The gas generator of a two-shaft gas turbine has a compressor pressure ratio of 5 and compressor and turbine inlet temperatures of 80°F and 2000°F, respectively, at sea level. All turbomachines have efficiencies of 90%, and the inlet air flow is 50 lbm/s. (a) What are the net work, pressure ratio, and horsepower of the power turbine and the cycle efficiency? (b) Suppose the power turbine is removed and the gas generator exhaust gas flows isentropically through a convergent-divergent propulsion nozzle that is fully expanded (exit pressure is ambient). What are the nozzle exhaust velocity and the static thrust? (c) Repeat part (b) for a choked convergent nozzle.