# The mass flow rate of air through an aircraft engine is $10 \mathrm{~kg} / \mathrm{s}$. The compressor outlet temperature is $400 \mathrm{~K}$ and the turbine inlet temperature is $1800 \mathrm{~K}$. The heating value of the fuel is $42 \mathrm{MJ} / \mathrm{kg}$ and the specific heat at constant pressure is $1 \mathrm{~kJ} / \mathrm{kg}-\mathrm{K}$. The mass flow rate of the fuel in $\mathrm{kg} / \mathrm{s}$ is approximately_____________

## Question ID - 156014 :- The mass flow rate of air through an aircraft engine is $10 \mathrm{~kg} / \mathrm{s}$. The compressor outlet temperature is $400 \mathrm{~K}$ and the turbine inlet temperature is $1800 \mathrm{~K}$. The heating value of the fuel is $42 \mathrm{MJ} / \mathrm{kg}$ and the specific heat at constant pressure is $1 \mathrm{~kJ} / \mathrm{kg}-\mathrm{K}$. The mass flow rate of the fuel in $\mathrm{kg} / \mathrm{s}$ is approximately_____________

3537

Answer Key : (0.3 to 0.35) -

0.3 to 0.35

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For a given inlet condition, if the turbine inlet temperature is fixed, what value of compressor efficiency given below leads to the lowest amount of fuel added in the combustor of a gas turbine engine?
(A) 1
(B) 0.95
(C) 0.85
(D) 0.8