A single spool turbojet engine under take off at sea level (Pa-1 bar, Ta=300 K). The...

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A single spool turbojet engine under take off at sea level (Pa-1 bar, Ta=300 K). The compressor pressure ratio is 10 and the air mass flow rate entering the compressor is 45 kg/s. The maximum temperature in the engine is 1275 K and the compressor and turbine olytropic efficiencies are 87% and 89% respectively. Calculate: (a) the fuel mass flow rate if (b) the stagnation conditions at the jet pipe (To4 and P04). Use for air k=1.4, Cpa-1005 g.K and for gas k=1.333, Cpg 1147 J/kg.K, h 43,100,000 J/kg and R-287 J/kg.K for h. A single spool turbojet engine under take off at sea level (Pa-1 bar, Ta=300 K). The compressor pressure ratio is 10 and the air mass flow rate entering the compressor is 45 kg/s. The maximum temperature in the engine is 1275 K and the compressor and turbine olytropic efficiencies are 87% and 89% respectively. Calculate: (a) the fuel mass flow rate if (b) the stagnation conditions at the jet pipe (To4 and P04). Use for air k=1.4, Cpa-1005 g.K and for gas k=1.333, Cpg 1147 J/kg.K, h 43,100,000 J/kg and R-287 J/kg.K for h.