Abstract: A turbine nozzle for a turbine includes: an airfoil having a shape with 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, and the profile sections at the Z distances are joined smoothly with one another to form the nominal profile.

Abstract: The present application provides a turbine rotor blade including an airfoil shape and a trailing edge shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, while the trailing edge profile is defined by Table II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance (e.g., inches). The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: The present application provides a turbine rotor blade including an airfoil shape and a trailing edge shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, while the trailing edge profile is defined by Table II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance (e.g., inches). The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: A turbine nozzle for a turbine includes: an airfoil having a shape with 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, and the profile sections at the Z distances are joined smoothly with one another to form the nominal profile.

Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a pair of part-span connectors extending from the airfoil at the suction side and the pressure side, respectively, wherein each of the pair of part-span connectors is located between approximately 40 percent and approximately 70 percent of a radial span measured from the base to a radial tip of the airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.

Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including an axisymmetric contour.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a pair of part-span connectors extending from the airfoil at the suction side and the pressure side, respectively, wherein each of the pair of part-span connectors is located between approximately 40 percent and approximately 70 percent of a radial span measured from the base to a radial tip of the airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.

Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including an axisymmetric contour.

Abstract: A system and method for integrating sections of a turbine are provided. In one system, a turbine includes a last stage bucket section with a first annular outer wall that is angled with respect to a centerline of the turbine at a first angle average. The turbine also includes a diffuser section having a second annular outer wall that is angled with respect to the centerline of the turbine at a second angle average for improving radial swirl. The first angle average is greater than the second angle average.

Abstract: A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway for a fluid flow and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway. The plurality of the blade stages includes a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage. The plurality of the nozzle stages includes a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage. At least one of the next-to-last blade stage and the next-to-last nozzle stage includes aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow.

Abstract: A turbomachine airfoil includes a base portion and a blade portion extending from the base portion to a tip portion defining a radial span dimension. The blade portion includes a leading edge, a trailing edge, a pressure side and a suction side. An axial chord dimension is defined between the leading edge and the trailing edge. At least one protuberance is provided on the pressure side. The at least one protuberance extends from about 10% of the axial chord dimension to about 90% of the axial chord dimension.

Abstract: The present application provides a turbine nozzle. The turbine nozzle may include an airfoil with a leading edge and a trailing edge and a flow groove extending from the leading edge to the trailing edge.

Abstract: The present application provides a turbine nozzle. The turbine nozzle may include an airfoil with a leading edge and a trailing edge and a flow fence extending from the leading edge to the trailing edge.

Abstract: A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that extends from a connection at the root to the approximate radial height of the platform, wherein, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein a pressure side of the platform comprises a topside extending circumferentially from the airfoil to a pressure side slashface. The platform cooling arrangement may include: a platform cavity formed within the pressure side of the platform, a high-pressure connector that connects the platform cavity to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the platform cavity to the low-pressure coolant region of the interior cooling passage; and a pin bank formed within the platform cavity that includes radial pins.

Abstract: A turbomachine component includes a turbine stator nozzle member having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil core shape.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.