Abstract: An article of manufacture includes a rotor blade configured for use with a turbomachine. The blade is configured for attachment to a rotor wheel. The blade is configured to substantially reduce the possibility of attachment with an undesired rotor wheel by modification of at least one characteristic of the blade, so that the modification of the characteristic is matched by a complementary characteristic of the rotor wheel. The characteristic of the blade is, neck width, platform length, platform angle, platform height, tang height, or circumferential width. The blade and the wheel comprise a first stage of the turbomachine. The undesired rotor wheel is in a second stage of the turbomachine, where the first stage is different from the second stage. The complementary characteristic of the wheel is, slot opening width, platform opening depth, slot neck width, slot neck angle, slot tang depth, or slot tang width.

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a pair of part-span connectors extending from the airfoil at the suction side and the pressure side, respectively, wherein each of the pair of part-span connectors is located between approximately 40 percent and approximately 70 percent of a radial span measured from the base to a radial tip of the airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a pair of part-span connectors extending from the airfoil at the suction side and the pressure side, respectively, wherein each of the pair of part-span connectors is located between approximately 40 percent and approximately 70 percent of a radial span measured from the base to a radial tip of the airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.

Abstract: A method is provided for modifying an airfoil shroud located at a tip of a blade of an airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge, and a trailing edge. The method includes locating a reference location in the first end edge of the airfoil shroud, the reference location including a portion of a seal rail extending circumferentially from a radially outer surface of the airfoil shroud, and a fillet extending from the radially outer surface and positioned directly adjacent to the seal rail. The method further includes forming a relief cut in the seal rail and fillet without performing a weld process on the airfoil shroud to remove the reference location, and installing the airfoil shroud in a turbomachine directly following forming the relief cut, wherein modifying the airfoil shroud is complete following forming the relief cut.

Abstract: An article of manufacture includes a rotor blade configured for use with a turbomachine. The blade is configured for attachment to a rotor wheel. The blade is configured to substantially reduce the possibility of attachment with an undesired rotor wheel by modification of at least one characteristic of the blade, so that the modification of the characteristic is matched by a complementary characteristic of the rotor wheel. The characteristic of the blade is, neck width, platform length, platform angle, platform height, tang height, or circumferential width. The blade and the wheel comprise a first stage of the turbomachine. The undesired rotor wheel is in a second stage of the turbomachine, where the first stage is different from the second stage. The complementary characteristic of the wheel is, slot opening width, platform opening depth, slot neck width, slot neck angle, slot tang depth, or slot tang width.

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: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: According to one aspect of the invention, a method is provided for modifying an airfoil shroud located at a tip of an airfoil of a airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge and a trailing edge. The method includes locating a reference location in the first end edge of the airfoil shroud, the reference location being proximate a seal rail extending circumferentially from the substantially horizontal surface and forming a relief cut in the airfoil shroud to remove the reference location, wherein a modifying of the airfoil shroud is complete following forming of the relief cut.

Abstract: An article of manufacture is provided having a first component configured for use with a turbomachine. The first component is configured for attachment to a second component. The first component is configured to substantially reduce the possibility of attachment with an undesired third component by modification of at least one characteristic of the first component, so that the modification of the at least one characteristic is matched by a complementary characteristic of the second component.

Abstract: An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a. characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.