Abstract: A method for producing a component layer-by-layer include the steps of: depositing a layer of particulate material having a first area over a build platform; applying a radiant-energy-curable binder to the layer so that a selected portion of the first area is uniformly coated with binder; selectively curing a second area of the layer smaller than the selected portion of first area, using an application of radiant energy in a specific pattern that defines the geometry of a cross-sectional layer of the component; and repeating the steps of depositing, applying, and curing for a plurality of layers until the component is complete.

Abstract: A turbine component assembly is disclosed, including a first component, a second component, and an interface shield. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The interface shield is disposed on a contact region of the first component, and directly contacts the second component.

Abstract: A shroud dampening pin is disclosed including a shaft, a dampening portion at a first end of the shaft, and a cap at a second end of the shaft. The dampening portion includes a bevel having a bevel angle and a contact surface. A turbine shroud assembly is disclosed, including an inner shroud, an outer shroud, the shroud dampening pin, and a biasing apparatus. The outer shroud includes a channel extending from an aperture adjacent to the inner shroud at a channel angle from the aperture. The shroud dampening pin is disposed within the channel. The dampening portion extends through the aperture with the contact surface contacting the inner shroud. The biasing apparatus contacts the cap and provides a biasing force to the inner shroud through the contact surface. The bevel angle is about the same as the channel angle, and the contact surface is about parallel to the aperture.

Abstract: A process for producing an internal cavity in a CMC article and mandrels used therewith. The process entails incorporating a mandrel made of a material that is substantially absorbed during thermal treatment of a preform to form the CMC article. The mandrel material is preferably reactive with one or more constituents of the CMC preform during the thermal treatment. The material is preferably silicon or a silicon alloy.

Abstract: A method for producing a component layer-by-layer include the steps of: depositing a layer of particulate material having a first area over a build platform; applying a radiant-energy-curable binder to the layer so that a selected portion of the first area is uniformly coated with binder; selectively curing a second area of the layer smaller than the selected portion of first area, using an application of radiant energy in a specific pattern that defines the geometry of a cross-sectional layer of the component; and repeating the steps of depositing, applying, and curing for a plurality of layers until the component is complete.

Abstract: A turbine component assembly is disclosed, including a first component, a second component, and an interface shield. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The interface shield is disposed on a contact region of the first component, and directly contacts the second component.

Abstract: A shroud dampening pin is disclosed including a shaft, a dampening portion at a first end of the shaft, and a cap at a second end of the shaft. The dampening portion includes a bevel having a bevel angle and a contact surface. A turbine shroud assembly is disclosed, including an inner shroud, an outer shroud, the shroud dampening pin, and a biasing apparatus. The outer shroud includes a channel extending from an aperture adjacent to the inner shroud at a channel angle from the aperture. The shroud dampening pin is disposed within the channel. The dampening portion extends through the aperture with the contact surface contacting the inner shroud. The biasing apparatus contacts the cap and provides a biasing force to the inner shroud through the contact surface. The bevel angle is about the same as the channel angle, and the contact surface is about parallel to the aperture.

Abstract: A process for producing an internal cavity in a CMC article and mandrels used therewith. The process entails incorporating a mandrel made of a fusible material that is melted and drained during a thermal treatment of a CMC preform to form the CMC article. The mandrel material is preferably non-wetting and non-reactive with any constituents of the CMC preform during the thermal treatment. The mandrel is preferably tin or an alloy of tin.

Abstract: Matrix composite component repair processes are disclosed. The matrix composite repair process includes applying a repair material to a matrix composite component, securing the repair material to the matrix composite component with an external securing mechanism and curing the repair material to bond the repair material to the matrix composite component during the securing by the external securing mechanism. The matrix composite component is selected from the group consisting of a ceramic matrix composite, a polymer matrix composite, and a metal matrix composite. In another embodiment, the repair process includes applying a partially-cured repair material to a matrix composite component, and curing the repair material to bond the repair material to the matrix composite component, an external securing mechanism securing the repair material throughout a curing period, In another embodiment, the external securing mechanism is consumed or decomposed during the repair process.

