Abstract: An environmental barrier coating system, a method of application and an article formed thereby suitable for reducing creep by incorporation of doping materials in grain boundaries of a bond coat layer to inhibit creep displacement of the EBC system when subjected to shear loading at elevated temperatures. The EBC system includes the bond coat layer on a silicon-containing substrate and at least one ceramic layer on the bond coat layer. The bond coat layer includes silicon and at least one doping material that includes a creep-resistant element. The doping material is located at grain boundaries within the bond coat layer in sufficient size and quantity to improve the creep resistance of the bond coat layer.

Abstract: A locking spacer assembly for insertion in a circumferential attachment slot includes a first end piece and a second end piece. The first and second end pieces each comprise an outer surface and an inner surface, the inner surfaces generally facing towards each other when the end pieces are inserted into the attachment slot. An actuator is movable between the inner surfaces and a spacer block is configured to be inserted between the inner surfaces. A fastener is configured to secure the spacer block to the actuator. The actuator is configured to engage the inner surfaces such that the end pieces move toward each other and lock the assembly within the attachment slot.

Abstract: A method for manufacturing a composite includes perforating an outer ply to create perforations through the outer ply and inserting a filler material into the perforations. The method further includes laminating the outer ply to an inner ply.

Abstract: A turbomachine includes a housing, and at least one turbine vane arranged within the housing. The at least one turbine vane includes a platform portion operatively connected to the airfoil portion. A cooling cavity is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged opposite the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned opposite the third wall. An impingement cooling plate extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate including at least one impingement cooling passage that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.

Abstract: A blade assembly for a rotor includes an attachment section operably connectable to a rotor, and an airfoil section. At least one retainer extends in a substantially tangential direction at least partially through the airfoil section and the attachment section to secure the airfoil section to the attachment section. A method of assembling a rotor assembly includes inserting at least one retainer in a substantially tangential direction at least partially through an attachment section of a blade assembly and an airfoil section of the blade assembly, thereby securing the airfoil section to the attachment section. The blade assembly is then secured to a rotor.

Abstract: A turbine includes a turbine wheel having a plurality of buckets, each of the buckets including a bucket airfoil, a bucket dovetail to connect the bucket to a turbine wheel and a shank shape to connect the airfoil to the bucket dovetail, the shank having an uncoated nominal profile including a concave, pressure side, substantially in accordance with Cartesian values of X, Y and Z? set forth in Table I wherein the Z? values are non-dimensional values in a range from 0 to 1 convertible to Z distances in inches by multiplying the Z? values by shank height in inches, and a convex, suction side, substantially in accordance with Cartesian values of X, Y and Z? set forth in Table II wherein the Z? values are non-dimensional values in a range from 0 to 1 convertible to Z distances in inches by multiplying the Z? values by the shank height in inches.

Abstract: A turbine bucket including a bucket airfoil having a hollow tip shroud, the hollow tip shroud having a hollow core having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, in inches, wherein the shape of the core is defined by the cloud of points listed which are distributed around each surface of the shroud, and the complete hollow portion of the tip shroud could be constructed by defining smooth sheet surfaces through the listed points.

Abstract: A locking spacer assembly for insertion in a circumferential attachment slot includes a first end piece and a second end piece. The first and second end pieces each comprise an outer surface and an inner surface, the inner surfaces generally facing towards each other when the end pieces are inserted into the attachment slot. An actuator is movable between the inner surfaces and a spacer block is configured to be inserted between the inner surfaces. A fastener is configured to secure the spacer block to the actuator. The actuator is configured to engage the inner surfaces such that the end pieces move toward each other and lock the assembly within the attachment slot.

Abstract: In one embodiment, a turbine bucket includes: a tip shroud with a front edge and a following edge, the front edge and the following edge including a Z-Notch profile according to the Cartesian coordinate values of X, Y and Z set forth in Table I; wherein the coordinate values are dimensional values representing a distance from an origin of an internal coordinate system for the bucket; and wherein when the X and Y values are connected by smooth continuing arcs, the Z-Notch profile is defined. A turbine is provided.

Abstract: A serpentine cooling circuit is formed in a gas turbine blade to cool portions of the tip shroud, primarily the fillet between the airfoil and the tip shroud and the shroud edges.

Abstract: A serpentine cooling circuit is formed in a gas turbine blade to cool portions of the tip shroud, primarily the fillet between the airfoil and the tip shroud and the shroud edges.

Abstract: A localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shroud.

Abstract: A turbine includes a turbine wheel having a plurality of buckets, each of the buckets including a bucket airfoil, a bucket dovetail to connect the bucket to a turbine wheel and a shank shape to connect the airfoil to the bucket dovetail, the shank having an uncoated nominal profile including a concave, pressure side, substantially in accordance with Cartesian values of X, Y and Z? set forth in Table I wherein the Z? values are non-dimensional values in a range from 0 to 1 convertible to Z distances in inches by multiplying the Z? values by shank height in inches, and a convex, suction side, substantially in accordance with Cartesian values of X, Y and Z? set forth in Table II wherein the Z? values are non-dimensional values in a range from 0 to 1 convertible to Z distances in inches by multiplying the Z? values by the shank height in inches.

Abstract: A turbine bucket including a bucket airfoil having a hollow tip shroud, the hollow tip shroud having a hollow core having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, in inches, wherein the shape of the core is defined by the cloud of points listed which are distributed around each surface of the shroud, and the complete hollow portion of the tip shroud could be constructed by defining smooth sheet surfaces through the listed points.

Abstract: In one embodiment, a turbine bucket includes: a tip shroud with a front edge and a following edge, the front edge and the following edge including a Z-Notch profile according to the Cartesian coordinate values of X, Y and Z set forth in Table I; wherein the coordinate values are dimensional values representing a distance from an origin of an internal coordinate system for the bucket; and wherein when the X and Y values are connected by smooth continuing arcs, the Z-Notch profile is defined. A turbine is provided.

Abstract: A method of assembling a rotor assembly is provided. The method includes coupling a first turbine bucket to a rotor disk wherein the first turbine bucket includes a first tip shroud including a first surface, providing a second turbine bucket that includes a second tip shroud including a second surface, and coupling the second turbine bucket to the rotor disk such that the second turbine bucket is circumferentially adjacent to the first turbine bucket and such that during operation of the rotor assembly the first tip shroud contacts the second tip shroud along the first and second surfaces to enable at least one of a portion of radial loading induced to the first tip shroud to be transferred to the second tip shroud and a portion of radial loading induced to the second tip shroud to be transferred to the first tip shroud.

Abstract: An investment casting process that enables directionally solidified tip shrouded turbine blades or buckets to have a continuous grain structure that extends through the tip shroud in addition to increasing the quantity of grains in the root of the part.

Abstract: A method for casting an airfoil for a turbine engine is provided. The method includes forming a casting core to define a hollow portion in the airfoil and forming a print out region at one end of the casting core. The method also includes coupling the casting core to the print out region with at least one frusto-conical member to facilitate structurally supporting the casting core.

Abstract: A turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, the shank portion having a forward shank wall and an aft shank wall; at least the aft shank wall convexly curved from one side of the bucket to an opposite side of the bucket.

Abstract: A turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, the shank portion having a forward shank wall and an aft shank wall; at least the aft shank wall convexly curved from one side of the bucket to an opposite side of the bucket.