Abstract: A gas turbine assembly includes a shroud that includes a plurality of interconnected shroud segments, wherein each one of the shroud segments comprises an arcuate base formed of a first metal material. The arcuate base is made up of an annular member having an axial component and a pair of upstanding ribs having flanges, wherein the arcuate base further comprises a high temperature capable material layer disposed on a surface of the arcuate base so as to define an inner diameter of the shroud segment (i.e., the hot gas path side or environmental side).

Abstract: A method of reducing stress in a turbine bucket having an internal cooling circuit formed by a casting core having laterally extending support pins of square or rectangular cross section includes: (a) redesigning the support pins to have a round cross section; or (b) removing the cross-over holes between adjacent cooling passages.

Abstract: The third stage nozzle has an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X and Y values are in inches and define airfoil profile sections at each distance Z and Z are non-dimensional values within a range from 0.1 to 0.9 convertible to Z distances in inches by multiplying the Z values of Table I within the range by a height of the airfoil in inches. The profile sections at the Z distances are joined smoothly with one another to form the nozzle airfoil shape. The X and Y distances may be scalable to provide a scaled-up or scaled-down airfoil for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.

Abstract: The third stage nozzle has an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X and Y values are in inches and define airfoil profile sections at each distance Z and Z are non-dimensional values within a range from 0.1 to 0.9 convertible to Z distances in inches by multiplying the Z values of Table I within said range by a height of the airfoil in inches. The profile sections at the Z distances are joined smoothly with one another to form the nozzle airfoil shape. The X and Y distances may be scalable to provide a scaled-up or scaled-down airfoil for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.