Abstract: A composition includes, by weight percent: Cobalt (Co) between about 4.5 and about 7.0; Chromium (Cr) between about 10.2 and about 11.5; Molybdenum (Mo) between about 0.5 and about 2.5; Tungsten (W) between about 4.0 and about 5.5; Rhenium (Re) between about 0 and about 1.2; Aluminum (Al) between about 6.2 and about 6.8; Tantalum (Ta) between about 4.5 and about 6.0; Titanium (Ti) between about 0 and about 0.5; Hafnium (Hf) between about 0 and about 0.5; Carbon (C) between about 0 and about 0.2; Boron (B) between about 0 and about 0.02; and the balance Nickel (Ni), and other incidental impurities.

Abstract: Compositions, and articles and methods for forming articles which include said compositions, are disclosed. The compositions include, by weight percent, about 13.7% to about 14.3% chromium (Cr), about 9.0% to about 9.9% cobalt (Co), about 4.0% to about 5.25% aluminum (Al), about 0.5% to about 3.0% titanium (Ti), about 4.5% to about 5.0% tungsten (W), about 1.4% to about 1.7% molybdenum (Mo), about 3.25% to about 3.75% niobium (Nb), about 0.08% to about 0.12% carbon (C), about 0.005% to about 0.04% zirconium (Zr), about 0.010% to about 0.014% boron (B), and balance nickel (Ni) and incidental impurities.

Abstract: A method for repairing a part and the resulting is disclosed. The method includes positioning a plug having an inner braze element coupled thereto into a cavity defined by an internal surface of a component. The cavity has a circular cross-section at the external surface of the component. The plug completely fills the circular cross-section and the inner braze element is within the cavity. A braze paste is positioned at least partially around the plug at the external surface. The component is positioned such that the inner braze element is above the plug. The component is subjected to a thermal cycle to melt the inner braze element around the plug, completely sealing the cavity by forming a metallurgical bond with the plug and the internal surface of the component. During the thermal cycle the braze paste is melted to form a metallurgical bond with the plug and external surface.

Abstract: A composition includes the constituents, in approximate weight percentages: Chromium 15-17; Silicon 2.5-3.5; Cobalt 6.0-8.0; Aluminum 1.0-2.0; Tantalum 1.5-2.5; Boron 1.5-2.5; Yttrium 0.015-0.025; Nickel balance; and incidental impurities.

Abstract: A composition includes, by weight percent: Cobalt (Co) between about 4.5 and about 7.0; Chromium (Cr) between about 10.2 and about 11.5; Molybdenum (Mo) between about 0.5 and about 2.5; Tungsten (W) between about 4.0 and about 5.5; Rhenium (Re) between about 0 and about 1.2; Aluminum (Al) between about 6.2 and about 6.8; Tantalum (Ta) between about 4.5 and about 6.0; Titanium (Ti) between about 0 and about 0.5; Hafnium (Hf) between about 0 and about 0.5; Carbon (C) between about 0 and about 0.2; Boron (B) between about 0 and about 0.02; and the balance Nickel (Ni), and other incidental impurities.

Abstract: A nickel-based superalloy composition including by weight percent: Cobalt 7.5; Chromium 9.75; Aluminum 5.45; Titanium 1.0; Niobium 3.5; Tungsten 6.0; Molybdenum 1.5; Carbon 0.08; Hafnium 0.15; Boron 0.01; and Nickel 65.0; and incidental impurities.

Abstract: A closure element for an internal passage in a component, and a related method and turbine blade or nozzle are disclosed. The closure element includes a spherical body made of a first superalloy, and a plurality of extensions extending from a surface of the spherical body. The plurality of extensions made of the same, similar or different material other than the first superalloy. Subjecting the component to at least one thermal cycle causes a braze material to form a metallurgical bond with the spherical body, the plurality of extensions and the passage wall to seal the internal passage.

Abstract: A composition includes the constituents, in approximate weight percentages: Chromium 15-17; Silicon 2.5-3.5; Cobalt 6.0-8.0; Aluminum 1.0-2.0; Tantalum 1.5-2.5; Boron 1.5-2.5; Yttrium 0.015-0.025; Nickel balance; and incidental impurities.

Abstract: Embodiments of the disclosure provide a system including: an enclosure having an interior sized to enclose and the workpiece and form a vacuum and pressurized atmosphere within the interior. A plurality of thermal applicators may be in thermal communication with first and second portions of the interior. First and second thermal applicators may independently heat and cool the first and second portions of the interior. The first thermal applicator may apply a first thermal treatment to a first portion of the workpiece in the first portion of the interior. A second thermal applicator may apply a second thermal treatment to a second portion of the workpiece in the second portion of the interior independently of the first thermal treatment.

Abstract: Embodiments of the disclosure provide a turbomachine component, including: a base portion configured for mounting on a rotor; an airfoil portion having a first end coupled to the base portion, and a second end opposite the first end. A creep resistance of the airfoil portion is greater than the base portion, and a fracture toughness of the airfoil portion is less than the base portion. A tip portion may be coupled to the second end of the airfoil portion. A creep resistance of the tip portion is less than the airfoil portion and greater than the base portion. A fracture toughness of the tip portion is less than the base portion and greater than the airfoil portion.

Abstract: In a non-limiting example, an article having a body including a nickel-based superalloy is provided. The nickel-based superalloy has a microstructure that includes a gamma phase matrix and a gamma prime phase including a plurality of rafting-resistant gamma prime particles dispersed in the gamma phase matrix. The plurality of the rafting-resistant gamma prime particles has an average particle perimeter of about 3 microns to about 15 microns, an average aspect ratio of about 1.2 to about 3, and where the microstructure of the nickel-based superalloy is substantially uniform throughout the body.

