Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include an airfoil, a tip shroud positioned radially outward from the airfoil, and a seal rail positioned radially outward from the tip shroud and extending in a generally tangential direction from a first end to a second end of the tip shroud. The seal rail may include a maximum axial thickness at a location positioned between the first end and the second end and offset from the airfoil in the generally tangential direction. The present application and the resultant patent further provide a gas turbine engine and a method for balancing a tip shroud of a turbine bucket of a gas turbine engine.

Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular airfoil profile, which can be used to determine a throat between adjacent airfoils. By shaping the throat according to the particular profile, the total pressure at an endwall can be energized, improving performance of the turbine.

Abstract: A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.

Abstract: A damper system for the buckets of a gas turbine engine. The damper system may include damper pins having a generally rounded top portion and a generally flat bottom portion along substantially the entire length thereof. The generally flat bottom portion may allow addition or removal of material to or from the pin in order to achieve an optimal dynamic weight ratio.

Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: A turbomachine airfoil includes a base portion and a blade portion extending from the base portion to a tip portion defining a radial span dimension. The blade portion includes a leading edge, a trailing edge, a pressure side and a suction side. An axial chord dimension is defined between the leading edge and the trailing edge. At least one protuberance is provided on the pressure side. The at least one protuberance extends from about 10% of the axial chord dimension to about 90% of the axial chord dimension.

Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include an airfoil, a tip shroud positioned radially outward from the airfoil, and a seal rail positioned radially outward from the tip shroud and extending in a generally tangential direction from a first end to a second end of the tip shroud. The seal rail may include a maximum axial thickness at a location positioned between the first end and the second end and offset from the airfoil in the generally tangential direction. The present application and the resultant patent further provide a gas turbine engine and a method for balancing a tip shroud of a turbine bucket of a gas turbine engine.

Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: A seal for a turbine engine is provided that includes a seal body disposed at a base of a turbine engine blade and a wing portion extending axially from the seal body. The wing portion has a first portion substantially parallel with a centerline of the engine and an angled upturn portion. The first portion extends between the seal body and the angled upturn portion. An angle between the engine centerline and the angled upturn portion is between about 0 degrees and about 90 degrees.

Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular airfoil profile, which can be used to determine a throat between adjacent airfoils. By shaping the throat according to the particular profile, the total pressure at an endwall can be energized, improving performance of the turbine.

Abstract: The present application provides a tip shroud assembly for use with a turbine engine. The tip shroud assembly may include a shroud, a seal rail positioned on the shroud, and a contoured fillet attaching the seal rail to the shroud.

Abstract: A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.

Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: A damper system for the buckets of a gas turbine engine. The damper system may include damper pins having a generally rounded top portion and a generally flat bottom portion along substantially the entire length thereof. The generally flat bottom portion may allow addition or removal of material to or from the pin in order to achieve an optimal dynamic weight ratio.

Abstract: In one aspect, a seal for a turbine engine includes a seal body disposed at a base of a turbine engine blade and a wing portion extending axially from said seal body. The wing portion has a first portion substantially parallel with a centerline of the engine and an angled upturn portion. The first portion extends between the seal body and the angled upturn portion. An angle between the engine centerline and the angled upturn portion is between about 0 degrees and about 90 degrees.

Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: A turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, a combustor assembly fluidly connected to each of the compressor portion and the turbine portion, a blade element including a base portion, an airfoil portion, and a natural frequency generated during rotation of the blade element. The blade element is rotatably mounted within one of the compressor portion and the turbine portion, and a blade tuning member rotatably mounted in the one of the compressor portion and the turbine portion. The blade tuning member is configured for engagement with the blade element to alter the natural frequency.