Aerospace Engineering > GATE 2021 > Turbofan Engines
A twin-spool turbofan engine is operated at sea level (Pa = 1 bar, Ta = 288 K).
The engine has separate cold and hot nozzles.
During the static thrust test at sea level, the overall mass flow rate of air through the engine and the cold exhaust temperature are measured to be 100 kg/s and 288 K, respectively.
The parameters for the engine are: Fan pressure ratio = 1.6, Overall pressure ratio = 20, Bypass ratio = 3.0, Turbine entry temperature = 1800 K. The specific heat at constant pressure (Cp) is 1.005 kJ/kg-K and the ratio of specific heats (γ) is 1.4 for air. Assuming an ideal fan and ideal expansion in the nozzle, the sea-level static thrust from the cold nozzle is _______ kN. (round off to two decimal places)
The engine has separate cold and hot nozzles.
During the static thrust test at sea level, the overall mass flow rate of air through the engine and the cold exhaust temperature are measured to be 100 kg/s and 288 K, respectively.
The parameters for the engine are: Fan pressure ratio = 1.6, Overall pressure ratio = 20, Bypass ratio = 3.0, Turbine entry temperature = 1800 K. The specific heat at constant pressure (Cp) is 1.005 kJ/kg-K and the ratio of specific heats (γ) is 1.4 for air. Assuming an ideal fan and ideal expansion in the nozzle, the sea-level static thrust from the cold nozzle is _______ kN. (round off to two decimal places)
Correct : 20 to 22
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