Abstract: Low rhenium nickel base superalloy compositions and articles formed from the superalloy composition are provided. The nickel base superalloy composition includes in percentages by weight: about 5-8 Cr; about 6.5-9 Co; about 1.3-2.5 Mo; about 4.8-6.8 W; about 6.0-7.0 Ta; if present, up to about 0.5 Ti; about 6.0-6.4 Al; about 1-2.3 Re; if present, up to about 0.6 Hf; if present, up to 1.5 C; if present, up to about 0.015 B; the balance being nickel and incidental impurities. Exemplary compositions are characterized by an Re ratio defined as the weight % of Re relative to the total of the weight % of W and the wt % of Mo, of less than about 0.3. Exemplary articles include airfoils for gas turbine engine blades or vanes, nozzles, shrouds, and splash plates.

Abstract: A nickel base superalloy composition substantially free of rhenium includes, in percentages by weight: about 5-8 Cr; about 7-8 Co; about 1.3-2.2 Mo; about 4.75-6.75 W; about 6.0-7.0 Ta; if present, up to about 0.5 Ti; about 6.0-6.4 Al; about 0.15-0.6 Hf; if present, from about 0.03-0.06 C; if present, up to about 0.004 B; if present, one or more rare earths selected from Y, La, and Ce up to about 0.03 total, the balance including nickel and incidental impurities. The superalloy composition is able to provide sustained-peak low cycle fatigue and/or oxidation resistance properties comparable to second generation superalloy compositions including at least about 3 wt % rhenium. Superalloy articles incorporating the compositions include nozzles, shrouds, and splash plates for gas turbine engines.

Abstract: Low rhenium nickel base superalloy compositions and articles formed from the superalloy composition are provided. The nickel base superalloy composition includes in percentages by weight: about 5-8 Cr; about 6.5-9 Co; about 1.3-2.5 Mo; about 4.8-6.8 W; about 6.0-7.0 Ta; if present, up to about 0.5 Ti; about 6.0-6.4 Al; about 1-2.3 Re; if present, up to about 0.6 Hf; if present, up to about 0-1.5 C; if present, up to about 0.015 B; the balance being nickel and incidental impurities. Exemplary compositions are characterized by an Re ratio defined as the weight % of Re relative to the total of the weight % of W and the wt % of Mo, of less than about 0.3. Exemplary articles include airfoils for gas turbine engine blades or vanes, nozzles, shrouds, and splash plates.

Abstract: A nickel-base superalloy composition including (measured in % by weight) from about 6.8 to about 7.5% aluminum, from about 4 to about 8% tantalum, from about 4 to about 10% chromium, from about 2 to about 7% tungsten, from 0 to about 6% rhenium, from 0 to about 5% cobalt, from 0 to about 0.2% silicon, optionally, from about 0.15 to about 0.7% hafnium, from 0 to about 0.5% titanium, from 0 to about 4% molybdenum, from 0 to about 0.005% boron, from 0 to about 0.06% carbon, from 0 to about 0.03% of a rare earth addition selected from the group consisting of yttrium, lanthanum, cesium, and combinations thereof, balance nickel and incidental impurities. The nickel-base superalloy composition may be used in single-crystal or directionally solidified superalloy articles such as high pressure turbine blades for a gas turbine engine.

Abstract: A nickel-base superalloy composition including (measured in % by weight) from about 6.5 to about 7.5% aluminum, from about 4 to about 8% tantalum, from about 3 to about 10% chromium, from about 2 to about 7% tungsten, from 0 to about 4% molybdenum, from 0 to about 6% rhenium, from 0 to less than about 0.001% niobium, from 0 to about 5% cobalt, from 0 to about 0.2% silicon, from 0 to about 0.06% carbon, optionally, from 0 to about 0.5% titanium, from 0 to about 0.005% boron, from about 0.15 to about 0.7% hafnium, from 0 to about 0.03% of a rare earth addition selected from the group consisting of yttrium, lanthanum, cesium, and combinations thereof, balance nickel and incidental impurities. The nickel-base superalloy composition may be used in single-crystal or directionally solidified superalloy articles such as high pressure turbine blades for a gas turbine engine.

Abstract: A turbine engine combustor member, for example a deflector including an inner surface at a combustor interior and an outer surface away from such interior includes a body of a high temperature alloy having properties combining resistance to hot corrosion in March=1 flows and oxidation to avoid coating the outer surface. In one embodiment, the inner surface includes an environmental resistant coating comprising a ceramic-base thermal barrier coating. In some forms such coating includes an inner coating including Al under the ceramic-base coating. In another embodiment, the member includes air cooling passages and is substantially uncoated. Provision of such a member enables complete combustor assembly including a plurality of members and then coating all inner surfaces concurrently rather than individually before assembly.

Abstract: A composition of matter is about 1 to about 3 percent rhenium, from about 6 to about 9 percent aluminum, from 0 to about 0.5 percent titanium, from about 4 to about 6 percent tantalum, from about 12.5 to about 15 percent chromium, from about 3 to about 10 percent cobalt, from about 2 to about 5 percent tungsten, from 0 to about 0.2 percent hafnium, from 0 to about 1 percent silicon, from 0 to about 0.25 percent molybdenum, from 0 to about 0.25 percent niobium, balance nickel and minor elements. The composition is preferably made into a substantially single crystal article, such as a component of a gas turbine engine.

Abstract: A composition of matter is about 1 to about 3 percent rhenium, from about 6 to about 9 percent aluminum, from 0 to about 0.5 percent titanium, from about 4 to about 6 percent tantalum, from about 12.5 to about 15 percent chromium, from about 3 to about 10 percent cobalt, from about 2 to about 5 percent tungsten, from 0 to about 0.2 percent hafnium, from 0 to about 1 percent silicon, from 0 to about 0.25 percent molybdenum, from 0 to about 0.25 percent niobium, balance nickel and minor elements. The composition is preferably made into a substantially single crystal article, such as a component of a gas turbine engine.

Abstract: A superalloy article has a composition consisting essentially of, in weight percent, from about 4 to about 12 percent cobalt, from about 3.5 to about 7 percent tungsten, from about 2 to about 9 percent chromium, from about 0.5 to about 4.5 percent tantalum, from about 5.5 to about 7.5 percent aluminum, from 0 to about 5.5 percent rhenium, from about 0.1 to about 1.2 percent titanium, from 0 to about 3 percent molybdenum, from 0 to about 3 percent ruthenium, from about 0.5 to about 2 percent columbium, about 0.01 percent maximum boron, about 0.07 percent maximum carbon, from about 0.3 to about 1 percent hafnium, about 0.01 percent maximum zirconium, about 0.03 percent maximum yttrium, from 0 to about 0.5 percent vanadium, about 0.01 percent maximum cerium, and about 0.01 percent maximum lanthanum, balance nickel and impurity elements. The article is preferably substantially a single crystal or oriented polycrystal in a shape such as a gas turbine blade.

Abstract: A structure includes a cooled article having an open-cell solid foam of ceramic or metal cell walls with a porous interconnected intracellular volume therebetween. A source of a pressurized gas is in communication with a source region of the cooled article. The source of the pressurized gas includes a gas plenum in gaseous communication with the source region, and a compressor having a compressed gas output in gaseous communication with the gas plenum. Gas flows from the source of the pressurized gas through the porous intracellular volume, to cool the cooled article.