An environmental barrier coating system for a turbine component, including an environmental barrier layer applied to a turbine component substrate containing silicon; the environmental barrier layer comprising an oxide matrix surrounding a fiber-reinforcement structure and a self-healing phase interspersed throughout the oxide matrix; wherein the fiber-reinforcement structure comprises at least one first fiber bundle oriented along a load bearing stress direction of said turbine component substrate; wherein the fiber-reinforcement structure comprises at least one second fiber bundle oriented orthogonal to the at least one first fiber bundle orientation; wherein the fiber-reinforcement structure comprises at least one third fiber woven between the at least one first fiber bundle and the at least one second fiber bundle.

A composite production method includes impregnating a plate-shaped porous inorganic structure and a fibrous inorganic material with a metal while the fibrous inorganic material is arranged to be adjacent to the porous inorganic structure. In the composite structure, first and second phases are adjacent to each other by using a porous inorganic structure having a porous silicon carbide ceramic sintered body and the fibrous inorganic material, the first phase being a phase in which the porous silicon carbide ceramic sintered body is impregnated with the metal, the second phase being a phase in which the fibrous inorganic material is impregnated with the metal, a percentage of the porous silicon carbide ceramic sintered body in the first phase is 50 to 80 volume percent, and a percentage of the fibrous inorganic material in the second phase is 3 to 20 volume percent. A composite is produced by the method.

A composite production method includes impregnating a plate-shaped porous inorganic structure and a fibrous inorganic material with a metal while the fibrous inorganic material is arranged to be adjacent to the porous inorganic structure. In the composite structure, first and second phases are adjacent to each other by using a porous inorganic structure having a porous silicon carbide ceramic sintered body and the fibrous inorganic material, the first phase being a phase in which the porous silicon carbide ceramic sintered body is impregnated with the metal, the second phase being a phase in which the fibrous inorganic material is impregnated with the metal, a percentage of the porous silicon carbide ceramic sintered body in the first phase is 50 to 80 volume percent, and a percentage of the fibrous inorganic material in the second phase is 3 to 20 volume percent. A composite is produced by the method.

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.

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.

This method is suitable for the strengthening of concrete or timber structures (1, 4) by applying prestressed Carbon FRP or Glass FRP lamella (8). Firstly, at least one groove (22) is cut into the concrete or timber structure (1, 4) along the direction in which the concrete or timber structure (1, 4) is to be strengthened. The grooves (22) are filled with epoxy resin (9) and a layer of epoxy resin (9) is put onto the entire section to be equipped with the CRFP or GFRP lamella (8). The lamella (8) will be prestressed and anchored at both ends. U-shaped brackets (24) are then being put over the two end sections of the CFRP or GFRP lamella (8) by inserting and submerging its both U-legs (27) into holes (26) filled with resin as well. These holding brackets (24) will then tightly press onto the CFRP or GFRP lamella (8) to prevent cracking or fracture of the concrete or timber and bending away of the extremities of the CFRP or GFRP lamella.

A ceramic honeycomb body comprising a peripheral skin layer and a fiber extending around the outer periphery of a honeycomb core, the fiber embedded in the peripheral skin layer is described. A method of making a honeycomb body having a fiber extending around the outer periphery of a honeycomb core and embedded in the peripheral skin layer is also described.

A ceramic honeycomb body comprising a peripheral skin layer and a fiber extending around the outer periphery of a honeycomb core, the fiber embedded in the peripheral skin layer is described. A method of making a honeycomb body having a fiber extending around the outer periphery of a honeycomb core and embedded in the peripheral skin layer is also described.

An improved terrazzo process for applying terrazzo to an existing concrete surface comprising preparing the concrete surface, applying two layers of a primer agent, applying a terrazzo layer comprising calcium sulfoaluminate (CSA) cement, white milk glass, and one or more of broken mirrored glass and colored glass, cutting the terrazzo layer, applying a concrete densifier such that the concrete densifier penetrates into at least a portion of the concrete substrate, and grinding and polishing the densified terrazzo layer.

An improved terrazzo process for applying terrazzo to an existing concrete surface comprising preparing the concrete surface, applying two layers of a primer agent, applying a terrazzo layer comprising calcium sulfoaluminate (CSA) cement, white milk glass, and one or more of broken mirrored glass and colored glass, cutting the terrazzo layer, applying a concrete densifier such that the concrete densifier penetrates into at least a portion of the concrete substrate, and grinding and polishing the densified terrazzo layer.