Abstract: A method for preparing a surface includes providing an article having an article surface, thereafter first processing the article surface to establish a first residual compressive stress state and a first surface roughness in the article surface, and thereafter second processing the article surface by surface compressive texturing to establish a second residual compressive stress state and a second surface roughness in the article surface. The second surface roughness is quantitatively less than the first surface roughness, and substantially no material is removed from the article surface in the step of second processing.

Abstract: Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.

Abstract: Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.

Abstract: A dual alloy disk made from a rim alloy having high stress rupture and creep resistance as well as good hold time fatigue crack resistance and a hub alloy having high tensile strength and good low cycle fatigue crack resistance is described. The dual alloy disk is designed for use as a disk in gas turbine engines operating as high as 1500.degree. F. The hub and rim are joined together at a substantially defect-free joint to form a turbine disk having improved properties in both the hub and rim regions.

Abstract: Improved, creep-stress rupture and hold-time fatigue resistant nickel base alloys for use at elevated temperatures are disclosed. The alloys consists essentially of, in weight percent, 10.9 to 12.9% Co; 11.8 to 13.8% Cr; 4.6 to 5.6% Mo; 2.1 to 3.1% Al; 4.4 to 5.4% Ti; 1.1 to 2.1% Nb; 0.005 to 0.025% B; 0.01 to 0.06% C; 0 to 0.6% Zr; 0.1 to 0.3% Hf; balance nickel. The article is characterized by a microstructure having an average grain size of from about 20 to 40 microns, with carbides, borides, and 0.3 to 0.4 micron-sized coarse gamma prime located at the grain boundaries, and 30 nanometer-sized fine gamma prime uniformly distributed throughout the grains. The alloys are suitable for use as turbine disks in gas turbine engines of the type used in jet engines, or for use as rim sections of dual alloy turbine disks for advanced turbine engines and are capable of operation at temperatures up to about 1500.degree. F. A method for achieving the desired properties in such turbine disks is also disclosed.

Abstract: Improved, high strength, fatigue crack-resistant nickel-base alloys for use at elevated temperatures are disclosed. The alloys are suitable for use as turbine disks in gas turbine engines of the type used in jet engines, or for use as hub sections of dual alloy turbine disks for advanced turbine engines, maintaining stability at engine operating temperatures up to about 1500.degree. F. The alloy is characterized by a microstructure having an average grain size of from about 10 microns to 20 microns. Coarse and fine intragranular gamma prime particles are distributed throughout the grains, of sizes 0.15-0.2 microns and 15 nanometers, respectively. The grain boundaries are substantially free of gamma prime, but have carbides and borides. A method for achieving the desired properties in such turbine disks is also disclosed.