Abstract: A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a skewed axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. A part span shroud is attached at an intermediate section of the airfoil portion between the ends thereof. The blade includes an exit annulus area of about 47.7 ft2 (4.43 m2) or greater.

Abstract: A method of assembling a steam turbine including a rotor assembly is provided. The method includes providing at least one turbine bucket including a dovetail that includes a plurality of crush surfaces, a plurality of non-contact surfaces, and at least one neck defined between one of the crush surfaces and one of the non-contact surfaces. The method also includes providing a turbine wheel that includes at least one dovetail slot defined therein that is defined by a plurality of crush surfaces and a plurality of non-contact surfaces, and coupling the dovetail of the at least one turbine bucket within the turbine wheel slot such that a slant angle of the at least one neck facilitates a substantially uniform distribution of load between the dovetail and the at least one slot.

Abstract: A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a skewed axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. A part span shroud is attached at an intermediate section of the airfoil portion between the ends thereof. The blade includes an exit annulus area of about 47.7 ft2 (4.43 m2) or greater.

Abstract: A method of assembling a steam turbine including a rotor assembly is provided. The method includes providing at least one turbine bucket including a dovetail that includes a plurality of crush surfaces, a plurality of non-contact surfaces, and at least one neck defined between one of the crush surfaces and one of the non-contact surfaces. The method also includes providing a turbine wheel that includes at least one dovetail slot defined therein that is defined by a plurality of crush surfaces and a plurality of non-contact surfaces, and coupling the dovetail of the at least one turbine bucket within the turbine wheel slot such that a slant angle of the at least one neck facilitates a substantially uniform distribution of load between the dovetail and the at least one slot.

Abstract: An open cooling circuit for a gas turbine bucket wherein the bucket has an airfoil portion, and a tip shroud, the cooling circuit including a plurality of radial cooling holes extending through the airfoil portion and communicating with an enlarged internal area within the tip shroud before exiting the tip shroud such that a cooling medium used to cool the airfoil portion is subsequently used to cool the tip shroud.

Abstract: A core for use in casting a turbine bucket including serpentine cooling passages is divided into two pieces including a leading edge core section and a trailing edge core section. Wall thicknesses at the leading edge and the trailing edge of the turbine bucket can be controlled independent of each other by separately positioning the leading edge core section and the trailing edge core section in the casting die. The controlled leading and trailing edge thicknesses can thus be optimized for efficient cooling, resulting in more efficient turbine operation.

Abstract: A core for use in casting a turbine bucket including serpentine cooling passages is divided into two pieces including a leading edge core section and a trailing edge core section. Wall thicknesses at the leading edge and the trailing edge of the turbine bucket can be controlled independent of each other by separately positioning the leading edge core section and the trailing edge core section in the casting die. The controlled leading and trailing edge thicknesses can thus be optimized for efficient cooling, resulting in more efficient turbine operation.

Abstract: An open cooling circuit for a gas turbine bucket wherein the bucket has an airfoil portion, and a tip shroud, the cooling circuit including a plurality of radial cooling holes extending through the airfoil portion and communicating with an enlarged internal area within the tip shroud before exiting the tip shroud such that a cooling medium used to cool the airfoil portion is subsequently used to cool the tip shroud.