Combustion gases enter the inlet of a rotor in a single-stage axial-flow turbine at the absolute velocity of 610 m/s. Their direction is 61? as measured from the cascade front in the direction of the...

Combustion gases enter the inlet of a rotor in a single-stage axial-flow turbine at the absolute velocity of 610 m/s. Their direction is 61? as measured from the cascade front in the direction of the blade motion. The values ? = 4/3 and cp = 1148 kJ/(kg K) are suitable for these gases. At exit of this rotor, the absolute velocity of the fluid is 305 m/s directed such that its tangential component is negative. The axial velocity is constant, the blade speed is 305 m/s, and the flow rate through the rotor is 5 kg/s. (a) Construct the rotor inlet and exit velocity diagrams showing the axial and tangential components of the absolute and relative velocities, as well as the flow angles. (b) Evaluate the change in total enthalpy across the rotor. (c) Evaluate the power delivered by the rotor. (d) Evaluate the average driving force exerted on the blades. (e) Evaluate the change in static and stagnation temperature of the fluid across the rotor. (f) Calculate the flow coefficient and the blade-loading coefficient. Are they reasonable?