9.9 Combustion gases with cp = 1148 J/kg K and gas constant R = 287 J/kgK enter the stator of a radial inflow turbine at the stagnation pressure poi = 346 kPa and stagnation temperature Toi = 980 K. They enter the rotor at the speed V₂ = 481.4 m/s with the relative flow making an angle 3₂ = -35° and exhaust into the atmosphere at 101.325 kPa. 358 RADIAL INFLOW TURBINES The total-to-static efficiency of the turbine is nts = 0.83. Find (a) the angle at which the flow enters the rotor and (b) the relative Mach number at the inlet.
9.9 Combustion gases with cp = 1148 J/kg K and gas constant R = 287 J/kgK enter the stator of a radial inflow turbine at the stagnation pressure poi = 346 kPa and stagnation temperature Toi = 980 K. They enter the rotor at the speed V₂ = 481.4 m/s with the relative flow making an angle 3₂ = -35° and exhaust into the atmosphere at 101.325 kPa. 358 RADIAL INFLOW TURBINES The total-to-static efficiency of the turbine is nts = 0.83. Find (a) the angle at which the flow enters the rotor and (b) the relative Mach number at the inlet.
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Transcribed Image Text:9.9 Combustion gases with cp = 1148 J/kg K and gas constant R = 287 J/kgK enter
the stator of a radial inflow turbine at the stagnation pressure poi = 346 kPa and stagnation
temperature T01 = 980 K. They enter the rotor at the speed V₂ = 481.4 m/s with the
relative flow making an angle 3₂ = -35° and exhaust into the atmosphere at 101.325 kPa.
358 RADIAL INFLOW TURBINES
The total-to-static efficiency of the turbine is nts = 0.83. Find (a) the angle at which the
flow enters the rotor and (b) the relative Mach number at the inlet.
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