Abstract: A trailing edge coupon for the trailing edge of a airfoil of a turbine nozzle segment is welded to an airfoil section of the nozzle segment having a damaged trailing edge portion removed. The coupon includes film cooling holes spaced one from the other along a pressure side wall portion of the coupon and a plurality of radially spaced openings along the trailing edge. By welding the pressure and suction side edges of the coupon to the pressure and side edges of the remaining portion of the airfoil, the operating life of the nozzle is extended.

Abstract: First stage stator vanes for a turbine comprised airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I, which define a plurality of radially spaced profile sections forming the nominal profile. The Z coordinate values for each profile section are radial distances from the turbine axis to a portion of the surface of revolution about the axis containing the profile section. The X and Y values for each profile section are coordinate values which, when connected by smooth continuing arcs define the airfoil profile section along the surface of revolution portion. The radially spaced profile sections are joined smoothly with one another to form the nominal airfoil profile.

Abstract: A trailing edge coupon for the trailing edge of a airfoil of a turbine nozzle segment is welded to an airfoil section of the nozzle segment having a damaged trailing edge portion removed. The coupon includes film cooling holes spaced one from the other along a pressure side wall portion of the coupon and a plurality of radially spaced openings along the trailing edge. By welding the pressure and suction side edges of the coupon to the pressure and side edges of the remaining portion of the airfoil, the operating life of the nozzle is extended.

Abstract: A method for assembling a turbine nozzle assembly with respect to a combustor of a gas turbine engine is provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles is provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle.

Abstract: An article of manufacture pattern for improving aerodynamic performance of a turbine including an abradable material capable of abradable contact. The abradable material is disposed in a pattern. The pattern includes a first plurality of ridges disposed at a base surface of the turbine. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

Abstract: A pattern for improving aerodynamic performance of a turbine includes a material disposed in a pattern at a base surface of a turbine shroud such that the material is capable of abradable contact with a tip portion of a turbine bucket. The pattern includes a first plurality of ridges disposed at the base surface such that a first portion of the first plurality of ridges corresponding to a back portion of the turbine bucket is oriented at a first angle with respect to an axis of rotation of the turbine bucket. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

Abstract: A trailing edge coupon for the trailing edge of a airfoil of a turbine nozzle segment is welded to an airfoil section of the nozzle segment having a damaged trailing edge portion removed. The coupon includes film cooling holes spaced one from the other along a pressure side wall portion of the coupon and a plurality of radially spaced openings along the trailing edge. By welding the pressure and suction side edges of the coupon to the pressure and side edges of the remaining portion of the airfoil, the operating life of the nozzle is extended.

Abstract: Nozzle segments are secured to a retention ring against circumferential rotation by anti-rotation pins extending generally axially between the outer bands of the nozzle segments and the retention ring. Retention plate segments overlie the ends of the pins, preventing axial removal thereof. To remove a selected nozzle segment, inner diameter retention plate segments and selected retention plate segments are removed, the latter exposing the ends of the pins for axial withdrawal. Upon removal of a predetermined number of pins, the nozzle segments adjacent the selected segment are displaced away from the latter segment to open a gap between the selected segment and adjacent segments whereby the selected segment can be removed in an axial direction.

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.