Abstract: A gas turbine blade may have a bond coat applied to its surface. A porous substrate may be applied to the bond layer and one or more protective layers may be applied to the bond layer such that the fiber mesh is embedded between the bond layer and the protective layer to prevent creep.

Abstract: A casing for a turbo-machine at least partially defines a flow path for a working fluid through or around one or more of a compressor section, a combustor assembly, or a turbine section. The casing defines an inner surface and the inner surface defines a plurality of debris routing channels. The plurality of debris routing channels are configured to route debris in a working fluid within the casing towards a debris collection mechanism.

Abstract: A turbomachine component includes a body having an exterior surface and an interior surface, an internal cavity defined by the interior surface, and a reactivity neutralizing member arranged within the internal cavity. The reactivity neutralizing member is configured and disposed to neutralize turbomachine combustion products on the interior surface of the body.

Abstract: A bond layer may be applied to the substrate of an article and a first layer may be applied to the bond layer by thermal spray. A second layer may be applied above the first layer by slurry coating.

Abstract: A gear set may include a gear having improved operating performance by including location specific strength and wear properties, more specifically the gear may include a hub that may be made from a first material and a plurality of gear teeth that may be made from a second material and mounted to the hub.

Abstract: A casing for a turbo-machine at least partially defines a flow path for a working fluid through or around one or more of a compressor section, a combustor assembly, or a turbine section. The casing defines an inner surface and the inner surface defines a plurality of debris routing channels. The plurality of debris routing channels are configured to route debris in a working fluid within the casing towards a debris collection mechanism.

Abstract: A method of making a composite sheet, a method of making composite component and a composite component are provided. The method of making a composite sheet includes providing a container, adding a binder to the container, adding a plurality of randomly oriented fibers to the binder in the container, and subjecting the container to motion to coat the plurality of randomly oriented fibers with the binder. The method includes curing the binder and coated plurality of randomly oriented fibers to form a composite sheet. The plurality of randomly oriented fibers of the composite sheet are interlocked within the binder. The composite has uniform strength in all planar directions.

Abstract: A turbine bucket assembly and turbine system are disclosed. The turbine bucket assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a non-segmented airfoil having a root section and a tip section integral with the root section, the tip section having a tip end with a second axial length, the second axial length being less than the first axial length; and a turbine wheel having a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The turbine wheel includes a turbine wheel material and the single-lobe joint and the non-segmented airfoil include a turbine bucket material, the turbine bucket material having a higher heat resistance and a lower thermal expansion than the turbine wheel material.

Abstract: A system for damping vibrations in a turbine includes a first rotating blade having a first ceramic airfoil, a first ceramic platform connected to the first ceramic airfoil, and a first root connected to the first ceramic platform. A second rotating blade adjacent to the first rotating blade includes a second ceramic airfoil, a second ceramic platform connected to the second ceramic airfoil, and a second root connected to the second ceramic platform. A non-metallic platform damper has a first position in simultaneous contact with the first and second ceramic platforms.

Abstract: A method for adhering a coating to a substrate structure comprises selecting a substrate structure having an outer surface oriented substantially parallel to a direction of radial stress, modifying the outer surface to provide a textured region having steps to adhere a coating thereto, and applying a coating to extend over at least a portion of the textured region, wherein the steps are oriented substantially perpendicular to the direction of radial stress to resist deformation of the coating relative to the substrate structure. A rotating component comprises a substrate structure having an outer surface oriented substantially parallel to a direction of radial stress. The outer surface defines a textured region having steps to adhere a coating thereto, and a coating extends over at least a portion of the textured region. The steps are oriented substantially perpendicular to the direction of radial stress to resist creep.

Abstract: A process of forming a material having nano-particles and a material having nano-particles are disclosed. The process includes arranging nano-particles in a predetermined pattern within a matrix material. The material includes arranged nano-particles forming a predetermined pattern in the matrix material.