An inward flow radial turbine (see Fig. P12.52) involves a
Chapter 12, Problem 12.52(choose chapter or problem)
An inward flow radial turbine (see Fig. P12.52) involves a nozzle angle, \(\alpha_1\), of \(60^\circ\) and an inlet rotor tip speed, \(U_1\), of 9 m/s. The ratio of rotor inlet to outlet diameters is 2.0. The radial component of velocity remains constant at 6 m/s through the rotor, and the flow leaving the rotor at section (2) is without angular momentum. If the flowing fluid is water and the stagnation pressure drop across the rotor is 110 kPa, determine the loss of available energy across the rotor and the efficiency involved.
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