7.1 A single-stage axial flow gas turbine has the following data: Inlet stagnation temperature The ratio of static pressure at the nozzle exit to the stagnation 1100K pressure at the nozzle inlet 0.53 Nozzle efficiency 0.93 Nozzle angle 20° Mean blade velocity 454 m/s Rotor efficiency 0.90 Degree of reaction 50% Cpg 1.147 kJ/kgK, y = 1.33 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%)