An integrated creep rupture strength degradation and water vapor degradation model for gas turbine oxide-based ceramic matrix composite (CMC) combustor liners was expanded with heat transfer computations to establish the maximum turbine rotor inlet temperature (TRIT) for gas turbines with 10:1 pressure ratio. Recession rates and average CMC operating temperatures were calculated for an existing baseline N720IA (N720/Al2Oj) CMC combustor liner system with and without protective AI2O3 friable graded insulation (FGl) for 30,000-h liner service life. The potential for increasing TRIT by Y3Al¡Oi2 (YAG) substitution for the fiber, matrix, and FGl constituents of the CMC system was explored, because of the known superior creep and water vapor degradation resistance of YAG compared to AI2O3. It was predicted that uncoated N720IA can be used as a combustor liner material up to a TRIT of ^1200 °C, offering no TRIT advantage over a conventional metal + thermal barrier coating (TBC) combustor liner. A similar conclusion was previously reached for a SiC/SiC CMC liner with barium strontium aluminum silicate (