Question: Problem: A single - stage gas turbine operates at its design condition with an axial absolute flow at entry and exit from the stage. At

Problem: A single-stage gas turbine operates at its design condition with an axial
absolute flow at entry and exit from the stage. At stage entry, the stagnation pressure
and temperature are 311 kPa and 1123 K respectively. The absolute flow angle at
nozzle exit is 70. The exhaust static pressure is 100 kPa . The total-to-static efficiency
is 0.87, and the mean blade speed is
Problem: A single - stage gas turbine operates at

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