The combustion products of a gas turbine engine can be assumed to be a calorically perfect gas with $\gamma=1.2$. The pressure ratio across the turbine stage is 0.14 . The measured turbine inlet and exit stagnation temperatures are $1200 \mathrm{~K}$ and $900 \mathrm{~K}$, respectively. The total-tototal turbine efficiency is_______%(round off to the nearest integer)

The combustion products of a gas turbine engine can be assumed to be a calorically perfect gas with $\gamma=1.2$. The pressure ratio across the turbine stage is 0.14 . The measured turbine inlet and exit stagnation temperatures are $1200 \mathrm{~K}$ and $900 \mathrm{~K}$, respectively. The total-tototal turbine efficiency is_______%(round off to the nearest integer)

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