Abstract: Various embodiments of the disclosure include turbine blades and systems employing such blades. Various embodiments include a turbine blade having: an airfoil having an airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each distance Z along at least a portion of the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the nominal profile.

Abstract: A blade airfoil including a platform, concave pressure sidewall and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and outboard tip. The blade further includes at least one part-span shroud positioned on the airfoil defined by a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in at least one of TABLE I and TABLE II. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying values by a length of the at least one part-span shroud. X and Y values are connected by continuing arcs to define part-span shroud profile sections at each distance Z along at least a portion of the at least one part-span shroud, profile sections at Z distances being joined with one another to form the nominal profile.

Abstract: A blade airfoil including a platform, concave pressure sidewall and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and outboard tip. The blade further includes at least one part-span shroud positioned on the airfoil defined by a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in at least one of TABLE I and TABLE II. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying values by a length of the at least one part-span shroud. X and Y values are connected by continuing arcs to define part-span shroud profile sections at each distance Z along at least a portion of the at least one part-span shroud, profile sections at Z distances being joined with one another to form the nominal profile.

Abstract: The present embodiments set forth a blade including an airfoil including an outer tip having a floor, a leading edge and a trailing edge, a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the floor and the tip cap. The airfoil further includes a tip cap extending from the floor of the outer tip and coextensive with the pressure sidewall and suction sidewall and around the leading edge and trailing edge. The tip cap includes a squealer tip configuration including a suction side tip cap portion and a pressure side tip cap portion. The suction side tip cap portion and pressure side tip cap portion extend unequal distances above the floor providing for cooling fluid flow out of the tip cap.

Abstract: A turbine nozzle for a gas turbine includes: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs that define airfoil profile sections at each distance Z along at least a portion of the airfoil, and the airfoil profile sections at the Z distances are joined smoothly with one another to form the nominal profile.

Abstract: A rotor blade for use in a turbine of a combustion turbine engine comprises an airfoil, which includes a concave pressure and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between base and outboard tip end. The rotor blade further including at least one mid-span shroud engages a corresponding mid-span shroud on at least one neighboring rotor blade. The airfoil includes an inboard region between the at least one mid-span shroud and base of the blade—and an outboard region between at least one mid-span shroud and outward tip. The outboard region includes at least two cavities extending from the outboard tip end inboard toward the at least one mid-span shroud; and inboard of the at least one mid-span shroud, the inboard region is substantially solid.

Abstract: Various embodiments of the disclosure include turbine blades and systems employing such blades. Various embodiments include a turbine blade having: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each distance Z along at least a portion of the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the nominal profile.

Abstract: A rotor blade for use in a turbine of a combustion turbine engine comprises an airfoil, which includes a concave pressure and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between base and outboard tip end. The rotor blade further including at least one mid-span shroud engages a corresponding mid-span shroud on at least one neighboring rotor blade. The airfoil includes an inboard region between the at least one mid-span shroud and base of the blade-and an outboard region between at least one mid-span shroud and outward tip. The outboard region includes at least two cavities extending from the outboard tip end inboard toward the at least one mid-span shroud; and inboard of the at least one mid-span shroud, the inboard region is substantially solid.

Abstract: A blade including an airfoil including a platform, concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and an outboard tip. The blade further includes an angled outboard snubber shroud positioned on the airfoil, the angled outboard snubber shroud being provided at an angle ? defined from a camber on the angled outboard snubber shroud and the platform of the blade; an angled inboard snubber shroud positioned on the airfoil, the angled inboard snubber shroud being provided at an angle ? defined from a camber on the angled inboard snubber shroud and the platform of the blade. The angle ? is independently set with respect to angle 4.

Abstract: The present embodiments set forth a blade including an airfoil including an outer tip having a floor, a leading edge and a trailing edge, a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the floor and the tip cap. The airfoil further includes a tip cap extending from the floor of the outer tip and coextensive with the pressure sidewall and suction sidewall and around the leading edge and trailing edge. The tip cap includes a squealer tip configuration including a suction side tip cap portion and a pressure side tip cap portion. The suction side tip cap portion and pressure side tip cap portion extend unequal distances above the floor providing for cooling fluid flow out of the tip cap.

Abstract: Various embodiments of the disclosure include turbine blades and systems employing such blades. Various embodiments include a turbine blade having: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each distance Z along at least a portion of the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the nominal profile.