Recent content by JK Gowdham

Simple single shaft gas turbine one compressor , one turbine . T1 COMPRESSOR inlet=288K,T2 combustor inlet=792.70K,T3 combustor outlet=1500K,T4 turbine outlet=733.50K, same points like pressure P1=101 kpa, P2=1800 kpa , p 3 = 1800 kpa , P4= 101 kpa ... compressor efficiency = 0.88 , combustion...

so what will be the mass flow rate through the fan for gas turbine of 50mw ...

Hi i have calculated compressor , combustor , turbine inlet and outlet temperature , pressure so on and my output of gas turbine is 50MW , So for this i want to calculate the mass flow rate of air and fuel in compressor , combustor , turbine . Like m0=?,m1=?fan inlet,m2=? compressor inlet,m3=...