Abstract: A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. The first metallic material is an aluminum alloy containing between about 0.5 wt % and about 3.0 wt % of lithium.

Abstract: A fan blade is disclosed comprising a lightweight metallic airfoil portion and a high-strength sheath portion. The airfoil portion has a forward airfoil edge, a first airfoil surface, and a second airfoil surface. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface.

Abstract: A turbine engine apparatus includes a structural component made of a superalloy material. A protective coating is disposed on the structural component and has a composition that consists essentially of up to 30 wt % cobalt, 5-40 wt % chromium, 7.5-35 wt % aluminum, up to 6 wt % tantalum, up to 1.7 wt % molybdenum, up to 3 wt % rhenium, up to 5 wt % tungsten, up to 2 wt % yttrium, 0.05-2 wt % hafnium, 0.05-7 wt % silicon, 0.01-0.1 wt % zirconium, and a balance of nickel.

Abstract: A revert alloy is used in the manufacture of a target alloy having a different composition. The weight percent of the elemental constituents of this first alloy and a second or target alloy are obtained, and the ratio of the percentage by weight of each elemental constituent in the first alloy to the second alloy is determined. The lowest ratio is used to determine the amount of the first alloy that is melted and the necessary elemental constituents that are added to the melt to produce the desired composition of the target alloy. The melt is solidified to produce the target alloy.

Abstract: A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. The first metallic material is an aluminum alloy containing between about 0.5 wt % and about 3.0 wt % of lithium.

Abstract: A revert alloy is used in the manufacture of a target alloy having a different composition. The weight percent of the elemental constituents of this first alloy and a second or target alloy are obtained, and the ratio of the percentage by weight of each elemental constituent in the first alloy to the second alloy is determined. The lowest ratio is used to determine the amount of the first alloy that is melted and the necessary elemental constituents that are added to the melt to produce the desired composition of the target alloy. The melt is solidified to produce the target alloy.

Abstract: A turbine engine apparatus includes a structural component made of a superalloy material. A protective coating is disposed on the structural component and has a composition that consists essentially of up to 30 wt % cobalt, 5-40 wt % chromium, 7.5-35 wt % aluminum, up to 6 wt % tantalum, up to 1.7 wt % molybdenum, up to 3 wt % rhenium, up to 5 wt % tungsten, up to 2 wt % yttrium, 0.05-2 wt % hafnium, 0.05-7 wt % silicon, 0.01-0.1 wt % zirconium, and a balance of nickel.

Abstract: A fan blade is disclosed comprising a lightweight metallic airfoil portion and a high-strength sheath portion. The airfoil portion has a forward airfoil edge, a first airfoil surface, and a second airfoil surface. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface.

Abstract: A revert alloy is used in the manufacture of a target alloy having a different composition. The weight percent of the elemental constituents of this first alloy and a second or target alloy are obtained, and the ratio of the percentage by weight of each elemental constituent in the first alloy to the second alloy is determined. The lowest ratio is used to determine the amount of the first alloy that is melted and the necessary elemental constituents that are added to the melt to produce the desired composition of the target alloy. The melt is solidified to produce the target alloy.

Abstract: A superalloy has a composition of, in weight percent, from about 16.0 percent to about 22.4 percent cobalt, from about 6.6 percent to about 14.3 percent chromium, from about 1.4 percent to about 3.5 percent tantalum, from about 1.9 percent to about 4.0 percent tungsten, from about 1.9 percent to about 3.9 percent molybdenum, from about 0.03 percent to about 0.10 percent zirconium, from about 0.9 percent to about 3.0 percent niobium, from about 2.4 percent to about 4.6 percent titanium, from about 2.6 percent to about 4.8 percent aluminum, from 0 to about 2.5 percent rhenium, from about 0.02 percent to about 0.10 percent carbon, from about 0.02 percent to about 0.10 percent boron, balance nickel and minor amounts of impurities. The superalloy is advantageously utilized in aircraft gas turbine disks.

Abstract: A die cast article such is composed of nickel base superaloy IN 718 is disclosed. The microstructure is characterized by an absence of flowlines and includes a fine average grain size, e.g., ASTM 3 or smaller. Exemplary articles include gas turbine engine components, such as blades, vanes, cases and seals.

Abstract: A method of heat treating articles cast of a superalloy, comprising a nickel-base alloy capable of forming a chromium carbide precipitate, such as INCONEL 939.TM.. The method includes selective heating of the article to cause chromium and carbon nuclei in the lattice of the crystals in the superalloy to go into solution, and selective cooling of the article to cause the formation of discrete chromium carbide nuclei along the grain boundary of the crystals. Additional heating steps may be performed to enhance the size of the chromium carbide nuclei. Articles so treated have improved mechanical properties.