Abstract: A turbine rotor blade that includes an airfoil defined between a concave pressure face and a laterally opposed convex suction face, and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; an outlet segment discharges the coolant from the rotor blade at a shallow angle relative to a flow direction of a working fluid through the turbine; and an elbow segment connects the supply segment to the outlet segment and is positioned near the outboard tip of the airfoil. The elbow segment may be configured for accommodating a change of direction between the supply segment and the outlet segment.

Abstract: A turbine rotor blade that includes: an airfoil defined between a pressure face and a suction face; a tip shroud that includes a seal rail projecting from an outboard surface and, formed thereon, a cutter tooth; and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; a cutter tooth segment is formed within the cutter tooth of the seal rail; and branching segments formed within at least one of the tip shroud and an outboard region of the airfoil. Each of the branching segments may extend between an upstream port, which connects to the cutter tooth segment, and an outlet port, which is formed on a target surface area, so that the branching segment bisects a target interior region.

Abstract: A rotor blade includes an airfoil portion that extends in a radial direction from a root end to a tip end. A plurality of internal airfoil cooling passages is defined in the airfoil portion. The rotor blade also includes a tip shroud. The tip shroud includes a shroud plate coupled to the tip end. A plurality of tip shroud cooling passages is defined within the shroud plate. Each of the tip shroud cooling passages extends within the shroud plate in a direction generally transverse to the radial direction. Each tip shroud passage includes an inlet coupled in flow communication with at least one of the airfoil cooling passages, and an exit opening defined in, and extending therethrough, a radially outer surface of the tip shroud. The exit opening is coupled in flow communication with the inlet.

Abstract: A turbine bucket according to various embodiments includes: a base; a blade coupled to the base and extending radially outward from the base, the blade including: a body having: a pressure side; a suction side opposing the pressure side; a leading edge between the pressure side and the suction side; and a trailing edge between the pressure side and the suction side on a side opposing the leading edge; a plurality of radially extending cooling passageways within the body; and at least one bleed aperture fluidly coupled with at least one of the plurality of radially extending cooling passageways, the at least one bleed aperture extending through the body at the trailing edge; and a shroud coupled to the blade radially outboard of the blade.

Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.

Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to the base, extending radially outward from the base, and including: a body having: a pressure side; a suction side opposing the pressure side; a leading edge between the pressure side and the suction side; and a trailing edge between the pressure side and the suction side on a side opposing the leading edge; and a plurality of radially extending cooling passageways within the body; and a shroud coupled to the blade radially outboard of the blade, including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within the body; and an outlet path extending at least partially circumferentially through the shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within the body.

Abstract: A rotor blade for a turbine of a gas turbine system. The rotor blade may include: an airfoil that includes a pressure sidewall and a suction sidewall defining an outer periphery, wherein the pressure sidewall and suction sidewall of the airfoil connect along a leading edge and a trailing edge; a tip that defines an outer radial end of the airfoil, wherein the tip included a cap on which an outboard projecting rail defines a tip cavity; and a rail gap formed through an aftward section of the rail.

Abstract: A turbine rotor blade includes a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall. Further included is at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity. Yet further included is a main body having a suction side wall and a pressure side wall each extending from a root portion of the turbine rotor blade to the tip portion.

Abstract: A steam turbine exhaust hood includes an exhaust hood section, and a butterfly plate arranged in the exhaust hood section. The butterfly plate includes a complex curvilinear cross-sectional profile having a first section that extends between a first end portion and a middle portion, and a second section that extends between the middle portion and a second end portion. One of the first and second sections is formed from at least two curvilinear segments including at least one curvilinear segment having a positive curvature and at least one curvilinear segment having a negative curvature.

Abstract: A steam turbine exhaust hood includes an exhaust hood section, and a butterfly plate arranged in the exhaust hood section. The butterfly plate includes a complex curvilinear cross-sectional profile having a first section that extends between a first end portion and a middle portion, and a second section that extends between the middle portion and a second end portion. One of the first and second sections is formed from at least two curvilinear segments including at least one curvilinear segment having a positive curvature and at least one curvilinear segment having a negative curvature.