  In this study, the effect of inlet air cooling and fuel type on the
performance parameters of thrust-specific fuel consumption (TSFC), thermal and
exergetic efficiencies, entropy generation rate, and Nitrogen oxide emission
intensity index (SNOx) of the GENX 1B70 engine is analyzed in two states of
take-off and on design. The results show that with a 20-degree delicious
reduction in inlet air temperature on design conditions and JP10 fuel usage,
the thermal efficiency and entropy generation rate, thrust and fuel mass flow
rate, and TSFC of the engine increase by 1.85 percent, 16.51 percent, 11.76
percent, 10.53 percent, and 2.15 percent and SNOx and exergetic efficiency
decrease by 2.11 percent and 26.60 percent, respectively. Also, optimization of
the GENX 1B70 engine cycle as hydrogen fuel usage with three separate objective
functions: thrust maximization, thermal efficiency maximization, and propulsive
efficiency maximization on design point condition was performed based on the
Genetic algorithm. Based on the economic approach and exero-environmental, the
best cycles from the optimal states were selected using the TOPSIS algorithm.
In on design conditions, entropy generation rate, nitrogen oxide production
rate, and TSFC for the chosen cycle based on the economic approach +18.89
percent, +10.01 percent, and -0.21percent, respectively, and based on the
exero-environmental approach -54.03percent, -42.02percent, and +21.44percent
change compared to the base engine, respectively.
