Abstract: A nozzle assembly includes a first nozzle cavity, a second nozzle cavity, a rib positioned between the nozzle cavities, a rib cap positioned on the rib, a first cavity insert, and a second cavity insert. The rib cap is wider than the rib, such that the rib cap extends outwardly into those portions of the nozzle cavities immediately adjacent the rib. The first cavity insert and the second cavity insert include a longitudinal surface offset from the rib. The offset surfaces include rib cap-interface surfaces that are joined to the rib cap. A method of modifying the nozzle assembly is achieved by installing a rib cap having a width greater than that of the rib and by installing modified cavity inserts having a surface offset from the rib, and by joining rib cap-interface surfaces of the modified cavity inserts to the rib cap.

Abstract: A nozzle assembly includes a first nozzle cavity, a second nozzle cavity, a rib positioned between the nozzle cavities, a rib cap positioned on the rib, a first cavity insert, and a second cavity insert. The rib cap is wider than the rib, such that the rib cap extends outwardly into those portions of the nozzle cavities immediately adjacent the rib. The first cavity insert and the second cavity insert include a longitudinal surface offset from the rib. The offset surfaces include rib cap-interface surfaces that are joined to the rib cap. A method of modifying the nozzle assembly is achieved by installing a rib cap having a width greater than that of the rib and by installing modified cavity inserts having a surface offset from the rib, and by joining rib cap-interface surfaces of the modified cavity inserts to the rib cap.

Abstract: The present application provides a nozzle assembly for use in a turbine engine. The nozzle assembly may include a first nozzle cavity, a second nozzle cavity, a rib positioned between the first nozzle cavity and the second nozzle cavity, a first cavity insert with a first cavity insert configuration, a second cavity insert with a second cavity insert configuration, and a rib cap positioned on the rib. The rib cap may include a rib cap configuration such that only the first cavity insert with the first cavity insert configuration fits within the first nozzle cavity and only the second cavity insert with the second cavity insert configuration fits within the second nozzle cavity.

Abstract: The second-stage nozzles have vanes comprising airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at the radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the nozzle.

Abstract: The second-stage nozzles have vanes comprising airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at the radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the nozzle.

Abstract: The third-stage nozzles have vanes comprising airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for each nozzle vane.