñ.268-269, 272273, 274-275, 283-284. (86) Çà âêà PCT: US 01/40155 (21.02.2001) C 2 C 2 (85) Äàòà ïåðåâîäà çà âêè PCT íà íàöèîíàëüíóþ ôàçó: 17.10.2002 R U 2 2 6 5 5 0 5 (87) Ïóáëèêàöè PCT: WO 01/87528 (22.11.2001) Àäðåñ äë ïåðåïèñêè: 129010, Ìîñêâà, óë. Á. Ñïàññêà , 25, ñòð.3, ÎÎÎ "Þðèäè÷åñêà ôèðìà Ãîðîäèññêèé è ...

Method and system for additive production and recovery using sintered wire manufacturing and feeding in situ

FIELD: sintered wire manufacturing.SUBSTANCE: group of inventions is intended for the manufacture of sintered wire and feedingin situinto a system for laser surfacing with filler wire in the additive production and/or recovery of a super-alloy component. A high-pressure container is connected to a system for feeding at least two powders to the powder-mixing zone. A heating device placed in the high-pressure container heats the mixture to ensure liquid-phase sintering of the powders and the formation of sintered wire, which is continuously fed to the system for laser deposition of a deposited material layer on the base material. The welding system contains a laser energy source and a welding head for receiving the specified sintered wire. The sintered wire is deposited immediately after its manufacture. The higher plastic properties of the wire material in the heated state allow it to be produced from a brittle material.EFFECT: use of sintered wire reduces the presence of pollutants during laser surfacing, while the sintered wire provides a chemical composition similar to that of the base material of the super-alloy component.19 cl, 3 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 750 316 C1 (51) МПК B23K 26/342 (2014.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК B23K 26/342 (2021.01) (21)(22) Заявка: 2020134933, 27.03.2018 (24) Дата начала отсчета срока действия патента: Дата регистрации: (73) Патентообладатель(и): СИМЕНС ЭНЕРДЖИ, ИНК. (US) 25.06.2021 (56) Список документов, цитированных в отчете о поиске: US 2017182558 A, 29.06.2017. DE 102015219341 A1, 13.04.2017. WO 2017096050 A1, 08.06.2017. CN 201720607 U, 26.01.2011. RU 2613006 C2, 14.03.2017. (45) Опубликовано: 25.06.2021 Бюл. № 18 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 27.10.2020 (86) Заявка PCT: US 2018/024523 (27.03.2018) 2 7 5 0 3 1 6 Приоритет(ы): (22) Дата подачи заявки: 27.03.2018 R U 27.03.2018 (72) Автор(ы): БУРБАУМ, Бернд ...

High temperature material conveying member

METHOD FOR CORRECTING METAL PARTS

1. Способ исправления металлических деталей, соединенных между собой высокотемпературной пайкой, отличающийся тем, что исправляют паяные зоны при помощи лазера для исправления, причем пиковая мощность лазера для исправления заключена между 1500 Вт и 3000 Вт, при этом лазер для исправления используется в импульсном режиме. ! 2. Способ по п.1, в котором исправление паяных зон осуществляют с использованием присадочного металла, нанесенного на паяные зоны. ! 3. Способ по п.2, в котором присадочный металл представлен в виде порошка, пасты, проволоки или предварительно спеченной формы. ! 4. Способ по п.2, в котором присадочный металл совместим с присадочным металлом, использовавшимся во время первоначальной пайки металлических деталей. ! 5. Способ по п.1, в котором лазером для исправления управляют полуручным способом. ! 6. Способ по п.1, в котором металлические детали выполнены из сплава на основе никеля или кобальта. ! 7. Способ по п.1, в котором время нарастания лазерного импульса меньше его времени падения. ! 8. Способ по п.1, в котором металлические детали были соединены между собой при помощи пайки в печи. ! 9. Способ по п.1, в котором время импульса лазера для исправления заключено между 5 и 15 мс. ! 10. Способ по п.1, в котором частота лазера для исправления заключена между 4 и 8 Гц. ! 11. Способ по п.1, в котором защищают паяемые металлические детали от окисления при помощи устройства газовой защиты от окисления. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2008 139 469 (13) A (51) МПК B23K 26/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21), (22) Заявка: 2008139469/02, 03.10.2008 (71) Заявитель(и): СНЕКМА (FR) (30) Конвенционный приоритет: 05.10.2007 FR 0707011 R U (57) Формула изобретения 1. Способ исправления металлических деталей, соединенных между собой высокотемпературной пайкой, отличающийся тем, что исправляют паяные зоны при помощи лазера для исправления, причем пиковая мощность лазера для ...

