Aerothermodynamic Analysis of Inlet Air Temperature Effects on Aero-Gas
Engine Performance and Optimization for High-Speed, High-Altitude Flight
Conditions
Abstract
In this study, the effects of variations in inlet air temperature, Mach
number, and flight altitude on the performance of the Ramjet XRJ47-W-5
turbofan engines, the F135PW100 and EJ200 turbofan engines, and the J85
GE17 turbojet engine have been investigated. Thrust, specific fuel
consumption (TSFC), fuel flow rate, thermal and propulsive efficiencies,
nitrous oxide emissions (EI NOx), and actual inlet air mass flow rate to
the engines have been considered as performance parameters. At a flight
altitude of 10000 meters and a Mach number of 0.8, with a 20-degree
reduction in inlet air temperature compared to the ISA Standard
Atmosphere (International Standard Atmosphere), the F135PW100 and EJ200
turbofan engines, as well as the J85 GE17 turbojet engine, experienced
thrust increases of 7.5%, 5.33%, and 11% respectively, and TSFC
reductions of 1.21%, 0.96%, and 0.23% respectively. For the Ramjet
XRJ47-W-5, at a flight altitude of 10000 meters and a Mach number of 3,
with a 20-degree reduction in inlet air temperature compared to ISA,
thrust increased by 9.11% and TSFC decreased by 1.62%. With an
increase in the Mach number, the impact of inlet air temperature
variations on engine performance parameters becomes more pronounced.
Using a genetic algorithm, the optimization of the studied engines has
been conducted within the flight altitude range of 20000 to 40000 meters
and Mach number range of 2 to 4.5, based on maximizing TSF, minimizing
TSFC, and maximizing thermal efficiency. Among the optimal cases,
considering energy consumption and power approach, the TOPSIS
decision-making method has been employed to select the best
configuration.