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1- Air to fuel ratio 2- Exhaust nozzle pressure 3- The velocity of the exhaust jet

1- Air to fuel ratio 2- Exhaust nozzle pressure 3- The velocity of the exhaust jet

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
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Q3) A turbojet engine is operates at altitude where temperature and pressure are 216K, 60kPa respectively. The air craft speed is 250m/s and the engine data is given below. Assume that, properties of the combustion gas same as those of air and no stagnation pressure losses in the inlet diffuser. Combustion • The stagnation temperature at the turbine chamber 3 inlet=1500K Toa Pea Tes Paa Temperature drop at the turbine= 205 C • Calorific valve of the fuel= 42MJ/ Kg Turbine efficiency= 0.9 • Compressor efficiency 0.8 • Combustion efficiency= 0.95 Exhaust Nozzle efficiency =0.93 Stagnation pressure at the turbine entry: (Po3) = 0.97 x Po2 Air Compressor Turbine Nozzie Exhaust TA T. Pe Intet difuser Tor. Por Toe Pos Calculate: 1- Air to fuel ratio 2- Exhaust nozzle pressure 3- The velocity of the exhaust jet 4- Thrust force develops if the inlet diffuser area is 0.5m2 5- Propulsive efficiency, specific thrust
Transcribed Image Text:Q3) A turbojet engine is operates at altitude where temperature and pressure are 216K, 60kPa respectively. The air craft speed is 250m/s and the engine data is given below. Assume that, properties of the combustion gas same as those of air and no stagnation pressure losses in the inlet diffuser. Combustion • The stagnation temperature at the turbine chamber 3 inlet=1500K Toa Pea Tes Paa Temperature drop at the turbine= 205 C • Calorific valve of the fuel= 42MJ/ Kg Turbine efficiency= 0.9 • Compressor efficiency 0.8 • Combustion efficiency= 0.95 Exhaust Nozzle efficiency =0.93 Stagnation pressure at the turbine entry: (Po3) = 0.97 x Po2 Air Compressor Turbine Nozzie Exhaust TA T. Pe Intet difuser Tor. Por Toe Pos Calculate: 1- Air to fuel ratio 2- Exhaust nozzle pressure 3- The velocity of the exhaust jet 4- Thrust force develops if the inlet diffuser area is 0.5m2 5- Propulsive efficiency, specific thrust
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