Abstract: A nickel-cobalt based superalloy composition consisting of by weight (wt.): 33.5 to 54 percent Ni; 19.5 to 36 percent Co; 9 to 12 percent Cr; 3.9 to 5.5 percent Al; 4.5 to 9.5 percent W; up to 5.5 percent Fe; 2 to 3.5 percent Mo; 0.6 to 5 percent Ta; 0.15 to 2.2 percent Ti; up to 1.75 percent Nb; up to 0.1 percent Hf; 0.005 to 0.03 percent C; 0.001 to 0.02 percent B; 0.005 to 0.06 percent Zr; up to 0.3 percent Si; up to 0.6 percent Mn; and the balance being impurities.

Abstract: A nickel-base superalloy includes essentially, by weight: 14.75 to 26.5 percent cobalt, 4.1 to 4.65 percent aluminium, 1.1 to 1.9 percent titanium, 3.85 to 6.3 percent tantalum, 1.2 to 2.55 percent niobium, up to 0.07 percent boron, up to 0.06 percent carbon, up to 14.0 percent chromium, up to 1.0 percent iron, up to 1.0 percent manganese, up to 4.2 percent molybdenum, up to 0.5 percent silicon, up to 4.9 percent tungsten, and up to 0.1 percent zirconium, the balance being nickel and incidental impurities; wherein the overall concentration in the alloy of aluminium, titanium, tantalum, and niobium is from 13 to 14 atomic percent and the atomic ratio of aluminium to titanium is from 4.625:1 to 6.333:1.

Abstract: The novel nickel-base superalloy useful in an additive manufacturing process or a powder-based manufacturing process includes the following composition in wt %: Cr 8.0-8.5; Co 9.0-9.5; Mo 0.4-0.6; W 9.3-9.7; Ta 2.9-3.6; Al 4.9-5.6; Ti 0.2-1.0; Hf 0-0.05; C 0.005-0.03; B 0.005-0.02; Zr 0.005-0.1; Nb 0.2-1; Mn 0-0.6; and S 0-0.002 (?20 ppm); the balance nickel and incidental elements and unavoidable impurities.

Abstract: A nickel-base superalloy consisting of, by weight: 14.6% to 15.9% cobalt; 11.5% to 13.0% chromium; 0.8% to 1.2% iron; 0.2% to 0.60% manganese; 2.00% to 2.40% molybdenum; 3.30% to 3.70% tungsten; 2.90% to 3.30% aluminum; 2.60% to 3.10% titanium; 3.50% to 5.10% tantalum; 1.20% to 1.80% niobium; 0.10% to 0.60% silicon; 0.02% to 0.06% carbon; 0.010% to 0.030% boron; 0.05% to 0.11% zirconium; up to 0.045% hafnium; and the balance being nickel and impurities.

Abstract: A nickel-base alloy of, in atomic percent unless otherwise stated, up to 8 percent Fe, up to 16 percent Co, between 15 and 25 percent Cr, up to 3 percent Mo, up to 2 percent W, between 3 and 5 percent Al, between 3 and 7.5 percent Nb, up to 3 percent Ta, up to 0.2 percent Ti, up to 0.5 percent C, up to 0.175 percent B, up to 0.07 percent Zr, up to 1 percent Mn, up to 1 percent Si, up to 0.2 percent Hf, the balance of Ni and incidental impurities, wherein the atomic ratio of Al to Nb is between 0.4 and 1.7, the atomic ratio of the sum of Al and Ti to Nb is between 0.4 and 1.8, and, the composition including at least 10 percent of elements from the group of Al, Nb, and Ti.

Abstract: A nickel-base superalloy that includes 6.55% to 7.15% aluminum, 3.3% to 3.7% titanium, 1.2% to 1.7% tantalum, and 0.8% to 1.0% niobium, such that a combined atomic percentage of the aluminum, the titanium, the tantalum and the niobium is between 12.65% and 13.15% to provide substantially 51% to 53% by volume of gamma prime precipitates.

