Abstract: A turbine bucket includes an airfoil extending from a platform, having high and low pressure sides; a wheel mounting portion; a hollow shank portion located radially between the platform and the wheel mounting portion, the platform having an under surface. An impingement cooling plate is located in the hollow shank portion, spaced from the under surface, and the impingement plate is formed with a plurality of impingement cooling holes therein.

Abstract: A turbine bucket includes an airfoil extending from a platform, having high and low pressure sides; a wheel mounting portion; a hollow shank portion located radially between the platform and the wheel mounting portion, the platform having an under surface. An impingement cooling plate is located in the hollow shank portion, spaced from the under surface, and the impingement plate is formed with a plurality of impingement cooling holes therein.

Abstract: A turbine blade includes an airfoil having opposite first and second sides and an internal passage extending longitudinally therebetween. A plurality of turbulator ribs extend from the first side into the passage and have substantially identical configurations including first and second ends having a span axis extending therebetween, first and second sides having a width therebetween, and a base and a tip having a height e measured therebetween. The passage includes a height H for defining a rib-to-passage height ratio e/H. Adjacent ribs are spaced apart at a longitudinal spacing S for defining a rib spacing-to-height ratio S/e. The rib configuration varies along the span axis between the rib first and second ends for correspondingly varying at least one of the ratios e/H and S/e to effect a varying convective heat transfer enhancement along the rib span axis for increasing enhancement and reducing cooling airflow.

Abstract: A gas turbine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. A plurality of longitudinally spaced apart primary turbulator ribs extend into the internal passage from at least one of the first and second sides. An auxiliary turbulator rib is spaced between adjacent ones of the primary ribs. The auxiliary rib has a height which is less than the height of the primary ribs for augmenting convective heat transfer enhancement with reduced pressure loss, and, therefore, reduced cooling air requirements.

Abstract: A gas turbine engine turbine blade and method of manufacture includes an airfoil having pressure and suction sides joined together at leading and trailing edges. The airfoil further includes a supply channel for receiving compressed air, and has an elongate recess disposed in at least one of the pressure and suction sides which is separated from the supply channel by a partition. The partition includes a plurality of spaced apart flow metering holes disposed in flow communication with the supply channel. A transpiration strip is fixedly joined to the airfoil in the recess and spaced from the partition to define a plenum for receiving the compressed air from the metering holes. The transpiration strip is pervious for channeling the compressed air from the plenum in a blanket of film cooling boundary layer air therefrom.