# Combustion gases with ? = 4/3 and cp = 1148 kJ/(kg K) flow through a turbine. The inlet stagnation..

Combustion gases with ? = 4/3 and cp = 1148 kJ/(kg K) flow through a turbine. The inlet stagnation temperature is T01 = 1400 K, and stagnation pressure is p01 = 1100 kPa. Blade speed is U = 300 m/s, and the blade height to axial chord ratio is b/cx = 3.5. The axial velocity is not constant, and the flow coefficients for the stator is f 2 = V x2 /U = 0.50. For the rotor it is f 3 = V x3 /U = 0.56. The absolute velocity enters the rotor at the angle a 2 = 68?, and the relative velocity leaves it at angle _3 = -65?. Assuming that Re = 105 and using the Soderberg correlations to establish the

Combustion gases with ? = 4/3 and cp = 1148 kJ/(kg K) flow through a turbine. The inlet stagnation temperature is T01 = 1400 K, and stagnation pressure is p01 = 1100 kPa. Blade speed is U = 300 m/s, and the blade height to axial chord ratio is b/cx = 3.5. The axial velocity is not constant, and the flow coefficients for the stator is f 2 = V x2 /U = 0.50. For the rotor it is f 3 = V x3 /U = 0.56. The absolute velocity enters the rotor at the angle a 2 = 68?, and the relative velocity leaves it at angle _3 = -65?. Assuming that Re = 105 and using the Soderberg correlations to establish the loss coefficients, find the areas entering the rotor and leaving the rotor

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