03 == 10.32 An axial-flow turbine stage, at its pitchline radius, is shown. The rotor exit...

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03 == 10.32 An axial-flow turbine stage, at its pitchline radius, is shown. The rotor exit is swirl free, i.e., C#3 = 0. The axial velocity is constant throughout the stage and is equal to C 300 m/s. The flow to the turbine stage is purely axial, i.e., C = C and the gas total temperature is T = 1500 K with = 1.33 and c = 1,156 J/kg K. Assume that the turbine is uncooled and the stage degree of reaction is 20%. Calculate zl (a) the nozzle exit flow angle, a, in degrees (b) the stage specific work in kJ/kg (c) total temperature relative to the rotor, T2.r, in K (d) absolute Mach number at nozzle exit, M2 (e) speed of sound, a3, in m/s (f) relative rotor exit Mach number, M 3r 1 N 2 R C 3 W3 2 C3 C | FIGURE P10.32 U = 400 m/s 7 03 == 10.32 An axial-flow turbine stage, at its pitchline radius, is shown. The rotor exit is swirl free, i.e., C#3 = 0. The axial velocity is constant throughout the stage and is equal to C 300 m/s. The flow to the turbine stage is purely axial, i.e., C = C and the gas total temperature is T = 1500 K with = 1.33 and c = 1,156 J/kg K. Assume that the turbine is uncooled and the stage degree of reaction is 20%. Calculate zl (a) the nozzle exit flow angle, a, in degrees (b) the stage specific work in kJ/kg (c) total temperature relative to the rotor, T2.r, in K (d) absolute Mach number at nozzle exit, M2 (e) speed of sound, a3, in m/s (f) relative rotor exit Mach number, M 3r 1 N 2 R C 3 W3 2 C3 C | FIGURE P10.32 U = 400 m/s 7