METHOD FOR CONNECTING AT LEAST TWO COMPONENTS, METHOD FOR GIVING EROSION RESISTANCE TO A COMPONENT AND TURBIN SHOVEL

1. Способ (500) соединения по меньшей мере двух компонентов, включающийиспользование (502) устройства (30) лазерного плакирования,выравнивание (504) первого компонента (40), имеющего первую соединительную поверхность (42), так что эта поверхность расположена смежно со второй соединительной поверхностью (52) второго компонента (50),соединение (510) первой соединительной поверхности (42) и второй соединительной поверхности (52) первого и второго компонентов (40, 50) вдоль соединительной плоскости (34) путем лазерного плакирования, причем соединительный материал (32) из устройства (30) лазерного плакирования обеспечивает по меньшей мере один соединительный слой (36) между первой соединительной поверхностью (42) и второй соединительной поверхностью (52), образующими угол (82, 84) скоса.2. Способ (500) по п.1, в котором дополнительно обеспечивают сварку (90) прихваточным швом или прикрепление первого компонента (40) ко второму компоненту (50) до проведения указанного этапа соединения.3. Способ (500) по п.1, в котором указанный угол (82) скоса первой соединительной поверхности (42) равен от приблизительно 0° до приблизительно 45° относительно соединительной плоскости (34).4. Способ (500) по п.1, в котором указанный угол (84) скоса второй соединительной поверхности (52) равен от приблизительно 0° до приблизительно 45° относительно соединительной плоскости (34).5. Способ (500) по п.1, в котором второй компонент (50) является противоэрозионной наплавкой (54).6. Способ (500) по п.1, в котором обеспечивают плакирование первого компонента (40) по меньшей мере одним промежуточным слоем (70) до проведения этапа (510) соединения.7. Способ (500) по п.1, в котором обеспечивают плакирование второго компонент РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F01D 5/28 (13) 2013 113 680 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2013113680/06, 27.03.2013 (71) Заявитель(и): Дженерал Электрик Компани (US) Приоритет(ы): (30) ...

Method of brazing and using a brazing foil for induction brazing

Ein Verfahren zum Hartlöten wird bereitgestellt, bei dem eine amorphe oder teilamorphe Hartlotfolie mit einer Zusammensetzung, die einen Metalloidgehalt von 10 bis 30 Atom% aufweist, an einer Verbindungsstelle zweier oder mehrerer Teile angeordnet wird. Die Hartlotfolie weist die Gestalt eines gewickelten Ringbands auf, das einen kurzgeschlossenen Strompfad zwischen mindestens zwei aufeinanderliegenden Lagen aufweist. Die Hartlotfolie wird induktiv erwärmt geschmolzen und eine hartgelötete Verbindung der Teile erzeugt. A brazing method is provided in which an amorphous or partially amorphous brazing foil having a composition having a metalloid content of 10 to 30 atom% is placed at a joint of two or more parts. The brazing foil has the shape of a wound annular band having a shorted current path between at least two superimposed layers. The brazing foil is inductively heated melted and produces a brazed joint of the parts.

Solder foil for high-temperature soldering and method of repairing or manufacturing components using this solder film.

