7. An axial single stage turbine has the following parameters: Inlet total temperature Inlet total pressure...

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7. An axial single stage turbine has the following parameters: Inlet total temperature Inlet total pressure Turbine Power Mass flow rate NGV total pressure loss (P02/P01) Rotor total pressure loss (P03r/P02r) NGV axial velocity ratio AVR21 Rotor axial velocity ratio AVR32 NGV radius ratio RR21 Rotor radius ratio RR32 NGV exit flow angle () 1750 K 2600 kPa 19240 kW 42.34 kg/s 0.953 0.911 1.7 1.5 0.99 All velocity magnitudes and angles for rotor inlet, rotor outlet/stator inlet, stator outlet Flow path dimensions O 0.988 72 < < 75 Efficiency of the turbine Reaction, work and flow coefficient of the rotor ( = 4, = Hints: Determine design radius and design rotational speed See Week 10 lecture notes, slide 9. Select appropriate inlet Mach number, inlet hub to tip ratio to determine inlet radius. Select appropriate exit Mach number and take AN^2 as AN^2 ~ 2.5x10^13 mm^2RPM^2 O No inlet swirl is imposed. a = 0 o cp = 1157 J/kg-K, y=1.33, R=287.1 J/kg-K VXrotor exit Urotor exit 7. An axial single stage turbine has the following parameters: Inlet total temperature Inlet total pressure Turbine Power Mass flow rate NGV total pressure loss (P02/P01) Rotor total pressure loss (P03r/P02r) NGV axial velocity ratio AVR21 Rotor axial velocity ratio AVR32 NGV radius ratio RR21 Rotor radius ratio RR32 NGV exit flow angle () 1750 K 2600 kPa 19240 kW 42.34 kg/s 0.953 0.911 1.7 1.5 0.99 All velocity magnitudes and angles for rotor inlet, rotor outlet/stator inlet, stator outlet Flow path dimensions O 0.988 72 < < 75 Efficiency of the turbine Reaction, work and flow coefficient of the rotor ( = 4, = Hints: Determine design radius and design rotational speed See Week 10 lecture notes, slide 9. Select appropriate inlet Mach number, inlet hub to tip ratio to determine inlet radius. Select appropriate exit Mach number and take AN^2 as AN^2 ~ 2.5x10^13 mm^2RPM^2 O No inlet swirl is imposed. a = 0 o cp = 1157 J/kg-K, y=1.33, R=287.1 J/kg-K VXrotor exit Urotor exit

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