Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially aligned with and axially spaced from a second end portion and a retention pin that is coaxially aligned with and disposed between the first end portion and the second end portion. The retention pin couples the first end portion to the second end portion. The damper pin further includes a plurality of rings coaxially aligned with and disposed along the retention pin between the first end portion and the second end portion. The first end portion, the second end portion and the plurality of rings define a generally arcuate outer surface of the damper pin that is configured to contact with a groove defined between the adjacent turbine blades.

Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially spaced from a second end portion and a spring member that extends axially from an inner surface of the first end portion to an inner surface of the second end portion. The first end portion, the spring member and the second end portion define a generally arcuate top portion of the damper pin. The top portion is configured to contact with a groove defined between the adjacent turbine blades.

Abstract: A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.

Abstract: A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.

Abstract: An article and a process of producing an article are provided. The article includes a base material, a cooling feature arrangement positioned on the base material, the cooling feature arrangement including an additive-structured material, and a cover material. The cooling feature arrangement is between the base material and the cover material. The process of producing the article includes manufacturing a cooling feature arrangement by an additive manufacturing technique, and then positioning the cooling feature arrangement between a base material and a cover material.

Abstract: A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.

Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially aligned with and axially spaced from a second end portion and a retention pin that is coaxially aligned with and disposed between the first end portion and the second end portion. The retention pin couples the first end portion to the second end portion. The damper pin further includes a plurality of rings coaxially aligned with and disposed along the retention pin between the first end portion and the second end portion. The first end portion, the second end portion and the plurality of rings define a generally arcuate outer surface of the damper pin that is configured to contact with a groove defined between the adjacent turbine blades.

Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially spaced from a second end portion and a spring member that extends axially from an inner surface of the first end portion to an inner surface of the second end portion. The first end portion, the spring member and the second end portion define a generally arcuate top portion of the damper pin. The top portion is configured to contact with a groove defined between the adjacent turbine blades.

Abstract: An article and a process of producing an article are provided. The article includes a base material, a cooling feature arrangement positioned on the base material, the cooling feature arrangement including an additive-structured material, and a cover material. The cooling feature arrangement is between the base material and the cover material. The process of producing the article includes manufacturing a cooling feature arrangement by an additive manufacturing technique, and then positioning the cooling feature arrangement between a base material and a cover material.

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: A turbine blade comprises a cooling passage defined between a pressure side wall and a suction side wall. A pin is disposed within the cooling passage and includes a first end that is connected to the pressure side wall and a second end that is connected to the suction side wall. A radially oriented fillet having a maximum radius of curvature value is disposed along a periphery of at least one of the first end or the second end within a region of peak steady state stress. An axially oriented fillet having a maximum radius of curvature value is disposed along a periphery of at least one of the first end or second end within a region of peak vibratory stress. The maximum radius of curvature value of the axially oriented fillet is greater than the maximum radius of curvature value of the radially oriented fillet.

Abstract: A retention system for a plurality of turbine buckets located in respective mating slots in a turbine rotor wheel includes a plurality of first circumferentially-oriented retention slots formed in outer peripheral portions of the turbine wheel; a plurality of second circumferentially-oriented retention slots formed in wheel mounting portions of said buckets, the first and second circumferentially-oriented retention slots aligned to form an annular lockwire retention slot; and a lockwire located within the annular lockwire retention slot. A first surface feature on one or both of the turbine rotor wheel and one or more of said plurality of turbine buckets is adapted to engage a second surface feature on the lockwire for preventing rotation of the lockwire beyond predetermined limits.

Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 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: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 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: A retention system for a plurality of turbine buckets located in respective mating slots in a turbine rotor wheel includes a plurality of first circumferentially-oriented retention slots formed in outer peripheral portions of the turbine wheel; a plurality of second circumferentially-oriented retention slots formed in wheel mounting portions of said buckets, the first and second circumferentially-oriented retention slots aligned to form an annular lockwire retention slot; and a lockwire located within the annular lockwire retention slot. A first surface feature on one or both of the turbine rotor wheel and one or more of said plurality of turbine buckets is adapted to engage a second surface feature on the lockwire for preventing rotation of the lockwire beyond predetermined limits.

Abstract: The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon.

Abstract: The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon.

Abstract: A damper pin for a turbine bucket includes an elongated main body portion of substantially uniform cross-sectional shape having opposite ends, one only of said opposite ends coated with a corrosion and oxidation-resistant coating.

Abstract: A weld process cuitable for repairing precipitation-strengthened superalloys, and particularly gamma prime-strengthened nickel-based superalloys. The process entails forming a weldment in a cavity present in a surface of an article formed of a precipitation-strengthened superalloy. The cavity has a root region and a cap region between the root region and the surface of the article. A solid body formed of a superalloy composition is placed in the root region of the cavity so as to occupy a first portion but not a second portion of the root region. A first filler material formed of a solid solution-strengthened superalloy is then weld-deposited in the second portion of the root region. Subsequently, a second filler material formed of a precipitation-strengthened superalloy is weld-deposited in the cap region of the cavity.

Abstract: Methods and apparatus for cooling rotor blades of a gas turbine are provided. The turbine blade has an airfoil connected to the platform and a dovetail extending from the platform. A main cooling circuit extends through the dovetail and into the airfoil. The main cooling circuit includes an exit for main cooling flow from the airfoil to exit out through the dovetail. In one aspect, the method includes the steps of extracting a portion of the coolant flowing through the main cooling circuit into a platform cooling circuit. After cooling a portion of the platform, the platform cooling flow splits with one portion of the flow rejoining the main cooling circuit and is used to cool the airfoil. The rest of the platform cooling flow continues to cool the platform and then returns to the main cooling circuit to flow through the exit.