Abstract: A system for a turbine blade tip to address wear during rubbing with a shroud, and also tip rail cooling, is provided. The turbine blade tip includes a tip rail and cooling passage(s) extending through a radially outer end surface thereof, providing direct cooling to the tip. The tip rail may include tip rail cooling inserts. The radial outer end surface of the tip rail includes a first portion radially inward of a second portion thereof. An abrasive layer extends along the first portion adjacent the cooling passage(s), and may include a matrix alloy having a plurality of cubic boron nitride (cBN) particles and a plurality of ceramic particles embedded therein. The abrasive layer extends radially outward of the second portion of the radial outer end surface. The system also may include a shroud including an abradable coating thereon.

Abstract: A rotor blade includes an airfoil defining at least one cooling passage and a camber line extending from a leading edge to a trailing edge. The rotor blade further includes a tip shroud coupled to the airfoil, the tip shroud and the airfoil defining a core fluidly coupled to the at least one cooling passage, the core including a plurality of outlet apertures, each of the plurality of outlet apertures including an opening defined in an exterior surface of the tip shroud. A first outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is between 15 degrees from parallel to and parallel to the camber line at the trailing edge. A second outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is greater than 15 degrees from parallel to the camber line at the trailing edge.

Abstract: A rotor blade includes an airfoil defining at least one cooling passage and a camber line extending from a leading edge to a trailing edge. The rotor blade further includes a tip shroud coupled to the airfoil, the tip shroud and the airfoil defining a core fluidly coupled to the at least one cooling passage, the core including a plurality of outlet apertures, each of the plurality of outlet apertures including an opening defined in an exterior surface of the tip shroud. A first outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is between 15 degrees from parallel to and parallel to the camber line at the trailing edge. A second outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is greater than 15 degrees from parallel to the camber line at the trailing edge.

Abstract: A rotor blade including an airfoil portion and a root portion, and an internal cooling circuit having flow passages in the root portion and the airfoil portion, wherein the internal cooling circuit includes: a first flow passage; and a non-integral plug. The plug may include a plug channel configured to correspond to a desired level of coolant flow through the first cooling passage. The plug may be connected to the rotor blade in a fixed blocking position relative to the first flow passage.

Abstract: A turbine blade is provided and includes pressure and suction surfaces connected to define an interior through which coolant is passable and first and second pedestal arrays, each of the first and second pedestal arrays including pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from pedestals of the second pedestal array by gaps respectively defined therebetween.

Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes an elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define a generally arcuate top portion of the elongated body that is configured to contact with a groove defined between the adjacent turbine blades. The elongated body includes a first side portion laterally opposed to a second side portion and defines a plurality of laterally extending slots. The slots are axially spaced along the center portion and each slot extends at least partially through at least one of the first side portion or the second side portion.

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: Turbine bucket nominal internal core profiles and core insert external profiles are provided. In one embodiment, a turbine bucket includes an airfoil, platform, shank and dovetail. The bucket has a nominal internal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are non-dimensional values which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the bucket, the profile sections at the Z distances being joined smoothly with one another to form said bucket internal core profile.

Abstract: A turbine bucket may include a platform and an airfoil extending from the platform. The airfoil may include an internal rib with a number of through holes positioned along a number of hole spaces and a number of in-between spaces. The in-between spaces may include a first depth, the hole spaces may include a second depth, and wherein the first depth is less than the second depth.

Abstract: A turbine bucket for use with a gas turbine engine, as described herein, 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: 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: 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 blade is provided and includes pressure and suction surfaces connected to define an interior through which coolant is passable and first and second pedestal arrays, each of the first and second pedestal arrays including pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from pedestals of the second pedestal array by gaps respectively defined therebetween.

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: 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: Turbine bucket nominal internal core profiles and core insert external profiles are provided. In one embodiment, a turbine bucket includes an airfoil, platform, shank and dovetail. The bucket has a nominal internal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are non-dimensional values which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the bucket, the profile sections at the Z distances being joined smoothly with one another to form said bucket internal core profile.

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: 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: The present application thus provides a turbine bucket. The turbine bucket may include a platform and an airfoil extending from the platform. The airfoil may include an internal rib with a number of through holes positioned along a number of hole spaces and a number of in-between spaces. The in-between spaces may include a first depth, the hole spaces may include a second depth, and wherein the first depth is less than the second depth.