At the inlet of the nozzle of an axial gas turbine, the total pressure and total temperature are 6 bar and 750 K, respectively. At the nozzle outlet, the static pressure is 3.4 bar and the absolute flow angle is 65°. If the rotor angles and velocities are identical to those of the nozzle (i.e. 50% blading), if both blades have an efficiency of 85%, and if the absolute rotor exit flow is purely axial, calculate the static pressure at the rotor's exit. [1.96 bar]

At the inlet of the nozzle of an axial gas turbine, the total pressure and total temperature are 6 bar and 750 K, respectively. At the nozzle outlet, the static pressure is 3.4 bar and the absolute flow angle is 65°. If the rotor angles and velocities are identical to those of the nozzle (i.e. 50% blading), if both blades have an efficiency of 85%, and if the absolute rotor exit flow is purely axial, calculate the static pressure at the rotor's exit. [1.96 bar]