Abstract: A turbine blade includes an airfoil section, wherein at least one cooling hole is formed a tip floor of the airfoil section, which is fluidically connected to an internal coolant cavity of the airfoil section. The turbine blade further includes an additively manufactured tip cap formed via layer-by-layer deposition of material directly over the tip floor of the airfoil section. The tip cap includes at least one squealer tip rail extending outward from the tip floor. The at least one squealer tip rail comprises an embedded cooling channel formed therein. The embedded cooling channel is aligned with and fluidically connected to the at least one cooling hole formed through the tip floor of the airfoil section. The embedded cooling channel comprises one or more outlets located on at least one of a side face and a top face of the at least one squealer tip rail.

Abstract: The present disclosure relates to novel nickel-base alloy compositions including 7.25-7.75 wt % Cr, 0.6-1.0 wt % Mo, 8.5-9.1 wt % W, 6.0-6.4 wt % Al, 0.6-1.0 wt % Ti, 0.06-0.10 wt % C, 0.01-0.02 wt % B, 0.4-0.6 wt % Hf, and at least one of: 8.6-9.6 wt % Co and 4.0-4.8 wt % Ta; or 8.6-9.4 wt % Co, 3.8-4.4 wt % Ta, and 0.4-0.6 wt % Re, with the balance being nickel and trace impurities. Gas turbine blades or guide vanes are also provided, where the blades or vanes are formed using an alloy having such compositions.

Abstract: Reprographic or imaging systems and methods issue a command to place multiple finishing devices into an alternating delivery mode such that consecutive sets are sent to different finishing devices, rather than to the same finishing device.

Abstract: Reprographic or imaging systems and methods issue a command to place multiple finishing devices into an alternating delivery mode such that consecutive sets are sent to different finishing devices, rather than to the same finishing device.