Abstract: Composition containing a MCrAlY, wherein M is selected from the group consisting of cobalt (Co), nickel (Ni), iron (Fe) and mixtures thereof, and germanium in an amount of about 10% by weight or less of germanium. Coated articles coated with the composition are also provided.

Abstract: Improved methods and containers for forming billets using hot isostatic pressing are provided. The methods and containers have features that control the deformations of the container during the high temperatures and pressures experienced in such processing so that the loss or removal of material from the resulting billet can be optimized.

Abstract: A fiber brush seal attached with metallic structure, suitable for use with SiC-SiC ceramic matrix composite (CMC) components. The fibers may be selected from oxides, carbides and nitrides of silicon, tungsten, chromium, iron, titanium, boron, zirconium and aluminum, and may optionally be coated with a boron nitride based coating.

Abstract: A fuel injector for injecting fuel into a gasifier includes a mating end including a nozzle portion and a first flange fixedly coupled to the mating end and having a first receiving hole there through and including a first diaphragm disposed therein. The injector also includes a fuel transmission nozzle displaced at least partially within the mating end and passing through the first receiving hole arranged and configured such that a secondary oxygen channel exists between the fuel transmission nozzle and the mating end, the fuel transmission nozzle being fixedly coupled to the first diaphragm and further including a fuel inlet for receiving fuel for introduction into the gasifier.

Abstract: Embodiments of methods and apparatus for providing a sacrificial shield for a fuel injector are provided. According to one example embodiment, a method for shielding a fuel injector associated with a combustion device is provided. The method can include providing at least one shield support device operable to mount to a tip of a fuel injector. The method can also include mounting a plurality of shields to the at least one support device, wherein each of the plurality of shields is spaced apart from each respective adjacent shield by at least one segmentation, and wherein each of the plurality of shields is operable to reduce heat exposure to the tip of the fuel injector.

Abstract: Embodiments disclosed herein provide hydrocarbon additives and methods of making and using the same. The additives are suitable for use in conjunction with gasifiers, furnaces, or other high-temperature vessels. The additives may be part of an input stream to a reaction vessel of a hydrocarbon gasifier. The additives may include materials that at least partially reduce the infiltration of slag into the refractory material.

Abstract: A feed injector for providing feed to a gasifier of an integrated gasification combined cycle system includes: a base leading to a body and terminating in a tip, the tip including an exitway for injecting feed into the gasifier; the tip including a mating of an inner shell disposed within a core insert, with an outer shell in which the core insert is disposed; a plurality of spacers disposed between the core insert and inner shell thus providing an inner annular space, and another plurality of spacers disposed between the core insert and outer shell thus providing an outer annular space; the inner annular space and the outer annular space being in fluid communication at the tip and providing for a flow of coolant from the base to the tip and back to the base. A method of fabrication and an integrated gasification combined cycle power plant are also disclosed.

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 method for tracking rotation of a turbomachine component including locating at least one tilt sensor at the turbomachine component and rotating the turbomachine component about a central axis to observe a portion of interest on the turbomachine component. The at least one tilt sensor detects an angle of rotation of the turbomachine component and transmits the angle of rotation from the at least one tilt sensor to a device which converts the angle of rotation to an indicia of the portion of interest. Further disclosed is a rotor including at least one tilt sensor and a system for tracking rotation of a turbomachine component including at least one tilt sensor and a device.

Abstract: A method of assembling a rotor shaft assembly is provided. The method includes assembling a self-aligning bearing seat from a first assembly and a second assembly such that the self-aligning bearing seat substantially circumscribes a rotor shaft. The method also includes creating an interface defined between the first assembly and the second assembly, such that when the rotor shaft experiences misalignment the interface accommodates misalignment of the rotor shaft.

Abstract: Systems and methods for cooling heated components in a turbine are provided. According to one embodiment, a system for cooling a turbine is provided that may include at least one liquid source which may include a coolant liquid. The system may also include at least one liquid nozzle in fluid communication with the liquid source or sources and operable to deliver the coolant liquid in an atomized form adjacent to at least one heated turbine component positioned in a hot gas path of the turbine. Upon delivering the atomized coolant liquid adjacent to the heated turbine component or components, at least a portion of the coolant liquid substantially changes phase to a gas.

