A single-stage axial flow gas turbine has the following data: Inlet stagnation temperature 1100K The ratio of static pressure at the nozzle exit to the stagnation pressure at the nozzle inlet 0.53 Nozzle efficiency 0.93 Nozzle angle 208 Mean blade velocity 454m/s Rotor efficiency 0.90 Degree of reaction 50% Take, y = 1.33, and Cp = 1147 J/kgK Find (1) the work output per kg/s of air flow, (2) the ratio of the static pressure at the rotor exit to the stagnation pressure at the nozzle inlet, and (3) the total-to- total stage efficiency. (282 kW, 0.214, 83.78%)