Aerospace Engineering > GATE 2019 > Turbine Efficiency
The combustion products of a gas turbine engine can be assumed to be a calorically perfect gas with γ = 1.2. The pressure ratio across the turbine stage is 0.14. The measured turbine inlet and exit stagnation temperatures are 1200 K and 900 K, respectively. The total-to-total turbine efficiency is _______ % (round off to the nearest integer).
Correct : 88 to 90
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