NOVELTY - The method involves filling a cavity located in an article i.e. turbine airfoil (24), with ceramic paste, where the ceramic paste comprises ceramic powder, an optionally ceramic fiber and a binder. The ceramic paste is heated in the cavity to remove the binder for forming porous ceramic material. Molten ceramic material is added to the porous ceramic material at temperature of about 1000 to about 2000 degree Celsius, where the porous ceramic material is heated to about 100 degree Celsius or higher to remove the binder. The optionally ceramic fiber is coated with particles.    USE - Method for repairing damage to an article e.g. ceramic-based tip or cap of gas turbine airfoil (claimed), constructed from ceramic matrix composite (CMC) material e.g. continuous fiber reinforced CMC material such as CMC materials reinforced with continuous carbon fibers, oxide fibers and silicon carbide monofilament fibers, and discontinuous fiber reinforced CMC materials, for extending working life of the airfoil in retrofit applications. Uses include but are not limited to particulate, platelet, whisker, discontinuous fiber and nano-composite reinforced CMC materials or mixtures.    ADVANTAGE - The method enables forming the airfoil by using CMC materials to generally exhibit enhanced high-temperature capabilities, so that the airfoil can reduce or eliminate the need for supplying a cooling medium e.g. air, to and/or through a tip or cap, thus increasing efficiency of a gas turbine. The method enables significantly reducing weight of the tip or cap compared to metal-based tips or caps due to low-densities of the CMC materials, thus reducing loads generated by the tip or cap during operation of the gas turbine. The method enables filling the cavity with the CMC material so as to repair and refurbish the turbine airfoil. The method enables providing the CMC material with reinforcing material to be incorporated so as to enhance material properties e.g. material strength and/or thermo-physical properties.    DETAILED DESCRIPTION - The cavity is formed as a hollow space, an opening, a crack, a gap, an aperture or a hole, within the turbine airfoil. The binder is formed as epoxy binder, polymeric binder, adhesive e.g. glue, or made of silicon dioxide, alumina oxide, carbon and boron. An INDEPENDENT CLAIM is also included for an intermediate formed during repair of a gas turbine airfoil.    DESCRIPTION OF DRAWING(S) - The drawing shows a schematic view of a gas turbine.    Gas turbine (10)    Compressor section (12)    Combustor section (14)    Shaft (18)    Turbine airfoil (24)