The performance date from inward radial flow exhaust gas turbine are as follows: Stagnation pressure at...
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The performance date from inward radial flow exhaust gas turbine are as follows: Stagnation pressure at inlet to nozzles, poi 705 kPa Stagnation temperature at inlet to nozzles, Toi 1080K Static pressure at exit from nozzles, p2 515 kPa Static temperature at exit from nozzles, T2 1000K Static pressure at exit from rotor, p3 360 kPa Static temperature at exit from rotor, T3 923K Stagnation temperature at exit from rotor, To3 925K Ratio a 0.5 Rotational speed, N 25, 500 rpm The flow into the rotor is radial and at exit the flow is axial at all radii. Calculate (1) the total-to-static efficiency of the turbine, (2) the impeller tip diameter, (3) the enthalpy loss coefficient for the nozzle and rotor rows, (4) the blade outlet angle at the mean diameter, and (5) the total-to-total efficiency of the turbine. [(1) 93%, (2) 0.32 m, (3) 0.019, 0.399, (4) 72.2°, (5) 94%] The performance date from inward radial flow exhaust gas turbine are as follows: Stagnation pressure at inlet to nozzles, poi 705 kPa Stagnation temperature at inlet to nozzles, Toi 1080K Static pressure at exit from nozzles, p2 515 kPa Static temperature at exit from nozzles, T2 1000K Static pressure at exit from rotor, p3 360 kPa Static temperature at exit from rotor, T3 923K Stagnation temperature at exit from rotor, To3 925K Ratio a 0.5 Rotational speed, N 25, 500 rpm The flow into the rotor is radial and at exit the flow is axial at all radii. Calculate (1) the total-to-static efficiency of the turbine, (2) the impeller tip diameter, (3) the enthalpy loss coefficient for the nozzle and rotor rows, (4) the blade outlet angle at the mean diameter, and (5) the total-to-total efficiency of the turbine. [(1) 93%, (2) 0.32 m, (3) 0.019, 0.399, (4) 72.2°, (5) 94%]
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Related Book For
Fundamentals of Thermodynamics
ISBN: 978-0471152323
6th edition
Authors: Richard E. Sonntag, Claus Borgnakke, Gordon J. Van Wylen
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