An aluminized metallic scaffold for high temperature applications comprises a porous non-refractory alloy structure including a network of interconnected pores extending therethrough. The porous non-refractory alloy structure comprises a transition metal phase and an aluminide phase, and portions of the porous non-refractory alloy structure between interconnected pores have a thickness no greater than about 500 nm. A method of making an aluminized metallic scaffold for high-temperature applications comprises introducing aluminum into a surface of a porous metallic structure at an elevated temperature. The porous metallic structure comprises a transition metal and has a network of interconnected pores extending therethrough, where portions of the porous metallic structure between interconnected pores have a thickness no greater than about 500 nm. As the aluminum is introduced into the surface and diffusion occurs, an aluminide phase is formed, resulting in a porous non-refractory alloy structure comprising the aluminide phase and a transition metal phase.

The present invention provides a Ni-based alloy, a heat-resistant and corrosion-resistant component, and a heat treatment furnace component, all of which have excellent corrosion resistance and mechanical strength at high temperatures. The Ni-based alloy of the present invention consists of, by mass %, Al: more than 5.0% and up to 26.0%, and Zr: more than 0% and up to 5.0%, the balance being Ni and unavoidable impurities. The Ni-based alloy preferably contains more than 0% and up to 5.0% of B, by mass %, in a combined amount with Zr. Moreover, it is preferable that the Ni-based alloy has P value and Q value and satisfies a relationship of Q value ≥ 0.89 × P value - 0.53, when the P value is obtained from a formula -18.95 + 0.1956 × Ni% + 0.1977 × Al% + 0.2886 × Zr% + 12.4 × B%, and the Q value is obtained by dividing an area percentage of Ni.sub.3Al precipitated on the surface of the alloy by 100.

A nickel alloy sputtering target comprises: a nickel alloy containing an element capable of decreasing the Curie temperature of nickel, wherein an area ratio of a Ni phase having a Ni content of 99.0 mass % or more is 13% or less and an average crystal grain diameter is 100 gm or less. It is preferred that an area ratio of a high-purity Ni phase having a Ni content of 99.5 mass % or more be 5% or less.

Ni—Mn—Si based braze filler alloys or metals which may be nickel-rich, manganese-rich, or silicon-rich braze filler alloys, have unexpectedly narrow melting temperature ranges, low solidus and low liquidus temperatures, as determined by Differential Scanning calorimetry (DSC), while exhibiting good wetting, and spreading, without deleterious significant boride formation into the base metal, and can be brazed at lower temperatures. The nickel rich alloys contain 58 wt % to 70 wt % nickel, the manganese-rich alloys contain 55 wt % to 62 wt % manganese, and the silicon-rich alloys contain 25 wt % to 29 wt % silicon. Copper with or without boron to partly replace nickel may be employed without any substantial increase of the melting point, or to reduce the melting point. The braze filler alloys have sufficient brazability to withstand high temperature conditions for thin-walled aeronautical and other heat exchangers.

A method for manufacturing a metal alloy component. The method comprises heating a shaped metal component and an alloying element source of vapor-phase transportable alloying element species in a reactor in the presence of a vapor-phase transport agent, wherein the heating is conducted under conditions which cause the vapor-phase transportable alloying element species to diffuse into the shaped metal component; and forming a metal alloy component alloyed with element species from the alloying element source.

A nickel base superalloy powder for additive manufacturing applications is disclosed. The alloy powder has the following broad weight percent composition:

TABLE-US-00001 C   0-0.1 Mn 0.5 max. Si   0-0.03 Cr  4-16 Fe   0-1.5 Mo 0-6 W 0-8 Co  0-15 Ti 0-2 Al 0.5-5.5 Nb 0-6 Ta  7.5-14.5 Hf   0-2.0 Zr   0-0.1 Re 0-6 Ru 0-3 B   0-0.03
The balance of the alloy is at least 50% nickel and the usual impurities. An article of manufacture made from the alloy is also disclosed.

A nickel-titanium alloy with an average grain size of between 0.2 and 10 microns and a recoverable strain of greater than 9% is disclosed herein, in which the alloy is formed using a method which involves applying a shape set heat treatment to the nickel-titanium alloy. The heat treatment includes applying heat at a temperature between 225° C. and 350° C. for a period of time between 20 and 240 minutes.

The present invention relates to conductive multicomponent multiphase metal alloy. The metal alloy has the following (in atom-%):Ni, in a total amount of 35-70; wherein the remaining 30-65 comprises at least three elements selected from the list consisting of Sn, Nb, Ta, B, Cr, Ce, Fe, La, Nd, Sm, Gd, Ti, Zr, Mn, Hf, Si, P, Al, Y and V in a total amount of at least 30. The metal alloy comprises at least three distinct crystalline phases, at least one phase being an intermetallic phase. The present invention also relates to an electrode material comprising said alloy, to a method for forming a coating on said alloy, and to a method for manufacturing said alloy.

An additive manufacturing method of producing a metal alloy article may involve: Providing a supply of a metal alloy in powder form; providing a supply of a nucleant material, the nucleant material lowering the nucleation energy required to crystallize the metal alloy; blending the supply of metal alloy powder and nucleant material to form a blended mixture; forming the blended mixture into a first layer; subjecting at least a portion of the first layer to energy sufficient to raise the temperature of the first layer to at least the liquidus temperature of the metal alloy; allowing at least a portion of the first layer to cool to a temperature sufficient to allow the metal alloy to recrystallize; forming a second layer of the blended mixture on the first layer; and repeating the subjecting and allowing steps on the second layer to form an additional portion of the metal alloy article.

An electrical connector for connecting electrical conductors in an aircraft includes a pin having a first contact surface and a socket to receive the pin. The socket has a second contact surface contacting a first contact surface of the pin when the pin is in the socket. A securing part is positioned to apply a contact or clamping force pressing the contact surfaces against each other. The securing part includes a shape memory alloy to exist in a martensite an austenite phase depending on temperature of the securing part, wherein the securing part assumes a first pre-set shape when the temperature is below a first temperature threshold, and a second pre-set shape when the temperature is above a second temperature threshold higher than the first temperature threshold, wherein the contact or clamping force applied by the securing part in the second pre-set shape is greater than in the first pre-set shape.