A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component includes a body and an outer region. The body includes a silicon containing ceramic composite. The outer region is on an outer surface of the body.

A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component includes a body and an outer region. The body includes a silicon containing ceramic composite. The outer region is on an outer surface of the body.

Embodiments of the present invention provide an osseointegrative implant and related tools, components and fabrication techniques for surgical bone fixation and dental restoration purposes. In one embodiment an all-ceramic single-stage threaded or press-fit implant is provided having finely detailed surface features formed by ceramic injection molding and/or spark plasma sintering of a powder compact or green body comprising finely powdered zirconia. In another embodiment a two-stage threaded implant is provided having an exterior shell or body formed substantially entirely of ceramic and/or CNT-reinforced ceramic composite material. The implant may include one or more frictionally anisotropic bone-engaging surfaces. In another embodiment a densely sintered ceramic implant is provided wherein, prior to sintering, the porous debound green body is exposed to ions and/or particles of silver, gold, titanium, zirconia, YSZ, ?-tricalcium phosphate, hydroxyapatite, carbon, carbon nanotubes, and/or other particles which remain lodged in the implant surface after sintering. Optionally, at least the supragingival portions of an all-ceramic implant are configured to have high translucence in the visible light range. Optionally, at least the bone-engaging portions of an all-ceramic implant are coated with a fused layer of titanium oxide.

Embodiments of the present invention provide an osseointegrative implant and related tools, components and fabrication techniques for surgical bone fixation and dental restoration purposes. In one embodiment an all-ceramic single-stage threaded or press-fit implant is provided having finely detailed surface features formed by ceramic injection molding and/or spark plasma sintering of a powder compact or green body comprising finely powdered zirconia. In another embodiment a two-stage threaded implant is provided having an exterior shell or body formed substantially entirely of ceramic and/or CNT-reinforced ceramic composite material. The implant may include one or more frictionally anisotropic bone-engaging surfaces. In another embodiment a densely sintered ceramic implant is provided wherein, prior to sintering, the porous debound green body is exposed to ions and/or particles of silver, gold, titanium, zirconia, YSZ, ?-tricalcium phosphate, hydroxyapatite, carbon, carbon nanotubes, and/or other particles which remain lodged in the implant surface after sintering. Optionally, at least the supragingival portions of an all-ceramic implant are configured to have high translucence in the visible light range. Optionally, at least the bone-engaging portions of an all-ceramic implant are coated with a fused layer of titanium oxide.

A graphite-metal carbide-rhenium article of manufacture is provided, which is suitable for use as a component in the hot zone of a rocket motor at operating temperatures in excess of approximately 3,000 degrees Celsius. One side of the metal carbide is chemically bonded to the surface of the graphite, and the rhenium containing protective coating is mechanically bonded to the other side of the metal carbide. Rhenium forms a solid solution with carbon at elevated temperatures. The metal carbide interlayer serves as a diffusion barrier to prevent carbon from migrating into contact with the rhenium containing protective coating. The metal carbide is formed by a conversion process wherein a refractory metal carbide former is allowed to react with carbon in the surface of the graphite. This structure is lighter and less expensive than corresponding solid rhenium components.

A graphite-metal carbide-rhenium article of manufacture is provided, which is suitable for use as a component in the hot zone of a rocket motor at operating temperatures in excess of approximately 3,000 degrees Celsius. One side of the metal carbide is chemically bonded to the surface of the graphite, and the rhenium containing protective coating is mechanically bonded to the other side of the metal carbide. Rhenium forms a solid solution with carbon at elevated temperatures. The metal carbide interlayer serves as a diffusion barrier to prevent carbon from migrating into contact with the rhenium containing protective coating. The metal carbide is formed by a conversion process wherein a refractory metal carbide former is allowed to react with carbon in the surface of the graphite. This structure is lighter and less expensive than corresponding solid rhenium components.

The present invention concerns a method for obtaining a finished or semi-finished zirconia-based article, the surface of the article having a metallic external appearance and non-zero surface electrical conductivity, wherein the method includes the steps of: taking at least one zirconia article, pre-shaped in its finished or semi-finished form; placing said article in a chamber in which a hydrogen and carbon/nitrogen gas mixture is heated; heating said article and the gas mixture using at least one resistive element traversed by an electric current to obtain dissociation of the hydrogen and carbon/nitrogen based gas molecules and an increase in the temperature of said article; keeping said article in the reactive atmosphere thus created to obtain diffusion of the carbon/nitrogen atoms in the external surface of said article.

The present invention concerns a method for obtaining a finished or semi-finished zirconia-based article, the surface of the article having a metallic external appearance and non-zero surface electrical conductivity, wherein the method includes the steps of: taking at least one zirconia article, pre-shaped in its finished or semi-finished form; placing said article in a chamber in which a hydrogen and carbon/nitrogen gas mixture is heated; heating said article and the gas mixture using at least one resistive element traversed by an electric current to obtain dissociation of the hydrogen and carbon/nitrogen based gas molecules and an increase in the temperature of said article; keeping said article in the reactive atmosphere thus created to obtain diffusion of the carbon/nitrogen atoms in the external surface of said article.

Disclosed is a method for producing a carbide derived carbon layer with a dimple pattern. The method includes forming a dimple pattern on the surface of a carbide ceramic material and forming a carbide derived carbon layer thereon. Also disclosed is a carbide derived carbon layer with a dimple pattern produced by the method. The carbide derived carbon layer with dimple pattern has high wear resistance, good adhesion to a machine part, and excellent frictional characteristics. The carbide derived carbon layer can be applied to various fields, such as coating of carbide coated and carbide materials. Particularly, the carbide derived carbon layer is suitable for coating of machine parts (e.g., sliding parts, mechanical seals, piston rings, and compressor vanes) where excellent mechanical properties are needed.

Disclosed is a method for producing a carbide derived carbon layer with a dimple pattern. The method includes forming a dimple pattern on the surface of a carbide ceramic material and forming a carbide derived carbon layer thereon. Also disclosed is a carbide derived carbon layer with a dimple pattern produced by the method. The carbide derived carbon layer with dimple pattern has high wear resistance, good adhesion to a machine part, and excellent frictional characteristics. The carbide derived carbon layer can be applied to various fields, such as coating of carbide coated and carbide materials. Particularly, the carbide derived carbon layer is suitable for coating of machine parts (e.g., sliding parts, mechanical seals, piston rings, and compressor vanes) where excellent mechanical properties are needed.