Question: air enters the compressor of a gas turbine cycle at...
Air enters the compressor of a gas turbine cycle at 300 K, 1 atm. The pressure ratio of the cycle is 10, and both the compressor and the turbine have isentropic efficiencies of 0.8. The pressure across the combustor is constant, and the air leaves the combustor at 1200 K. Calculate the actual temperature at each point in the cycle, the net work per unit mass, and the cycle thermal efficiency.
Work this problem out two ways: 1) assuming constant specific heats for the air, and 2) using the air tables.