Determine the total-to-static efficiency of the turbine

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Reference no: EM131057170

A radial turbine is proposed as the gas expansion element of a nuclear powered Brayton cycle space power system. The pressure and temperature conditions through the stage at the design point are to be as follows:

The ratio of rotor exit mean diameter to rotor inlet tip diameter is chosen as 0.49 and the required rotational speed as 24,000 rev/min. Assuming the relative flow at rotor inlet is radial and the absolute flow at rotor exit is axial, determine

a. the total-to-static efficiency of the turbine;

b. the rotor diameter;

c. the implied enthalpy loss coefficients for the nozzles and rotor row. The gas employed in this cycle is a mixture of helium and xenon with a molecular weight of 39.94 and a ratio of specific heats of 5/3. The universal gas constant is R0 = 8.314 kJ/(kgmol K).

Reference no: EM131057170

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