An axial turbine stage has an inlet temperature of 1400 K. At mid-radius, while operating at design speed and flow rate, the axial velocity ratio ca / U is 0.5, the degree of reaction is 50%, and there is no swirl in the absolute velocity leaving the rotor. The tip blade speed is 400 m/s, and the hub-to-tip radius ratio is 0.8. (a) Estimate the stagnation pressure ratio for the stage. (b) If, during off-design operation, the inlet flow conditions are unchanged but the blade speed increases 20%, show how the change i