Abstract: The present application provides a turbine bucket for use with a gas turbine engine. The turbine bucket may include a platform, an airfoil extending from the platform, and a number of cooling circuits extending through the platform and the airfoil. One of the cooling circuits may be a serpentine cooling channel positioned within the platform.

Abstract: The present application thus provides a turbine bucket. The turbine bucket may include a platform, an airfoil extending from the platform at an intersection thereof, and a core cavity extending within the platform and the airfoil. The core cavity may include a contoured turn about the intersection so as to reduce thermal stress therein.

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 turbine blade includes an airfoil portion including a suction side having a suction side contour, a pressure side having a pressure side contour, a leading edge, a trailing edge and a tip portion, and a squeeler pocket formed in the tip portion. The squeeler pocket includes a first side wall and a second side wall. The first side wall includes a first internal surface having a first substantially continuous curvilinear profile and the second side wall includes a second internal surface having a second substantially continuous curvilinear profile. A bleed passage extends from the squeeler pocket towards the trailing edge. The first and second side walls are configured to deliver a substantially unobstructed fluid flow from the squeeler pocket to the bleed passage and limit the fluid flow spillage onto one of the pressure side and the suction side.

Abstract: A turbomachine is provided and includes first and second endwalls disposed to define a pathway, each of the first and second endwalls including a surface facing the pathway and first and second blades extendible across the pathway from at least one of the first and second endwalls, each of the first and second blades having an airfoil shape and being disposed such that a pressure side of the first blade faces a suction side of the second blade. A portion of the surface of at least one of the first and second endwalls between the first and second blades has at least a first hump proximate to a leading edge and the pressure side of the first blade, and a second hump disposed at 10-60% of a chord length of the first blade and proximate to the pressure side thereof.

Abstract: A turbomachine component includes a main body having a gas path surface configured to be exposed to gases passing along a turbomachine gas path, a non gas path surface configured to be arranged in a turbomachine wheelspace outside the turbomachine gas path, and a non-axisymetric flow contour feature extending from the gas path surface to the non gas path surface.

Abstract: The present application thus provides an airfoil for use in a turbine. The airfoil may include a wall, an internal cooling plenum, and a cooling hole extending through the wall to the cooling plenum. The cooling hole may include an offset counterbore therein.

Abstract: According to one aspect of the invention, a turbine airfoil includes a platform and a blade extending from the platform. The airfoil also includes a slot formed in a slashface of the platform, the slot being configured to receive a pressurized fluid via passages and configured to direct the pressurized fluid to a selected region of the turbine airfoil to improve airfoil life.

Abstract: A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body.

Abstract: A configuration of cooling channels through the interior of a turbine rotor blade having a platform, wherein the rotor blade includes an airfoil cooling channel that includes a cooling channel formed within the airfoil and an outboard airfoil supply channel. The configuration of cooling channels may include: a platform cooling channel that comprises a cooling channel that traverses at least a portion of the platform, the platform cooling channel having an upstream end and a downstream end; an outboard platform supply channel, which comprises a cooling channel that stretches from a second coolant inlet formed in the root to the upstream end of the platform cooling channel; and an inboard platform return channel, which comprises a cooling channel that stretches from the downstream end of the platform cooling channel to a termination point formed in the root.

Abstract: A dual-component locking spacer assembly for insertion in a circumferential dovetail slot includes a stationary member having a platform configured to fit into a space between the adjacent rotor blade platforms. A first leg extends transversely from an underside of the platform. A longitudinally extending groove is defined in the platform. A slide member is movably engaged with the stationary member along the groove, and includes an upper plate and a second leg connected to the upper plate. The slide member is movable along the groove between a first unlocked position wherein the first and second legs are spaced apart a first distance so as to be insertable into the dovetail slot, and a second locked position wherein the first and second legs are spaced apart an extended second distance so as to engage against opposite walls of the dovetail slot and lock the stationary member in position in the dovetail slot.

Abstract: The present application provides a turbine blade cooling system. The turbine blade cooling system may include a first turbine blade with a first turbine blade platform having a cooling cavity in communication with a pressure side passage and a second turbine blade with a second turbine blade platform having a platform cooling cavity with a suction side passage. The pressure side passage of the first turbine blade platform is in communication with the suction side passage of the second turbine blade platform.

Abstract: A bucket assembly and a method for forming the bucket assembly are disclosed. The bucket assembly includes a platform, an airfoil, and a lower body portion. The platform defines a platform cooling circuit configured to flow cooling medium therethrough. The airfoil extends radially outward from the platform. The lower body portion extends radially inward from the platform. The lower body portion defines a root and a cooling passage extending from the root. The cooling passage is configured to flow cooling medium therethrough. The platform and lower body portion further include a ligament between the cooling passage and the platform cooling circuit. The ligament defines a bore hole extending through the ligament between the cooling passage and the platform cooling circuit.

Abstract: Disclosed is a coating for gas turbine components including at least one material having vibration-damping properties. Further disclosed is an airfoil of a gas turbine having damped vibrational characteristics including an airfoil substrate and a coating applied to the airfoil substrate including at least one material having vibration-damping properties. A method of damping vibration of a gas turbine component includes applying a coating including at least one material having damping properties to the turbine component.

Abstract: A dual-component locking spacer assembly for insertion in a circumferential dovetail slot includes a stationary member having a platform configured to fit into a space between the adjacent rotor blade platforms. A first leg extends transversely from an underside of the platform. A longitudinally extending groove is defined in the platform. A slide member is movably engaged with the stationary member along the groove, and includes an upper plate and a second leg connected to the upper plate. The slide member is movable along the groove between a first unlocked position wherein the first and second legs are spaced apart a first distance so as to be insertable into the dovetail slot, and a second locked position wherein the first and second legs are spaced apart an extended second distance so as to engage against opposite walls of the dovetail slot and lock the stationary member in position in the dovetail slot.

Abstract: A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body.

Abstract: A blade for a turbine includes: a support structure of high strength material as a central portion of the blade, the support structure including a root and a body extending to a tip, the body providing a leading edge, a trailing edge and mounting section; and a honeycomb skin attached to the mounting section for providing a lightweight airfoil portion of the blade. A method and a turbine are included.

Abstract: Disclosed is a coating for gas turbine components including at least one material having vibration-damping properties. Further disclosed is an airfoil of a gas turbine having damped vibrational characteristics including an airfoil substrate and a coating applied to the airfoil substrate including at least one material having vibration-damping properties. A method of damping vibration of a gas turbine component includes applying a coating including at least one material having damping properties to the turbine component.