Abstract: A nickel-based superalloy composition including by weight percent: Cobalt 7.5; Chromium 9.75; Aluminum 5.45; Titanium 1.0; Niobium 3.5; Tungsten 6.0; Molybdenum 1.5; Carbon 0.08; Hafnium 0.15; Boron 0.01; and Nickel 65.0; and incidental impurities.

Abstract: A method for repairing a part and the resulting is disclosed. The method includes positioning a plug having an inner braze element coupled thereto into a cavity defined by an internal surface of a component. The cavity has a circular cross-section at the external surface of the component. The plug completely fills the circular cross-section and the inner braze element is within the cavity. A braze paste is positioned at least partially around the plug at the external surface. The component is positioned such that the inner braze element is above the plug. The component is subjected to a thermal cycle to melt the inner braze element around the plug, completely sealing the cavity by forming a metallurgical bond with the plug and the internal surface of the component. During the thermal cycle the braze paste is melted to form a metallurgical bond with the plug and external surface.

Abstract: In a non-limiting example, an article having a body including a nickel-based superalloy is provided. The nickel-based superalloy has a microstructure that includes a gamma phase matrix and a gamma prime phase including a plurality of rafting-resistant gamma prime particles dispersed in the gamma phase matrix. The plurality of the rafting-resistant gamma prime particles has an average particle perimeter of about 3 microns to about 15 microns, an average aspect ratio of about 1.2 to about 3, and where the microstructure of the nickel-based superalloy is substantially uniform throughout the body.

Abstract: Embodiments of the disclosure provide a turbomachine component, including: a base portion configured for mounting on a rotor; an airfoil portion having a first end coupled to the base portion, and a second end opposite the first end. A creep resistance of the airfoil portion is greater than the base portion, and a fracture toughness of the airfoil portion is less than the base portion. A tip portion may be coupled to the second end of the airfoil portion. A creep resistance of the tip portion is less than the airfoil portion and greater than the base portion. A fracture toughness of the tip portion is less than the base portion and greater than the airfoil portion.

Abstract: Embodiments of the disclosure provide a system including: an enclosure having an interior sized to enclose and the workpiece and form a vacuum and pressurized atmosphere within the interior. A plurality of thermal applicators may be in thermal communication with first and second portions of the interior. First and second thermal applicators may independently heat and cool the first and second portions of the interior. The first thermal applicator may apply a first thermal treatment to a first portion of the workpiece in the first portion of the interior. A second thermal applicator may apply a second thermal treatment to a second portion of the workpiece in the second portion of the interior independently of the first thermal treatment.

Abstract: A cast nickel-base superalloy that includes iron added substitutionally for nickel. The cast nickel-base superalloy comprises, in weight percent about 1-6% iron, about 7.5-19.1% cobalt, about 7-22.5% chromium, about 1.2-6.2% aluminum, optionally up to about 5% titanium, optionally up to about 6.5% tantalum, optionally up to about 1% Nb, about 2-6% W, optionally up to about 3% Re, optionally up to about 4% Mo, about 0.05-0.18% C, optionally up to about 0.15% Hf, about 0.004-0.015 B, optionally up to about 0.1% Zr, and the balance Ni and incidental impurities. The superalloy is characterized by a ?? solvus temperature that is within 5% of the ?? solvus temperature of the superalloy that does not include 1-6% Fe and a mole fraction of ?? that is within 15% of the mole fraction of the superalloy that does not include 1-6% Fe.

Abstract: A closure element for an internal passage in a component, and a related method and turbine blade or nozzle are disclosed. The closure element includes a spherical body made of a first superalloy, and a plurality of extensions extending from a surface of the spherical body. The plurality of extensions made of the same, similar or different material other than the first superalloy. Subjecting the component to at least one thermal cycle causes a braze material to form a metallurgical bond with the spherical body, the plurality of extensions and the passage wall to seal the internal passage.

Abstract: A composition of matter includes from about 16 to about 20 wt % chromium, greater than 6 to about 10 wt % aluminum, from about 2 to about 10 wt % iron, less than about 0.04 wt % yttrium, less than about 12 wt % cobalt, less than about 1.0 wt % manganese, less than about 1.0 wt % molybdenum, less than about 1.0 wt % silicon, less than about 0.25 wt % carbon, about 0.03 wt % boron, less than about 1.0 wt % tungsten, less than about 1.0 wt % tantalum, about 0.5 wt % titanium, about 0.5 wt % hafnium, about 0.5 wt % rhenium, about 0.4 wt % lanthanide elements, and the balance being nickel and incidental impurities. This nickel-based superalloy composition may be used in superalloy articles, such as a blade, nozzle, a shroud, a splash plate, a squealer tip of the blade, and a combustor of a gas turbine engine.

Abstract: A composition of matter includes from about 16 to about 20 wt % chromium, greater than 6 to about 10 wt % aluminum, from about 2 to about 10 wt % iron, less than about 0.04 wt % yttrium, less than about 12 wt % cobalt, less than about 1.0 wt % manganese, less than about 1.0 wt % molybdenum, less than about 1.0 wt % silicon, less than about 0.25 wt % carbon, about 0.03 wt % boron, less than about 1.0 wt % tungsten, less than about 1.0 wt % tantalum, about 0.5 wt % titanium, about 0.5 wt % hafnium, about 0.5 wt % rhenium, about 0.4 wt % lanthanide elements, and the balance being nickel and incidental impurities. This nickel-based superalloy composition may be used in superalloy articles, such as a blade, nozzle, a shroud, a splash plate, a squealer tip of the blade, and a combustor of a gas turbine engine.