Abstract: The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.

Abstract: A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge of the platform. A related turbomachine is also disclosed.

Abstract: The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.

Abstract: A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge root extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge root. A related turbomachine is also disclosed.

Abstract: A cooling circuit for a turbine bucket having an airfoil portion includes a trailing edge cooling circuit portion provided with a first radially outwardly directed inlet passage intermediate leading and trailing edges of the airfoil portion of the bucket, extending from a platform portion of the bucket to a location adjacent a radially outer tip of the bucket, and connecting to a second radially inwardly directed passage extending from a location adjacent the radially outer tip to a location adjacent the platform portion. The second radially inwardly directed passage connects to a third trailing edge region passage, and a plurality of crossover passages connect a radially outer half of the second radially inwardly directed passage to a radially outer half of the third trailing edge region passage.

Abstract: A turbine blade having a tip including a tip shelf through which pass one or more diffuser cooling holes, the diffuser cooling holes directing the flow of cooling gas along the tip shelf, spreading the flow of cooling gas more evenly along the tip shelf and enhancing the formation of a curtain of cooling air along the tip shelf, leading to lower blade tip temperatures, reduced diversion of cooling air, and greater turbine blade life.

Abstract: A cooling circuit for a turbine bucket having an airfoil portion includes a trailing edge cooling circuit portion provided with a first radially outwardly directed inlet passage intermediate leading and trailing edges of the airfoil portion of the bucket, extending from a platform portion of the bucket to a location adjacent a radially outer tip of the bucket, and connecting to a second radially inwardly directed passage extending from a location adjacent the radially outer tip to a location adjacent the platform portion. The second radially inwardly directed passage connects to a third trailing edge region passage, and a plurality of crossover passages connect a radially outer half of the second radially inwardly directed passage to a radially outer half of the third trailing edge region passage.

Abstract: A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root. The platform may include a pressure side slashface and a suction side slashface. The platform cooling arrangement may include: a cooling channel formed within the interior of the platform, the cooling channel extending from a first end toward one of the pressure side slashface and the suction side slashface. At a second end, the cooling channel may include a pocket. The pocket may include an abrupt increase in cross-sectional flow area just before the cooling channel reaches the slashface.

Abstract: A component is provided and includes a first surface, a second surface adjacent to and oriented transversely with respect to the first surface and having a pocket formed therein defining a rib along a periphery thereof and a thermal barrier coating (TBC) respectively applied to the first surface and to the second surface at the pocket such that the rib is interposed between the TBC of the first and second surfaces.

Abstract: A turbine bucket includes an airfoil, a platform adjacent to the airfoil, and a shank adjacent to the platform. The shank defines a shank cavity, and a divider in the shank cavity creates a pressure differential across the shank cavity. A method for cooling a turbine bucket includes directing a fluid to a forward shank cavity and creating a pressure differential between the forward shank cavity and an aft shank cavity.

Abstract: A turbine blade includes an outer surface, and a rim surrounds at least a portion of the outer surface. A trench in the rim extends around at least a portion of the outer surface.

Abstract: A turbine bucket is provided and includes a shank defining a cavity therein, which is connectable with a rotor such that wheelspace air having an initial pressure is permitted to flow into the cavity and a platform coupled to the shank and defining a cooling hole therein, the shank and the platform each further defining the cavity and the cooling hole, respectively, as being fluidly communicative with one another, such that the wheelspace air permitted to flow into the cavity is deliverable from the cavity and through the cooling hole at a second pressure greater than the initial pressure.

Abstract: A component is provided and includes a first surface, a second surface adjacent to and oriented transversely with respect to the first surface and having a pocket formed therein defining a rib along a periphery thereof and a thermal barrier coating (TBC) respectively applied to the first surface and to the second surface at the pocket such that the rib is interposed between the TBC of the first and second surfaces.

Abstract: A turbine bucket includes an airfoil, a platform adjacent to the airfoil, and a shank adjacent to the platform. The shank defines a shank cavity, and a divider in the shank cavity creates a pressure differential across the shank cavity. A method for cooling a turbine bucket includes directing a fluid to a forward shank cavity and creating a pressure differential between the forward shank cavity and an aft shank cavity.

Abstract: A turbine bucket is provided and includes a shank defining a cavity therein, which is connectible with a rotor such that wheelspace air having an initial pressure is permitted to flow into the cavity and a platform coupled to the shank and defining a cooling hole therein, the shank and the platform each further defining the cavity and the cooling hole, respectively, as being fluidly communicative with one another, such that the wheelspace air permitted to flow into the cavity is deliverable from the cavity and through the cooling hole at a second pressure greater than the initial pressure.