Aerospace Engineering > GATE 2009 > Engine Cycle Analysis
Air enters the combustor of a gas-turbine engine at a total temperature T0 of 500 K. The air stream is split into two parts: primary and secondary streams. The primary stream reacts with fuel supplied at a fuel-air ratio of 0.05. The resulting combustion products are then mixed with the secondary air stream to obtain gas with total temperature of 1550 K at the turbine inlet. The fuel has a heating value of 42 MJ/kg. The specific heats of air and combustion products are taken as cp = 1 kJ/kg/K.
The approximate ratio of mass flow rates of the primary air stream to the secondary air stream required
to achieve the turbine inlet total temperature of 1550 K is
The approximate ratio of mass flow rates of the primary air stream to the secondary air stream required
to achieve the turbine inlet total temperature of 1550 K is
Correct : b
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