Abstract: A nickel-base alloy having the following composition (in atomic percent unless otherwise stated): between 12 and 15% of elements from the group consisting of Al, Ti, Ta and Nb, between 12.5% and 17.5% Cr, between 22 and 29% Co, between 0 and 1.5% W, between 0 and 3% Mo, between 0.1 and 0.3% C, between 0.05 and 0.2% B, between 0.02 and 0.07% Zr and, optionally, up to 2% Fe, up to 1% Mn, up to 1% Si, and up to 0.05 Mg; the balance being Ni and incidental impurities. The alloy has an improved combination of properties (principally improved resistance to high temperature deformation and surface environmental damage) compared with known alloys, and is intended to operate for prolonged periods of time above 700° C., and up to peak temperatures of 800° C.

Abstract: The present invention relates to a method of manufacturing a multiple composition component 10, comprising: arranging first, second and third constituent parts 40, 30, 42 having first, second and third compositions respectively A, B, C so that the first constituent part 40 shares a first boundary with the second constituent part 30 and the second constituent part 30 shares a second boundary with the third constituent part 40. The first, second and third constituent parts 40, 30, 42 are each either a powder or a solid so that the first and second boundaries are each a solid adjacent to a powder. The arrangement is then processed so as to form a single solid component having first, second and third regions 16, 18, 20 having first, second and third compositions A, B, C respectively.

Abstract: An alloy disc includes a hub portion, a rim portion and a web portion disposed between the hub portion and the rim portion. The disc includes a fine grain structure substantially in a first region of the disc and a coarse grain structure substantially in a second region of the disc. The fine grain structure may be in the hub portion of the disc, and the coarse grain structure may be in the rim portion of the disc. The coarse grain structure may extend a greater distance radially inwardly from the rim portion into the web portion on the first axial end of the disc than on the second axial end of the disc. The fine grain structure may extend a greater distance radially outwardly from the hub portion into the web portion on the second axial end of the disc than on the first axial end of the disc.

Abstract: A method of heat treating a superalloy component includes solution heat treating the component at a temperature below the gamma prime solvus temperature to produce a fine grain structure. Insulation is placed over a first area to form an insulated assembly that is placed in a furnace at a temperature below the solvus temperature and maintained at that temperature for a predetermined time to achieve a uniform temperature. The temperature is increased at a predetermined rate to a temperature above the solvus temperature to maintain a fine grain structure in a first region, produce a coarse grain structure in a second region and produce a transitional structure in a third region between the first and second regions. The insulated assembly is removed from the furnace when the second region has been above the solvus temperature for a predetermined time and/or the first region has reached a predetermined temperature.

Abstract: A nickel base superalloy consisting of 20 to 40 wt % cobalt, 10 to 15 wt % chromium, 3 to 6 wt % molybdenum, 0 to 5 wt % tungsten, 2.5 to 4 wt % aluminium, 3.4 to 5 wt % titanium, 1.35 to 2.5 wt % tantalum, 0 to 2 wt % niobium, 0.5 to 1 wt % hafnium, 0 to 0.1 wt % zirconium, 0.01 to 0.05 wt % carbon, 0.01 to 0.05 wt % boron, 0 to 2 wt % silicon and the balance nickel plus incidental impurities. The gamma prime phase comprises (Ni/Co)3 (Al/Ti/Ta).

Abstract: A method of heat treating a superalloy component comprises solution heat treating the component at a temperature below the gamma prime solvus temperature to produce a fine grain structure in the component. Insulation is placed over a first area of the component to form an insulated assembly. The insulated assembly is placed in a furnace at a temperature below the solvus temperature and maintained at that temperature for a predetermined time to achieve a uniform temperature in the component. The temperature is increased at a predetermined rate to a temperature above the solvus temperature to maintain a fine grain structure in a first region, to produce a coarse grain structure in a second region and to produce a transitional structure in a third region between the first and second regions of the component.