A plane is powered by a turbojet engine where atmospheric conditions are To = 232 K,...

  

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A plane is powered by a turbojet engine where atmospheric conditions are To = 232 K, Po = 60kPa. Temperature before the turbine is T4 = 1300K and the flight speed is 700km/h. Mass flow rate of fuel is 0,13 kg/sec. Assume total mass flow rate is equal to ma+mf, ne = 0,98, T=12, CV=44 MJ/kg, k=1,4, R=287 J/kg K. assume Cpc = CpT = Cp and inlet pressure loss coefficient is 0,95. Calculations should be done for total parameters. Calculate: . · ● Tro. Pro Trz, Prz Trari Pra ma Power delivered to the compressor (le) A plane is powered by a turbojet engine where atmospheric conditions are To = 232 K, Po = 60kPa. Temperature before the turbine is T4 = 1300K and the flight speed is 700km/h. Mass flow rate of fuel is 0,13 kg/sec. Assume total mass flow rate is equal to ma+mf, ne = 0,98, T=12, CV=44 MJ/kg, k=1,4, R=287 J/kg K. assume Cpc = CpT = Cp and inlet pressure loss coefficient is 0,95. Calculations should be done for total parameters. Calculate: . · ● Tro. Pro Trz, Prz Trari Pra ma Power delivered to the compressor (le)

Answer rating: 100% (QA)

SOLUTION To solve this problem we will use the following thermodynamic equations and relationships The isentropic efficiency of the compressor etac h2s h1 h2 h1 where h1 and h2 are the enthalpies at t... View the full answer