Abstract: A method for repairing a hub pitch gear assembly. The method includes providing a ring assembly for adjusting a pitch angle of a wind turbine blade having a plurality of gear teeth. A segment of the ring assembly is removed, the segment including at least a portion of at least one gear tooth, to form a repair cavity. A repair segment configured to mate the repair cavity is provided and the repair segment is directed into the repair cavity and fastened in position. A repaired pitch gear assembly and wind turbine are also disclosed.

Abstract: A disk rotor comprises a hub having a bore, and a plurality of spoke segments radially extending from the hub, each spoke segment including a base portion being attached to the hub and a rim portion, wherein the rim portion includes one or more airfoils integrally formed thereon, the plurality of spoke segments collectively forming a ring.

Abstract: A method for assembling a nozzle is provided. The method includes providing an injection tube that includes an outlet that is configured to discharge fuel therefrom. A face plate is also provided that extends about the injection tube such that the face plate substantially circumscribes the outlet. A cooling chamber is defined within the injection tube and configured to channel cooling fluid adjacent to the face plate. At least one surface defining the cooling chamber is configured to disrupt a flow of the cooling fluid flowing through the cooling chamber.

Abstract: Disclosed herein are methods for coating metal substrates, systems therefore, and articles made therefrom. In one embodiment, the method of coating a metal substrate comprises: disposing a metallic bond coating on the metal substrate, creating ions with a reverse polarity high frequency apparatus at a frequency of greater than or equal to about 2.5 kHz, roughening the surface with the ions to a subsequent average surface roughness of greater than or equal to about 5 ?m, and disposing a ceramic coating on the metallic bond coating surface. The metallic bond coating had a surface with an initial average surface roughness of less than or equal to about 1 ?m.

Abstract: A method of assembling a rotor shaft assembly is provided. The method includes assembling a self-aligning bearing seat from a first assembly and a second assembly such that the self-aligning bearing seat substantially circumscribes a rotor shaft. The method also includes creating an interface defined between the first assembly and the second assembly, such that when the rotor shaft experiences misalignment the interface accommodates misalignment of the rotor shaft.

Abstract: A silicon carbide fiber brush seal, suitable for use with SiC—SiC CMC components. The seal may be coated with a boron nitride based coating.

Abstract: Methods and apparatus for assembling a wind turbine generator are provided. The wind turbine generator includes a core and a plurality of stator windings circumferentially spaced about a generator longitudinal axis, a rotor rotatable about the generator longitudinal axis wherein the rotor includes a plurality of magnetic elements coupled to a radially outer periphery of the rotor such that an airgap is defined between the stator windings and the magnetic elements and the plurality of magnetic elements including a radially inner periphery having a first diameter. The wind turbine generator also includes a bearing including a first member in rotatable engagement with a radially inner second member, the first member including a radially outer periphery, a diameter of the radially outer periphery of the first member being substantially equal to the first diameter, the rotor coupled to the stator through the bearing such that a substantially uniform airgap is maintained.

Abstract: An assembly that includes a CMC article, and a method of forming the assembly, so as to reduce the likelihood during a transient thermal condition of the CMC article becoming interlocked with the worn shank of a fastener used to secure the article to its support structure. The CMC article has oppositely-disposed first and second surfaces, a hole through the article and intersecting the first and second surfaces so as to define oppositely-disposed first and second openings at the first and second surfaces, respectively, and continuous chamfers along the entirety of the first and second openings. The assembly further includes a support structure adjacent the article, and a fastener received in the hole of the CMC article and securing the CMC article to the support structure. The location of the chamfers at the perimeter of each opening eliminates a relatively sharp edge that could interlock with the worn shank of the fastener during a thermal excursion.

Abstract: An assembly that includes a CMC article, and a method of forming the assembly, so as to reduce the likelihood during a transient thermal condition of the CMC article becoming interlocked with the worn shank of a fastener used to secure the article to its support structure. The CMC article has oppositely-disposed first and second surfaces, a hole through the article and intersecting the first and second surfaces so as to define oppositely-disposed first and second openings at the first and second surfaces, respectively, and continuous chamfers along the entirety of the first and second openings. The assembly further includes a support structure adjacent the article, and a fastener received in the hole of the CMC article and securing the CMC article to the support structure. The location of the chamfers at the perimeter of each opening eliminates a relatively sharp edge that could interlock with the worn shank of the fastener during a thermal excursion.