Die Erfindung betrifft eine beschichtete Lötfolie (1) auf Ni-Basis, Co-Basis oder Ni-Co-Basis zum Hochtemperaturlöten sowie ein Verfahren zum Verbinden mindestens zweier Bauteilelemente aus einkristallinen oder gerichtet erstarrten Superlegierungen zwecks Herstellung bzw. Reparatur von Bauteilen, insbesondere Gasturbinenschaufeln, unter Verwendung der erfindungsgemässen Lötfolie. Die amorphe mittels Schmelzspinn-Verfahren hergestellte Lötfolie (1) weist eine Oberseite und eine Unterseite auf und ist dadurch gekennzeichnet, dass die Oberseite und die Unterseite mit einem Film aus metallischem Lotpulver (2) auf Ni-Basis, Co-Basis oder Ni-Co-Basis mit einer Partikelgrösse im Nanometerbereich dünn beschichtet sind, wobei sowohl die Lötfolie (1) als auch das Lotpulver (2) zusätzlich korngrenzenstabilisierende Elemente als Legierungselemente aufweisen. Ausserdem können schmelzpunkterniedrigende Elemente in kommerziell üblicher Menge bzw. mit deutlich erhöhtem Anteil in der Lötfolie bzw. im Nano-Lotpulver (2) enthalten sein. Mit der erfindungsgemässen beschichteten Lötfolie (1) werden vorteilhaft sowohl die Schmelztemperatur des Lotmaterials als auch die Rekristallisationswahrscheinlichkeit beim Löten im angrenzenden Grundmaterial gesenkt. The invention relates to a coated solder foil (1) based on Ni, Co-based or Ni-Co for high-temperature soldering and a method for joining at least two component elements of monocrystalline or directionally solidified superalloys for the purpose of producing or repairing components, in particular gas turbine blades, using the solder foil according to the invention. The amorphous melt-spun solder sheet (1) has a top and a bottom, and is characterized in that the top and bottom are covered with a Ni-based, Co-based or Ni-Co metallic solder powder (2) film Base are coated with a particle size in the nanometer range thin, both the solder foil (1) and the solder powder (2) additionally have grain boundary stabilizing elements as alloying ...

Magnetic nickel base ternary brazing material and method of application

A ternary magnetic braze alloy and method for applying the braze alloy in areas having limited access. The magnetic braze alloy is a nickel-based braze alloy from the perminvar region of the Ni, Fe, Co phase diagram. The braze alloy includes, by weight percent 8-45% Fe, 0-78% Co, 2.0-4.0% of an element selected from the group consisting of B and Si and combinations thereof, and the balance Ni. The nickel-based braze alloy is characterized by a brazing temperature in the range of 1850-2100° F. The nickel-based braze alloy is magnetic below its Curie temperature.

Iron-based solder for connecting TiAl alloy and Ni-based high-temperature alloy

本发明公开了一种用于连接TiAl合金和Ni基高温合金的铁基钎料。该钎料配方包括如下组分：35wt%‑40wt%Fe、35wt%‑40wt%Co、15wt%‑20wt%Ni、3‑5wt%Si、3‑5wt%B和0.1‑0.5wt%Y；采用熔炼和甩带的方法，制备出厚度约50μm，宽度约为10mm的非晶条带。利用所述成分获得的条带在较宽的过冷液相区范围内具有超塑性变形能力，能够使得中间层与母材的接触面积大大提高；利用本发明提供的钎料，所获得的焊接接头强度可以超过300Mpa。

Article having turbulation and method of providing turbulation on an article

An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.

Method of brazing and using a brazing foil for induction brazing

Ein Verfahren zum Hartlöten wird bereitgestellt, bei dem eine amorphe oder teilamorphe Hartlotfolie mit einer Zusammensetzung, die einen Metalloidgehalt von 10 bis 30 Atom-% aufweist, an einer Verbindungsstelle zweier oder mehrerer Teile angeordnet wird. Die Hartlotfolie weist die Gestalt eines gewickelten Ringbands auf, das einen kurzgeschlossenen Strompfad zwischen mindestens zwei aufeinanderliegenden Lagen aufweist. Die Hartlotfolie wird induktiv erwärmt geschmolzen und eine hartgelötete Verbindung der Teile erzeugt.

