A single-stage axial flow gas turbine has the following data: Inlet stagnation temperature 1100K The...

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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%) 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%)