Abstract: A method includes positioning a braze material along a defect of a component of a turbine system, positioning a cover over the braze material, and focusing a heat source on the cover to melt the braze material along the defect.

Abstract: A system includes a gas turbine component having a recessed portion with a recessed surface in a hard-to-weld (HTW) material. The system includes a plate disposed over the recessed portion. The plate has an easy-to-weld (ETW) material. The plate has an outer surface and an inner surface, and the inner surface faces the recessed portion. The system includes a braze material disposed within the recessed portion between the recessed surface and the inner surface of the plate. The braze material is configured to bond the recessed surface of the recessed portion with the inner surface of the plate when the braze material is heated to a brazing temperature. The system includes a filler material disposed on the outer surface of the plate disposed over the recessed portion. Application of the filler material to the outer surface of the plate is configured to heat the braze material to the brazing temperature.

Abstract: A system includes a gas turbine component having a recessed portion with a recessed surface in a hard-to-weld (HTW) material. The system includes a plate disposed over the recessed portion. The plate has an easy-to-weld (ETW) material. The plate has an outer surface and an inner surface, and the inner surface faces the recessed portion. The system includes a braze material disposed within the recessed portion between the recessed surface and the inner surface of the plate. The braze material is configured to bond the recessed surface of the recessed portion with the inner surface of the plate when the braze material is heated to a brazing temperature. The system includes a filler material disposed on the outer surface of the plate disposed over the recessed portion. Application of the filler material to the outer surface of the plate is configured to heat the braze material to the brazing temperature.

Abstract: A process includes placing a powder composition of a first metal powder of a first alloy and a second metal powder of a second alloy in a ceramic die and sintering the powder composition in the ceramic die to form a sintered rod in the ceramic die. The process also includes removing the sintered rod from the ceramic die and slicing the sintered rod into a plurality of pre-sintered preforms.

Abstract: Casting methods and articles are disclosed wherein a molten first material is introduced into a mold which distributes the first material to form a first region of the article where it is subjected to a first condition suitable for growing a first grain structure, forming the first region of the article. A molten second material, compositionally distinct from the first material, is introduced into the mold to form a second region of the article. A hybridized material is formed by intermixing a first portion of the second material with the second portion of the first material. A second portion of the second material is subjected to a second condition suitable for growing a second grain structure distinct from the first grain structure, forming the second region of the article. The first region and the second region are integrally formed as a single, continuous article with a hybridized region formed between.

Abstract: Casting methods and articles are disclosed wherein a molten first material is introduced into a mold which distributes the first material to form a first region of the article where it is subjected to a first condition suitable for growing a first grain structure, forming the first region of the article. A molten second material, compositionally distinct from the first material, is introduced into the mold to form a second region of the article. A hybridized material is formed by intermixing a first portion of the second material with the second portion of the first material. A second portion of the second material is subjected to a second condition suitable for growing a second grain structure distinct from the first grain structure, forming the second region of the article. The first region and the second region are integrally formed as a single, continuous article with a hybridized region formed between.

Abstract: An article and a method for forming the article are disclosed. The article comprising a composition, wherein the composition comprises, by weight percent, about 20.0% to about 22.0% chromium (Cr), about 18.0% to about 20.0% cobalt (Co), about 1.0% to about 2.0% tungsten (W), about 3.0% to about 6.0% niobium (Nb), about 0.5% to about 1.5% titanium (Ti), about 2.0% to about 3.0% aluminum (Al), about 0.5% to about 1.5% molybdenum (Mo), about 0.03% to about 0.18% carbon (C), up to about 0.15% tantalum (Ta), up to about 0.20% hafnium (Hf), up to about 0.20% iron (Fe),balance nickel (Ni) and incidental impurities. The amount of Al is present according to the following formula: Al??(0.5*Ti)+3.75 The composition is weldable, has a microstructure comprising between about 35 vol % and 45 vol % gamma prime (??) and is substantially devoid of Eta and reduced content of TCP phases at elevated working temperatures. A method of making an article and a method of operating a gas turbine are also disclosed.

Abstract: A cast nickel-iron-base alloy component having by weight about 12.0% to about 16.5% Cr, about 1.0% to about 2.0% Al, about 2.0% to about 3.0% Ti, about 2.0% to about 3.0% W, about 3.0 to about 5.0% Mo, up to about 0.1% Nb, up to about 0.2% Mn, up to about 0.1% Si, about 0.05% to about 0.10% C, about 0.003 to about 0.010% B, about 35% to about 37% Fe, and balance essentially Ni and inevitable impurities. The nickel-iron-base alloy component has a creep rupture life greater than about 1000 hours at about 25 ksi to about 30 ksi at about 1400° F. A method for forming the cast nickel-iron-base alloy component is also disclosed.

Abstract: Disclosed is a turbine, a turbine seal structure, and a process of servicing a turbine. The turbine includes the seal structure. The seal structure is mechanically secured within the hot gas path of the turbine. The process of servicing includes positioning the seal structure within the hot gas path of the turbine and mechanically securing the seal structure within the turbine.

Abstract: Provided is a turbine seal, a turbine, and a process of fabricating a turbine seal. The turbine seal includes a metallic foam positioned along a hot gas path of a turbine. The turbine includes a blade configured to rotate along a predetermined path in response to a hot gas and a metallic foam turbine seal positioned to be contacted by the hot gas. The process of fabricating the turbine seal includes providing a blade configured to rotate along a predetermined path in response to a hot gas and positioning a metallic foam turbine seal to be contacted by the hot gas.

Abstract: A nickel-iron-base alloy has by weight about 0.06% to about 0.09% C, about 35% to about 37% Fe, about 12.0% to about 16.5% Cr, about 1.0% to about 2.0% Al, about 1.0% to about 3.0% Ti, about 1.5% to about 3.0% W, up to about 5.0% Mo, up to about 0.75% Nb, up to about 0.2% Mn, up to about 0.1% Si, up to about 0.006% B, and balance essentially Ni. A method for making the nickel-iron-base alloy is also disclosed.