Abstract: A turbine blade with a generally hollow airfoil having an outer wall that defines a chamber for receiving cooling air, the airfoil comprising a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, a concave pressure side, and an insert disposed within the chamber that is configured to initially receive at least a portion of the cooling air entering the chamber and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall, the insert further comprising a configuration that generally conforms to the contour of the outer wall of the chamber but in spaced relation thereto, wherein the chamber and insert narrow as they extend toward the trailing edge, the insert eventually terminating and the chamber eventually terminating at a pin array section, wherein a first distance exists that comprises the generally axial distance between the position of downstream termination point of the insert an

Abstract: Gas turbine systems having flexible chordal hinge seals are provided. According to an embodiment, a turbine system comprises: a nozzle segment comprising a stator vane extending between an inner band segment and an outer band segment; an inner support ring adjacent to the inner band segment; and an inner chordal hinge seal in operable communication with the nozzle segment, the inner chordal hinge seal comprising a flexible inner rail extending inwardly from the inner band segment, the inner rail having a projection for sealingly engaging the inner support ring.

Abstract: A retention pin for fastening retaining lugs of an outer sidewall, of a turbine nozzle, within a groove between a forward land and an aft land of a retaining ring. The retention pins fit through coaxial holes in the lug and the lands, securing the radial and circumferential location of the nozzles as well as allowing transitional motion. While maintaining limited contact with both the nozzles and the retaining ring they significantly reduce conductive heat transfer from the nozzle to the retaining ring. By positioning the nozzles, they also set the desired nozzle throat areas for targeted turbine performance. The pins have been designed such that the nozzle cannot disengage within the assembly due to the pin backing out of its nominal axial position, and the pin will not fail due to low cycle fatigue, creep, or yielding, all of which prevent nozzle fallout.

Abstract: An outer sidewall retention scheme for a singlet first stage nozzle of a gas turbine. The retention scheme includes a circumferential retaining ring with a main body and a pair of circumferential retaining lands projecting inward radially. A circumferential annular retaining groove is formed between the pair of circumferential retaining lands. A first lug and a second lug mounted on an outer face of the outer sidewall of each nozzle are adapted to fit within the circumferential annular retaining groove of the retaining ring and are supported radially and circumferentially by a first retaining pin and a second retaining pin, each pin passing though the circumferential retaining lands. Each nozzle further includes a chordal hinge rail and seal on the outer sidewall and a chordal hinge rail and seal on the inner sidewall providing axial support for the nozzle.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth TABLE I. The X and Y values are distances in inches, which when connected by smooth continuing arcs define airfoil profile sections at each distance Z in inches The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of +0.130 inch to ?0.030 inch.

Abstract: A turbine blade with a generally hollow airfoil having an outer wall that defines a chamber for receiving cooling air, the airfoil comprising a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, a concave pressure side, and an insert disposed within the chamber that is configured to initially receive at least a portion of the cooling air entering the chamber and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall, the insert further comprising a configuration that generally conforms to the contour of the outer wall of the chamber but in spaced relation thereto, wherein the chamber and insert narrow as they extend toward the trailing edge, the insert eventually terminating and the chamber eventually terminating at a pin array section, wherein a first distance exists that comprises the generally axial distance between the position of downstream termination point of the insert an

Abstract: Gas turbine systems having flexible chordal hinge seals are provided. According to an embodiment, a turbine system comprises: a nozzle segment comprising a stator vane extending between an inner band segment and an outer band segment; an inner support ring adjacent to the inner band segment; and an inner chordal hinge seal in operable communication with the nozzle segment, the inner chordal hinge seal comprising a flexible inner rail extending inwardly from the inner band segment, the inner rail having a projection for sealingly engaging the inner support ring.

Abstract: A retention pin for fastening retaining lugs of an outer sidewall, of a turbine nozzle, within a groove between a forward land and an aft land of a retaining ring. The retention pins fit through coaxial holes in the lug and the lands, securing the radial and circumferential location of the nozzles as well as allowing transitional motion. While maintaining limited contact with both the nozzles and the retaining ring they significantly reduce conductive heat transfer from the nozzle to the retaining ring. By positioning the nozzles, they also set the desired nozzle throat areas for targeted turbine performance. The pins have been designed such that the nozzle cannot disengage within the assembly due to the pin backing out of its nominal axial position, and the pin will not fail due to low cycle fatigue, creep, or yielding, all of which prevent nozzle fallout.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth TABLE I. The X and Y values are distances in inches, which when connected by smooth continuing arcs define airfoil profile sections at each distance Z in inches The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of +0.130 inch to ?0.030 inch.

Abstract: An outer sidewall retention scheme for a singlet first stage nozzle of a gas turbine. The retention scheme includes a circumferential retaining ring with a main body and a pair of circumferential retaining lands projecting inward radially. A circumferential annular retaining groove is formed between the pair of circumferential retaining lands. A first lug and a second lug mounted on an outer face of the outer sidewall of each nozzle are adapted to fit within the circumferential annular retaining groove of the retaining ring and are supported radially and circumferentially by a first retaining pin and a second retaining pin, each pin passing though the circumferential retaining lands. Each nozzle further includes a chordal hinge rail and seal on the outer sidewall and a chordal hinge rail and seal on the inner sidewall providing axial support for the nozzle.