For questions 1 through 7, consider the first stage (that is stator row followed by rotor row) of a gas turbine, where stagnation temperature and pressure at the inlet to the stage 1 stator row (S1) are Too = 1800 K and Poo = 2500 kPa, respectively. Use 1.3 for the value of the ratio of specific heat at constant pressure to that at constant volume. The following table gives mean-line values for (a) rotor linear speed, and (b) various flow velocity components. The rotor is rotating at 3600 RPM. Assume no losses, and that the axial component of flow velocity is held constant from stator inlet to rotor exit. Rotor Rotor Inlet Exit U m/s 400 Cz m/s 400.0 400.0 C_theta m/s 550.0 ?? W_theta m/s ?? -150.0