Abstract: A method for casting comprising: providing a seed, the seed characterized by: an arcuate form and a crystalline orientation progressively varying along an arc of the form; providing molten material; and cooling and solidifying the molten material so that a crystalline structure of the seed propagates into the solidifying material.

Abstract: A coating-substrate combination includes: a Ni-based superalloy substrate comprising, by weight percent: 2.0-5.1 Cr; 0.9-3.3 Mo; 3.9-9.8 W; 2.2-6.8 Ta; 5.4-6.5 Al; 1.8-12.8 Co; 2.8-5.8 Re; 2.8-7.2 Ru; and a coating comprising, exclusive of Pt group elements, by weight percent: Ni as a largest content; 5.8-9.3 Al; 4.4-25 Cr; 3.0-13.5 Co; up to 6.0 Ta, if any; up to 6.2 W, if any; up to 2.4 Mo, if any; 0.3-0.6 Hf; 0.1-0.4 Si; up to 0.6 Y, if any; up to 0.4 Zr, if any; up to 1.0 Re, if any.

Abstract: A method for casting comprising: providing a seed, the seed characterized by: an arcuate form and a crystalline orientation progressively varying along an arc of the form; providing molten material; and cooling and solidifying the molten material so that a crystalline structure of the seed propagates into the solidifying material.

Abstract: 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.

Abstract: A blade has an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The blade has a compositional variation along the airfoil.

Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

Abstract: A casting mold (260) comprises a shell (262) extending from a lower end (264) to an upper end (266) and having: an interior space (280) for casting metal; and an opening (268) for receiving metal to be cast. A plurality of thermocouples (900) are vertically-spaced from each other on the shell.

Abstract: A casting mold (260) comprises a shell (262) extending from a lower end (264) to an upper end (266) and having: an interior space (280) for casting metal; and an opening (268) for receiving metal to be cast. A plurality of thermocouples (900) are vertically-spaced from each other on the shell.

Abstract: A method is provided for casting an article such as a blade having an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The method comprises introducing a molten alloy into a mold; and varying a composition of the introduced alloy during the introduction so as to produce a compositional variation.

Abstract: A process for rejuvenating a turbine disk having a plurality of slots includes the steps of determining a depth of a damaged layer containing M23C6 carbide dissolution; and removing the damaged layer from the slots in accordance with the determined depth.

Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

Abstract: A method is provided for casting an article such as a blade having an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The method includes introducing a molten alloy into a mold. A composition of the introduced alloy is varied during the introduction so as to produce a compositional variation.

Abstract: A formable nickel based superalloy composition including a two phase ?/?? precipitation hardenable nickel base superalloy with a sum of primarily ?? forming elements in atom % is in the range of about 10-16, forming about a 40-64 volume % of the ?? precipitate, cast in form of a single crystal.

Abstract: A method for casting an article comprises a first region and a second region. The method comprises casting an alloy in a shell, the shell having a casting core protruding from a first metal piece; and deshelling and decoring to remove the shell and core and leave the first region formed by the first piece and the second region formed by the casted alloy.

Abstract: An embodiment of a turbine assembly includes, among other possible things, a first component including a first component surface, a second component including a second component surface spaced apart from the first component surface, and a brush seal disposed between the first component and the second component. The brush seal includes, among other things, a first bristled region extending in a first direction from a backing plate, and sealingly engaging one of the first component surface and the second component surface. At least one of the backing plate and the first bristled region includes a nickel-based superalloy material having at least 40% of a Ni3(Al,X) precipitate phase, X being a metallic or refractory element other than Al.

Abstract: An alloy part is cast in a mold (280) having a part-forming cavity (292, 294, 296). The method comprises pouring a first alloy into the mold. The pouring causes: a surface (550) of the first alloy in the part-forming cavity to raise relative to the part-forming cavity; a branch flow of the poured first alloy to pass upwardly through a first portion (304) of a passageway; and the branch flow to pass downwardly through a second portion (310), of the passageway; solidifying some of the first alloy in the passageway to block the passageway while at least some of the first alloy in the part-forming cavity remains molten. A second alloy is poured into the mold atop the first alloy and solidified.

Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

Abstract: An alloy part is cast in a mold (280) having a part forming cavity (292, 294, 296). The method comprises pouring a first alloy into the mold. The pouring causes: a surface (550) of the first alloy in the part forming cavity to raise relative to the part forming cavity; a branch flow of the poured first alloy to pass upwardly through a first portion (304) of a passageway; and the branch flow to pass downwardly through a second portion (310), of the passageway; solidifying some of the first alloy in the passageway to block the passageway while at least some of the first alloy in the part forming cavity remains molten. A second alloy is poured into the mold atop the first alloy and solidified.

Abstract: A process includes solution heat treating a nickel based superalloy with greater than about 40% by volume of gamma prime precipitate to dissolve the gamma prime precipitate in the nickel based superalloy; cooling the nickel based superalloy to about 85% of a solution temperature measured on an absolute scale to coarsen the gamma prime precipitate such that a precipitate structure is greater than about 0.7 micron size; and wrought processing the nickel based superalloy at a temperature below a recrystallization temperature of the nickel based superalloy. A material includes a nickel based superalloy with greater than about 40% by volume of gamma prime precipitate in which the precipitate structure is greater than about 0.7 micron size.

Abstract: 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.