Amorphous alloy and solder made from amorphous alloy

Hybrid article, method for forming hybrid article and method for welding

A hybrid article (100) is disclosed including a sintered coating (104) disposed on and circumscribing the lateral surface (106) of a core (102) having a core material (108) and a greater density than the sintered coating (104). The sintered coating (104) includes more than 95% up to 99.5% of a first metallic particulate material (110) including a first melting point, and from 0.5% up to 5% of a second metallic particulate material (112) having a second melting point lower than the first melting point. A method for forming the hybrid article (100) is disclosed including disposing the core (102) in a die (200), introducing a slurry (204) having the metallic particulate materials (110 and 112) into a gap (202) between the lateral surface (106) and the die (200), and sintering the slurry (204). A method for welding a workpiece (600) is disclosed including the hybrid article (100) serving as a weld filler.

Process of filling openings in a component

A process for filling openings, including blind holes, through-holes, and cavities, in high temperature components. The process entails forming a powder mixture by mixing particles of at least a base alloy and a second alloy that contains a sufficient amount of a melting point depressant to have a lower melting temperature than the base alloy. The powder mixture is combined with a binder and compacted to form a compacted preform, which is then heated to remove the binder and form a rigid sintered preform. The sintered preform is produced, or optionally is further shaped, to have a cross-sectional shape and dimensions to achieve a clearance of up to 200 micrometers with the opening, after which the preform is placed in the opening and diffusion bonded within the opening to form a brazement comprising the particles of the base alloy dispersed in a matrix formed by the second alloy.

Hybrid article, method for forming hybrid article and method for welding

A hybrid article is disclosed including a sintered coating disposed on and circumscribing the lateral surface of a core having a core material and a greater density than the sintered coating. The sintered coating includes more than about 95% up to about 99.5% of a first metallic particulate material including a first melting point, and from about 0.5% up to about 5% of a second metallic particulate material having a second melting point lower than the first melting point. A method for forming the hybrid article is disclosed including disposing the core in a die, introducing a slurry having the metallic particulate materials into a gap between the lateral surface and the die, and sintering the slurry. A method for welding a workpiece is disclosed including the hybrid article serving as a weld filler.

Method of cladding and fusion welding of superalloys

FIELD: metallurgy. SUBSTANCE: invention relates to welding by fusion of superalloys and can be used for manufacturing and repairing gas turbine engine elements. Base material made of superalloy is coated with a composite filler powder, containing 5–50 wt% brazing powder, which includes melting point depressants, and 50–95 wt% high temperature welding powder. Method includes simultaneous heating base material and composite filler powder to a temperature that will fully melt brazing powder and and at least partially melt high temperature welding powder, and also melt a surface layer to form a weld pool. Weld pool is cooled at rate providing, during crystallisation and cooling, formation of a composite structure, comprising interconnected grid of dendrites with high melting point, obtained from high-temperature welding powder, and formation from high-melting point solder powder, high-temperature welding powder and base material in weld bead of dendritic eutectic matrix. Splicing of weld bead and base material is obtained. Method includes performing post-welding thermal treatment at temperature above temperature of solidus of brazing powder and below temperature of solidus of high-temperature welding powder. EFFECT: technical result is enabling self-healing of cracks during welding and post-welding heat treatment. 10 cl, 8 dwg, 3 tbl, 9 ex РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 610 198 C2 (51) МПК B23K 26/34 (2014.01) B23K 26/342 (2014.01) B23K 35/24 (2006.01) B23K 35/32 (2006.01) B23P 6/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ 2014141779, 05.12.2012 (24) Дата начала отсчета срока действия патента: 05.12.2012 Дата регистрации: (73) Патентообладатель(и): ЛИБУРДИ ИНЖИНИРИНГ ЛИМИТЕД (CA) Приоритет(ы): (22) Дата подачи заявки: 05.12.2012 (43) Дата публикации заявки: 27.09.2016 Бюл. № 27 2012065581 A2, 24.05.2012. US 20060249231 A1, 09.11.2006. RU 2281845 C1, 20.08.2006. RU ...

Amorphous or partially amorphous metal alloy

Amorphous or partially amorphous cobalt/iron/zirconium alloys are described which can be used in the form of brazing foils for brazing different materials such as ceramics, metal or graphite.

