Abstract: A core for use in casting a gas turbine bucket, the core comprising a solid, curved upper body portion and a pair of co-planar legs extending downwardly from the solid, curved upper body portion, the pair of legs separated by an elongated open slot extending from a lower end of the core upwardly more than half a height dimension of the core, into the upper body portion, and a pair of axially aligned pegs projecting in axially opposite directions from opposite sides of the solid, curved upper body portion, perpendicular to and above the elongated slot but spaced from an upper edge of the solid, curved upper body portion, the pair of pegs lying substantially in a plane containing the co-planar legs, and wherein, in a radial direction, the pegs are closer to the elongated slot than to the upper edge.

Abstract: An airfoil. The airfoil may include a first number of cooling holes and a second number of cooling holes positioned within the airfoil. The first number of cooling holes and the second number of cooling holes each may include a turbulated section and a non-turbulated section.

Abstract: A tip shroud for use with a bucket of a turbine. The tip shroud may include a seal rail with a middle portion and a cutter tooth mounted about the middle portion of the seal rail.

Abstract: Second stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0.05 to 0.95 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.160 inches in directions normal to the surface of the airfoil.

Abstract: A turbine stage one bucket has an airfoil having a plurality of cooling holes passing through the airfoil from 0% span to 100% span whereby cooling air exits the airfoil tip into the hot gas path. X and Y coordinate values are given in Table I, locating the holes relative to the airfoil profile at airfoil profile sections of 5%, 50% and 90% span, Table I also giving the hole diameters. In this manner, cooling hole optimization for this turbine bucket airfoil is achieved. The cooling holes are also located in relation to the profile of the bucket airfoil given by the X, Y and Z coordinate values of Table II, the two coordinate systems having the same origin.

Abstract: A core for use in casting a gas turbine bucket, the core comprising a solid upper body portion and a pair of legs extending downwardly from the solid upper body portion, the pair of legs separated by an elongated slot, and a pair of pegs projecting axially from opposite sides of the upper body portion, above the elongated slot but spaced from an upper edge of the upper body portion.