For the radial-flow turbine described in the previous problem and operating at the prescribed "hot" design point condition, the gas leaves the exducer directly to the atmosphere at a pressure of 100 kPa and without swirl. The absolute flow angle at rotor inlet is 72°to the radial direction. The relative velocity w3 at the mean radius of the exducer (which is one-half of the rotor inlet radius r2) is twice the rotor inlet relative velocity w2. The nozzle enthalpy loss coefficient, ζN = 0.06. Assuming the gas has the properties of air with an average value of γ= 1.34 (this temperature range) and R = 287 J/kg K, determine
a. the total-to-static efficiency of the turbine;
b. the static temperature and pressure at the rotor inlet;
c. the axial width of the passage at inlet to the rotor;
d. the absolute velocity of the flow at exit from the exducer;
e. the rotor enthalpy loss coefficient;
f. the radii of the exducer exit given that the radius ratio at that location is 0.4.