PROCESS FOR PRODUCING A TURBOMACHINE PIECE

Le procédé d'élaboration comporte les étapes de réalisation d'une préforme par fusion sélective, la préforme comportant une surface d'assemblage destinée à être brasée à la pièce à réparer et contenant un matériau de brasage, puis à assembler la préforme à la pièce de la turbomachine par brasage-diffusion. L'amplitude thermique du pic principal (A1) de transformation du matériau de brasage utilisé pour réaliser la préforme sera au moins le double de chacune des amplitudes thermiques respectives des pics secondaires (A2,A3) de transformation de ce matériau de brasage. The production process comprises the steps of producing a preform by selective melting, the preform comprising an assembly surface intended to be brazed to the part to be repaired and containing a brazing material, and then to assemble the preform to the part. of the turbomachine by soldering-diffusion. The thermal amplitude of the main transformation peak (A1) of the brazing material used to produce the preform will be at least twice each of the respective thermal amplitudes of the secondary peaks (A2, A3) of transformation of this brazing material.

Process for manufacturing or repairing turbine engine or compressor components

A process of the kind used for producing or repairing a turbine or compressor or fan blade by laser consolidation wherein a laser beam is moved relative to a metal surface and a stream of metal is supplied to the surface via a supply tube, so that said laser beam melts a thin layer of the metal substrate and also melts the metal being delivered to the substrate and thus forms a band of fused metal on said surface, the process being repeated until a desired blade is built up or repaired. The invention is characterized in that the laser beam is orientated at an acute angle to the surface. The supply tube may deliver the metal substantially along a path normal to the surface, with the laser beam being one of a plurality of laser beams each orientated at an acute angle to the surface and spaced around the supply means. Alternatively, a single laser beam may be used at a first acute angle to the surface, with the supply tube being at a second acute to the surface, the laser beam and supply tube being at opposite sides to the normal to the surface.

HIGH-TEMPERATURE SOLDER PREPARATIONS

А 2016124542 ко РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) (11) аа ааа в а (13) нь << 5“ | Кам < А КО Оо Ча Зее (50) МПК В22Е 1/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2016124542, 20.11.2014 (71) Заявитель(и): ХЕГАНЕС АБ (ПАБЛ) (5Е) Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): 22.11.2013 ЕР 13194086.8 КНУТССОН Пер ($Е), САБО Кристоф (ОЕ) (43) Дата публикации заявки: 27.12.2017 Бюл. №36 (85) Дата начала рассмотрения заявки РСТ на национальной фазе: 22.06.2016 (86) Заявка РСТ: ЕР 2014/075146 (20.11.2014) (87) Публикация заявки РСТ: УГО 2015/075122 (28.05.2015) Адрес для переписки: 129090, Москва, ул. Б.Спасская, 25, строение 3, ООО "Юридическая фирма Городисский и Партнеры" (54) ЗАГОТОВКИ ДЛЯ ВЫСОКОТЕМПЕРАТУРНОЙ ПАЙКИ (57) Формула изобретения 1. Способ получения заготовки припоя, включающий стадии: обеспечение порошка припоя на основе железа, железа-хрома, никеля или кобальта с размером частиц менее 355 мкм, смешивание этого порошка с 0,1-5%, предпочтительно 0,5-3%, наиболее предпочтительно 0,5-2% по массе водорастворимого связующего, выбранного из группы поливинилового спирта, полиэтиленгликоля с молекулярной массой между 1500 и 35000, карбоксиметилцеллюлозы, метилцеллюлозы, этилцеллюлозы, акрилатов или желатина, и, необязательно, добавление и примешивание водонерастворимого связующего, выбранного из группы полиамидов, олигомеров амида и полиэтиленов, причем суммарное количество связующих составляет 0,1-5%, предпочтительно 0,5-3%, подвергание смешанного порошка процессу агломерации с получением агломерированного порошка с размером агломерированных частиц менее | мм, необязательное добавление водонерастворимого связующего, выбранного из группы полиамидов, олигомеров амида и полиэтиленов, причем суммарное количество связующих составляет 0,1-5%, предпочтительно 0,5-3%, уплотнение полученного агломерированного порошка под давлением по меньшей мере 300 МПа в процессе одноосного прессования до плотности по ...

