Aerospace Engineering > GATE 2014 > Gas Turbine Engines
A gas turbine engine is operating under the following conditions:
Stagnation temperature at turbine inlet 1350 K
Stagnation pressure at the turbine inlet 10 bar
Static temperature at turbine exit 800 K
Velocity at turbine exit 200 m/s
Total-to-total efficiency of turbine 0.96
y (ratio of specific heats) 1.33
Cp(specific heat at constant pressure) 1.147 kJ/kgK
The stagnation pressure (in bar) in the nozzle (considering isentropic nozzle) is equal to
Stagnation temperature at turbine inlet 1350 K
Stagnation pressure at the turbine inlet 10 bar
Static temperature at turbine exit 800 K
Velocity at turbine exit 200 m/s
Total-to-total efficiency of turbine 0.96
y (ratio of specific heats) 1.33
Cp(specific heat at constant pressure) 1.147 kJ/kgK
The stagnation pressure (in bar) in the nozzle (considering isentropic nozzle) is equal to
Correct : 1.10 to 1.25
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