Abstract: A method of forging includes a first forging action that changes the shape of a metallic alloy work piece. A second forging action further changes the shape of the metallic alloy work piece after the first forging action. A heat treatment step is conducted after the first forging action and prior to the second forging action. The heat treatment step includes subjecting the metallic alloy work piece to a heat treatment temperature that alters the microstructure of the metallic alloy work piece without the application of a forging action that changes the shape of the metallic alloy work piece.

Abstract: A manufacturing method includes providing a component, such as a superalloy aircraft component, with a substrate surface having damaged brittle compound particles from machining. The manufacturing method removes the damaged compound particles from the substrate surface without producing significant amount of new damaged compound particles in the substrate surface. In one example, the damaged compound particles are removed with an abrasive media. The method results in a machined substrate surface free from damaged intermetallic component particles.

Abstract: A method of forging includes a first forging action that changes the shape of a metallic alloy work piece. A second forging action further changes the shape of the metallic alloy work piece after the first forging action. A heat treatment step is conducted after the first forging action and prior to the second forging action. The heat treatment step includes subjecting the metallic alloy work piece to a heat treatment temperature that alters the microstructure of the metallic alloy work piece without the application of a forging action that changes the shape of the metallic alloy work piece.

Abstract: A manufacturing method includes providing a component, such as a superalloy aircraft component, with a substrate surface having damaged brittle compound particles from machining. The manufacturing method removes the damaged compound particles from the substrate surface without producing significant amount of new damaged compound particles in the substrate surface. In one example, the damaged compound particles are removed with an abrasive media. The method results in a machined substrate surface free from damaged intermetallic component particles.

Abstract: A manufacturing method includes providing a component, such as a superalloy aircraft component, with a substrate surface having damaged brittle compound particles from machining. The manufacturing method removes the damaged compound particles from the substrate surface without producing significant amount of new damaged compound particles in the substrate surface. In one example, the damaged compound particles are removed with an abrasive media. The method results in a machined substrate surface free from damaged intermetallic component particles.

Abstract: A multi-axis machine includes a controller operable to control a nozzle which ejects a particulate material relative to a part surface to maintain a compound angle and predetermined stand off distance to remove surface and near-surface crack initiation sites.

Abstract: A manufacturing method includes providing a component, such as a superalloy aircraft component, with a substrate surface having damaged brittle compound particles from machining. The manufacturing method removes the damaged compound particles from the substrate surface without producing significant amount of new damaged compound particles in the substrate surface. In one example, the damaged compound particles are removed with an abrasive media. The method results in a machined substrate surface free from damaged intermetallic component particles.

Abstract: A process for casting titanium alloy based parts includes the steps of melting a quantity of titanium alloy to form a molten titanium alloy; adding to the molten titanium alloy a quantity of boron in an amount of about 0.2 weight percent to about 1.3 weight percent of the molten titanium alloy to form a molten boron modified titanium alloy; and casting a boron modified titanium alloy based part.

Abstract: A nickel base super alloy composition wherein the ratio of molybdenum to tungsten or to the sum of tungsten and rhenium, Mo W ? ? ? o ? ? ? r , Mo W + Re Is in the range of about 0.25 to about 0.5 weight percent.

Abstract: A nickel base super alloy composition wherein the ratio of molybdenum to tungsten or to the sum of tungsten and rhenium, 1 M ⁢   ⁢ o W ⁢   ⁢ o ⁢   ⁢ r , M ⁢   ⁢ o W + R ⁢   ⁢ e

Abstract: A nickel base super alloy composition wherein the ratio of molybdenum to tungsten or to the sum of tungsten and rhenium, Mo w ⁢   or , Mo w + Re Is in the range of about 0.25 to about 0.5 weight percent.

Abstract: A creep resistant titianium aluminide alloy composition consisting essentially of, in atomic percent, about 44 to about 49 Al, about 0.5 to about 4.0 Nb, about 0.0 to about 3.0 Mn, about 1.0 to about 1.5 W, about 0.1 to about 1.0 Mo, about 0.4 to about 0.75 Si, and the balance Ti.

Abstract: Creep resistant titanium aluminide alloy article consisting essentially of, in atomic %, about 45 to about 48 Al, about 1.0 to about 3.0 Nb, about 0.5 to about 1.5 Mn, about 0.25 to about 0.75 Mo, about 0.25 to about 0.75 W, about 0.15 to about 0.3 Si and the balance titanium. The article has a heat treated microstructure including gamma phase, alpha-two phase and at least one additional particulate phase including, one or more or W, Mo, and Si dispersed as distinct regions in the microstructure.

Abstract: Fine grain titanium forgings and to a process for refining the grain size of .alpha. and .alpha.-.beta. titanium alloys through forging and recrystallization above the alloy's .beta.-transus temperature. Specifically, the method employs an isothermal press in which a billet heated above the alloy's .beta.-transus temperature, forged to produce an elongated, flattened grain structure, is held above the alloy's .beta.-transus temperature for a predetermined time to allow fine grains to nucleate and grow through recrystallization, and then is quenched to arrest grain growth and to establish a fine grained titanium alloy. A second forging step may be employed to attain an aspect ratio of the grains. The fine grained titanium forgings made by this process have a maximum prior .beta.-grain size of 0.5 mm throughout the workpiece.

Abstract: An improved forging billet of dual alloys and an improved method for forging a dual alloy billet. The billet is cylindrical in shape having an outer tubular portion of one alloy and another alloy filling the central opening through the tubular portion, the ends of the billet include a radial flange of the tubular alloy extending a short distance outward at each end of the billet and having a skirt extending from the outer end of the radial flange axially away from the body of the billet to form a circular opening at each end of the billet which has at least as large a diameter as the outer diameter of the outer tubular portion, and a sandwich structure positioned within each of said circular opening including a plurality of layers of a powdered lubricant, preferably boron nitride lubricant, separated by foil layers, preferably a high purity nickel foil.