A gas turbine stage has an initial absolute pressure of 350 kPa and a temperature of...

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A gas turbine stage has an initial absolute pressure of 350 kPa and a temperature of 565C with negligible initial velocity. At the mean radius, 0.36 m, conditions are as follows: Nozzle exit flow angle 68 Nozzle exit absolute pressure 207 kPa Stage reaction 0.2 Determine the flow coefficient and stage loading factor at the mean radius and the reaction at the hub, radius 0.31 m, at the design speed of 8000 rev/min, given that stage is to have a free-vortex swirl at this speed. You may assume that losses are absent. Comment upon the results you obtain. Take Cp = 1.148 kJ/(kg C) and y = 1.33. A gas turbine stage has an initial absolute pressure of 350 kPa and a temperature of 565C with negligible initial velocity. At the mean radius, 0.36 m, conditions are as follows: Nozzle exit flow angle 68 Nozzle exit absolute pressure 207 kPa Stage reaction 0.2 Determine the flow coefficient and stage loading factor at the mean radius and the reaction at the hub, radius 0.31 m, at the design speed of 8000 rev/min, given that stage is to have a free-vortex swirl at this speed. You may assume that losses are absent. Comment upon the results you obtain. Take Cp = 1.148 kJ/(kg C) and y = 1.33.