Abstract: A turbine bucket for a gas turbine engine may include a platform, an airfoil extending radially outward from the platform, and a number of cooling passages defined at least partially within the airfoil. At least one of the cooling passages may extend radially to an outlet defined in an outer surface of the airfoil radially inward from a tip end of the turbine bucket.

Abstract: The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include a platform, an airfoil extending radially outward from the platform, and a number of cooling passages defined at least partially within the airfoil. At least one of the cooling passages may extend radially to an outlet defined in an outer surface of the airfoil radially inward from a tip end of the turbine bucket. The present application and the resultant patent further provide a method for cooling a turbine bucket of a gas turbine engine.

Abstract: A retention system retains a turbine blade dovetail in a retention ring dovetail slot. The retention system includes a retention opening formed in the blade dovetail. A through hole is formed in the retention ring, wherein the through hole is positioned such that it is aligned with the retention opening when the dovetail is assembled in the dovetail slot. A connector is disposed in the through hole and engages the retention opening. In this manner, undesirable relative movement of parts can be reduced or eliminated, thereby preventing excessive wear.

Abstract: Accordingly, in one aspect, the invention relates to a variable guide vane for an axial flow compressor comprising: a first radially outer vane section; and a second radially inner vane section; the first and second vane sections angularly adjustable relative to each other about a longitudinal radial axis of the vane.

Abstract: Stator blade counts of an upper compressor casing for adjacent stages S0 and S1 are changed in the field to provide additional stator vanes and hence an increased vane count. Particularly, the upper casing half of the compressor is removed from the lower casing half. The original stator vanes on opposite axial sides of the first stage buckets are removed from the upper casing half and replaced by an additional sets of stator vanes providing a non-uniform vane spacing as between the upper and lower halves of the compressor as well as between axially adjacent stages S0 and S1. The unequal vane counts reduce the vibratory response of the rotating blades between stages S0 and S1.

Abstract: A retention system retains a turbine blade dovetail in a retention ring dovetail slot. The retention system includes a retention opening formed in the blade dovetail. A through hole is formed in the retention ring, wherein the through hole is positioned such that it is aligned with the retention opening when the dovetail is assembled in the dovetail slot. A connector is disposed in the through hole and engages the retention opening. In this manner, undesirable relative movement of parts can be reduced or eliminated, thereby preventing excessive wear.