Abstract: A turbine bucket is disclosed which includes a dovetail for mounting the bucket within the turbine, a parallelogram-shaped platform connected to the dovetail, a parallelogram-shaped shroud, and an airfoil connected between the platform and the shroud. The platform includes an inner flowpath surface at which a first end of the airfoil intersects with the platform the inner flowpath surface being parallelogram-shaped and formed from a first inclined plane and a second inclined plane that meet at a first common boundary and form a first ridge or valley, boundary bisecting the inner flowpath surface, the shroud including an outer flowpath surface at which the second end of the airfoil intersects the shroud, the outer flowpath surface being parallelogram-shaped and formed from a third inclined plane and a fourth inclined plane that meet at a second common boundary and form a second ridge or valley, second common boundary bisecting the outer flowpath surface.

Abstract: A method for assembling a turbine, wherein the method includes coupling at least one nozzle assembly including an outer band, an inner band, a nozzle, and a dovetail, to a stator that includes a plurality of dovetail slots and channels defined therein, slidably coupling the at least one nozzle assembly into a respective dovetail slot, and fixedly securing the at least one nozzle assembly to the stator with a load pin that extends between the nozzle assembly and the dovetail slot.

Abstract: A turbine bucket is disclosed which includes a dovetail for mounting the bucket within the turbine, a parallelogram-shaped platform connected to the dovetail, a parallelogram-shaped shroud, and an airfoil connected between the platform and the shroud. The platform includes an inner flowpath surface at which a first end of the airfoil intersects with the platform the inner flowpath surface being parallelogram-shaped and formed from a first inclined plane and a second inclined plane that meet at a first common boundary and form a first ridge or valley, boundary bisecting the inner flowpath surface, the shroud including an outer flowpath surface at which the second end of the airfoil intersects the shroud, the outer flowpath surface being parallelogram-shaped and formed from a third inclined plane and a fourth inclined plane that meet at a second common boundary and form a second ridge or valley, second common boundary bisecting the outer flowpath surface.

Abstract: Nozzles for a turbine have dovetail-shaped bases for reception in corresponding dovetail-shaped grooves in the carrier halves of a turbine. The nozzles at each of the horizontal joint faces of each carrier half have notches formed along their bases including an abutment face. Key slots are formed in the horizontal joint faces and receive keys bearing against the abutment faces. The keys are peened or screwed into the carrier half at the horizontal joint faces. Radial loading pins engage the end nozzle bases to bias the end nozzles radially inwardly without interfering with the keys retaining the nozzles in the grooves.

Abstract: Nozzles for a turbine have dovetail-shaped bases for reception in corresponding dovetail-shaped grooves in the carrier halves of a turbine. The nozzles at each of the horizontal joint faces of each carrier half have notches formed along their bases including an abutment face. Key slots are formed in the horizontal joint faces and receive keys bearing against the abutment faces. The keys are peened or screwed into the carrier half at the horizontal joint faces. Radial loading pins engage the end nozzle bases to bias the end nozzles radially inwardly without interfering with the keys retaining the nozzles in the grooves.

Abstract: A combustion liner and cooling sleeve assembly for a turbine combustor includes a substantially cylindrical combustion liner; and a substantially cylindrical outer cooling sleeve surrounding at least an axial portion of the combustion liner; wherein the outer cooling sleeve is secured to the combustion liner by a weld at one end of the cooling sleeve at its aft end, with a predetermined radial gap therebetween, the gap determined by respective operating temperatures and thermal expansion coefficients.

Abstract: A brazing process is provided that addresses the braze joint failure problems encountered in some multi-nozzle combustion end covers. The brazing process embodying the invention provides optimal, predictable low cycle fatigue joint life in particular when brazing 304L stainless steel parts using Amdry 915 braze alloy. The invention was realized in particular in the combination of and application of tightly controlled vital variables of gap, braze alloy, braze peak temperature hold time, cooling (quench) rate, surface finish and braze media to optimal limits for the process parameters. The process provides robust/reliable design limits for braze joints experiencing stress during operation.