Abstract: A medical device includes a substrate structure with a surface. The surface is laser treated to define at least one protrusion and/or at least one void extending relative to the surface. A coating having antibacterial, antimicrobial and/or drug eluding properties is applied to the substrate structure such that the coating engages within or along a surface portion of one or more of the protrusions and/or voids.

Abstract: A disclosed method of forming a ceramic article includes forming a pre-ceramic polymer article within a mold tool, and performing a first pyrolizing step on the initial pre-ceramic polymer article to form a ceramic article. The method further includes performing at least one pre-heat treatment polymer infiltration and pyrolizing (PIP) cycle on the ceramic article and an initial heat treatment cycle of the ceramic article after the at least one pre-heat treatment PIP cycle. Subsequent PIP cycles and heat treatment cycles are performed in combination to form a ceramic article including a desired density.

Abstract: The present invention provides a thin film coating comprising a metal oxide material, wherein the metal oxide material comprises Ir and metals M and M?, wherein M and M? are the same or different and are Ru, Rh, Pd, Os or Pt.

Abstract: A method of providing a self-healing coating includes providing substrate, applying a layer of an aluminum-containing MAX phase material and another material to the substrate. The method includes exposing the layer to a temperature greater than 2000° F. to form alpha aluminum.

Abstract: A method of manufacturing a gas turbine engine air seal comprising forming at least one MAX phase particle. The method includes coating the at least one MAX phase particle with a metallic shell. The method includes applying the at least one MAX phase metallic coated particle to a surface of a substrate of the air seal to form an abradable layer of a MAXMET composite abradable material from the at least on MAX phase metallic coated particle.

Abstract: An article includes a MAX phase solid and a high temperature melting point metallic material interdispersed with the MAX phase material.

Abstract: A method of fabricating a ceramic article includes providing a porous body that includes a plurality of fiber bundles that has an intra-bundle porosity and an inter-bundle porosity, infiltrating the intra-bundle porosity and the inter-bundle porosity with a mixture of particles in a liquid carrier, the particles having an average size selected with respect to at least the intra-bundle porosity, removing the liquid carrier from the porous body to deposit the particles in the intra-bundle porosity and in the inter-bundle porosity, infiltrating a preceramic polymer into a remaining intra-bundle porosity and a remaining inter-bundle porosity, and thermally converting the preceramic polymer to a ceramic material.

Abstract: A vibration resistant fan guide vane for a gas turbine engine is provided. The fan guide vane comprises a vibration damping component made of a MAXMET composite. The damping component may be a cover that covers some or all of the fan guide vane body. Alternatively, portions of the fan guide vane body or the entire vane body may be made from MAXMET composites. The disclosure makes use of the ultrahigh, fully reversible, non-linear elastic hysteresis behavior that MAXMET composites exhibit during cyclic elastic deformation in order to damp vibration.

Abstract: A method of providing a self-healing coating includes providing substrate, applying a layer of an aluminum-containing MAX phase material and another material to the substrate. The method includes exposing the layer to a temperature greater than 2000° F. to form alpha aluminum.

Abstract: A gas turbine engine includes a plurality of circumferentially-spaced blades. The blades have a polymeric coating thereon. An abradable seal circumscribes the blades and includes a polymeric matrix with a dispersion of a nanolayer material.

Abstract: A method of manufacturing a gas turbine engine air seal comprising forming at least one MAX phase particle. The method includes coating the at least one MAX phase particle with a metallic shell. The method includes applying the at least one MAX phase metallic coated particle to a surface of a substrate of the air seal to form an abradable layer of a MAXMET composite abradable material from the at least on MAX phase metallic coated particle.

Abstract: A vibration resistant fan guide vane for a gas turbine engine is provided. The fan guide vane comprises a vibration damping component made of a MAXMET composite. The damping component may be a cover that covers some or all of the fan guide vane body. Alternatively, portions of the fan guide vane body or the entire vane body may be made from MAXMET composites. The disclosure makes use of the ultrahigh, fully reversible, non-linear elastic hysteresis behavior that MAXMET composites exhibit during cyclic elastic deformation in order to damp vibration.

Abstract: A method of manufacturing a gas turbine engine air seal comprising forming at least one MAX phase particle. The method includes coating the at least one MAX phase particle with a metallic shell. The method includes applying the at least one MAX phase metallic coated particle to a surface of a substrate of the air seal to form an abradable layer of a MAXMET composite abradable material from the at least on MAX phase metallic coated particle.

Abstract: A component for high temperature applications includes a substrate and a layer of an aluminum-containing MAX phase material and another material applied to the substrate.

Abstract: A vibration resistant fan guide vane for a gas turbine engine is provided. The fan guide vane comprises a vibration damping component made of a MAXMET composite. The damping component may be a cover that covers some or all of the fan guide vane body. Alternatively, portions of the fan guide vane body or the entire vane body may be made from MAXMET composites. The disclosure makes use of the ultrahigh, fully reversible, non-linear elastic hysteresis behavior that MAXMET composites exhibit during cyclic elastic deformation in order to damp vibration.

Abstract: A method of fabricating a ceramic article includes providing a porous body that includes a plurality of fiber bundles that has an intra-bundle porosity and an inter-bundle porosity, infiltrating the intra-bundle porosity and the inter-bundle porosity with a mixture of particles in a liquid carrier, the particles having an average size selected with respect to at least the intra-bundle porosity, removing the liquid carrier from the porous body to deposit the particles in the intra-bundle porosity and in the inter-bundle porosity, infiltrating a preceramic polymer into a remaining intra-bundle porosity and a remaining inter-bundle porosity, and thermally converting the preceramic polymer to a ceramic material.

Abstract: A turbine engine system comprising a turbine engine component, such as a fan includes a fan casing and a fan blade rotatable within the fan casing. An abradable seal coupled to the fan casing proximate the fan blade. The abradable seal comprising an abradable composite layer including a MAX phase solid and a polymer based abradable composition.

Abstract: A process of forming a MAXMET composite coating or component on an article, that in the case of components can be removed, comprising providing an article having a substrate. The process includes providing at least one powder containing the MAXMET composite, wherein the MAXMET composite comprises a mixture of MAX phase particles and metal. Cold spraying the at least one powder on the substrate at a critical velocity. Forming a layer of the MAXMET composite on the substrate.

Abstract: A method of fabricating a ceramic article includes providing a porous body that includes a plurality of fiber bundles that has an intra-bundle porosity and an inter-bundle porosity, infiltrating the intra-bundle porosity and the inter-bundle porosity with a mixture of particles in a liquid carrier, the particles having an average size selected with respect to at least the intra-bundle porosity, removing the liquid carrier from the porous body to deposit the particles in the intra-bundle porosity and in the inter-bundle porosity, infiltrating a preceramic polymer into a remaining intra-bundle porosity and a remaining inter-bundle porosity, and thermally converting the preceramic polymer to a ceramic material.

Abstract: A turbine engine system comprising a turbine engine air seal having at least one contact portion. The turbine engine air seal having a MAXMET composite bonded to at least one contact portion.