7. A single-stage axial flow gas turbine has a mean radius of 30 cm. The hot gases
enter the turbine stage at 1900 kPa and 1200 K and the absolute velocity leaving
the stator ($C_2$) is 600 m/s making $65^\circ$ with the axial direction ($\alpha_2$). The rotor inlet
and outlet blade angles ($\beta_2$ and $\beta_3$) are $25^\circ$ and $60^\circ$, respectively. The mass flow
rate is 50 Kg/s. The stage efficiency is 0.88. Cp=1148 J/kg. K, $\gamma$= 1.333 Calculate:
a) Calculate the rotor rotational speed (rpm)
b) Calculate the stage total temp drop, K
c) Calculate the stage pressure ratio
d) Calculate the degree of reaction
