Aerospace Engineering > GATE 2009 > Combustion
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.
If the sensible enthalpy of fuel is neglected, the temperature of combustion products from the reaction
of primary air stream with fuel is approximately
If the sensible enthalpy of fuel is neglected, the temperature of combustion products from the reaction
of primary air stream with fuel is approximately
Correct : c
Similar Questions
A surrogate liquid hydrocarbon fuel, approximated as C10H12, is being burned in a land-based gas turbine combustor with dry air (79% N2 and 21% O2 by volume). H...
In an airbreathing gas turbine engine, the combustor inlet temperature is 600 K. The heating value of the fuel is 43.4 x 106 J/kg. Assume Cp to be 1100 J/kg K f...
A gas turbine combustor is burning methane and air at an equivalence ratio ฯ = (F/A)/(F/A)stoich, where ฯ = 0.5 and (F/A)stoich is the ratio of the mass flow ra...
Total Unique Visitors
Loading......