Multi-phase ceramic matrix composite

A CMC jet engine component having a matrix with a carbide matrix phase and an oxide matrix phase, prepared by a process comprising:

• (a) preparing a CMC preform containing fiber tows;
• (b) infiltrating the CMC preform with a carbide matrix phase by chemical vapor infiltration (CVI);
• (c) depositing one or more metal oxide layer(s) on surfaces of the CMC preform with carbide matrix phase by atomic layer deposition (ALD);
• (d) subjecting the CMC preform with carbide matrix and metal oxide layer(s) to slurry infiltration using a slurry containing alumina powder, mullite powder, alkaline alumina silicate powder, and/or rare earth silicate powder, and optionally SiC powder as a filler, wherein the powders fill void spaces within the infiltrated preform, and heating the slurry infiltrated CMC preform to melt the powders and obtain a ceramic matrix composite having matrix that has an carbide matrix phase and an oxide matrix phase;
• (e) introducing molten oxide into the slurry infiltrated CMC preform by melt infiltration;
• and
• (f) subjecting the melt infiltrated CMC preform to one or more heat treatments to react the molten oxide and powder(s) to form a crystalline oxide matrix phase and obtain a ceramic matrix composite having matrix that has a carbide matrix phase and an oxide matrix phase.