Abstract: A method of repairing a turbomachine rotor wheel including a first outer circumferential edge extending to a second outer circumferential edge through a circumferential surface, a dovetail interface extending across the outer circumferential surface between the first and second outer circumferential edges, and a bucket mounted to the dovetail interface includes identifying a defect on one of the first and second outer circumferential edges of the rotor wheel adjacent the bucket, securing the bucket in the dovetail interface to substantially constrain axial movement, and removing a portion of the one of the first and second outer circumferential edges to remove the defect.

Abstract: A stator ring for use in a compressor of a gas turbine engine and a method of assembling the stator ring are provided. The stator ring includes a first plurality of segments that includes a first segment including a first circumferential end formed with a first cut and a second circumferential end formed with a second cut that is complementary to the first cut, wherein the first plurality of segments are configured to be circumferentially-coupled together, and a second plurality of segments that includes a second segment including a first circumferential end with a third cut and a second circumferential end with a fourth cut that is complementary to the third cut, wherein the second plurality of segments are configured to be circumferentially-coupled together.

Abstract: A method of repairing a turbomachine rotor wheel including a first outer circumferential edge extending to a second outer circumferential edge through a circumferential surface, a dovetail interface extending across the outer circumferential surface between the first and second outer circumferential edges, and a bucket mounted to the dovetail interface includes identifying a defect on one of the first and second outer circumferential edges of the rotor wheel adjacent the bucket, securing the bucket in the dovetail interface to substantially constrain axial movement, and removing a portion of the one of the first and second outer circumferential edges to remove the defect.

Abstract: A stator ring for use in a compressor of a gas turbine engine and a method of assembling the stator ring are provided. The stator ring includes a first plurality of segments that includes a first segment including a first circumferential end formed with a first cut and a second circumferential end formed with a second cut that is complementary to the first cut, wherein the first plurality of segments are configured to be circumferentially-coupled together, and a second plurality of segments that includes a second segment including a first circumferential end with a third cut and a second circumferential end with a fourth cut that is complementary to the third cut, wherein the second plurality of segments are configured to be circumferentially-coupled together.

Abstract: A stator blade segment for a compressor includes an inner ring segment and an outer ring segment and a plurality of stator blades extending radially between the inner and outer ring segments, the stator blade secured to the outer ring at a shank portion of the blade and loosely held in a slot in the inner ring segment at a tip portion of the blade, the slot formed to substantially match a cross-sectional profile of the tip portion of the blade but sized to create a clearance between the tip portion and the slot.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S–16S, 1R–17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.