A kind of manufacture method of spherical self-melting alloy solder

一种球形自熔性合金钎料的制造方法，包括如下步骤：准备自熔性合金粉末；准备自熔性合金粉末与碳材料粉末或与陶瓷材料粉末的均匀混合粉末；高温热处理使自熔性合金熔融并凝固成金属球；高温热处理的温度是达到所述合金熔融的温度，优选是自熔性合金熔点温度以上40到100℃的范围内；分离碳材料粉末或陶瓷材料粉末获得微米、纳米球形自熔性合金粉末。方法简单，可规模化生产，无需特殊精密喷射设备，成本较低，而且制造的球形合金粉表面光洁，流动性好，有利于热喷涂送粉和堆焊填料。

Diffusion bonding of gaps

A process for diffusion bonding of cracks and other gaps in high-temperature nickel and cobalt alloy components is described. The gap is filled with alloy powder matching the substrate alloy, or with an alloy of superior properties, such as MAR-M 247, MAR-M 247LC, or CM 247LC. A braze containing a melting point depressant is either mixed into the alloy powder or applied over it. The depressant is preferably hafnium, zirconium, or low boron. The component is heated for 15-45 minutes above the melting point of the braze, which fills the spaces between the alloy powder particles. The component is diffused at a temperature above or below the liquidus of the braze and solution heat-treated and aged at a temperature at which the braze and alloy mixture in the gap is solid, but the depressant diffuses away.

Repair of HPT schrouds with sintered preforms

Method of producing rib on vane free end, vane produced by said method and gas turbine engine equipped with said vane

FIELD: process engineering. SUBSTANCE: invention aims at fabricating gas turbine engine vanes with, at least, one rib on free end by consecutive application of metal layers on vane foot to form extending part of rib 2282. For this, laser source is activated connected with optical head 34 and focused to the point of rib foot top surface, as well as source 34, 35 of first and second powder materials connected with spraying nozzle 38. Powder is fed into melt bath to produce localised bulge. Thereafter, optical head 34 and nozzle 38 are displaced to another point adjoining said bulge to repeat said jobs to complete layer formation on foot 82. Note here that head 32 is displaced longitudinally between edges 120, 220 and 122, 222 relative to produced bulge to form two annular seams 83a on rib foot surface. Gap between annular seams 83a are filled with first powder material. EFFECT: simplified process, higher quality of product. 18 cl, 13 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 415 003 (13) C2 (51) МПК B23P 15/00 (2006.01) B24C 1/10 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2006140331/02, 15.11.2006 (24) Дата начала отсчета срока действия патента: 15.11.2006 (72) Автор(ы): МОН Клод (FR), ВИНЬО Жоэль (FR) R U (73) Патентообладатель(и): СНЕКМА (FR) Приоритет(ы): (30) Конвенционный приоритет: 15.11.2005 FR 05 11578 (43) Дата публикации заявки: 20.05.2008 Бюл. № 14 2 4 1 5 0 0 3 (45) Опубликовано: 27.03.2011 Бюл. № 9 2 4 1 5 0 0 3 R U Адрес для переписки: 129090, Москва, ул.Б.Спасская, 25, стр.3, ООО "Юридическая фирма Городисский и Партнеры", пат.пов. Е.И.Емельянову, рег.№ 174 C 2 C 2 (56) Список документов, цитированных в отчете о поиске: WO 02097241 А1, 05.12.2002. RU 2003134537 А, 10.05.2005. FR 2858650 А1, 11.02.2005. RU 2100479 С1, 27.12.1997. RU 2228243 С2, 10.05.2004. RU 2058871 С1, 10.05.2004. (54) СПОСОБ ИЗГОТОВЛЕНИЯ РЕБРА НА СВОБОДНОМ КОНЦЕ ЛОПАТКИ, ЛОПАТКА, ...