Abstract:

The objectives of this study are to determine the optimum design parameters of a IBCE for hypersonic flight and to investigate the relationship between engine performance and design parameters. The investigation of these objectives is made first in the literature in this study. The optimization of inverted Brayton cycle engine ,IBCE, is performed using the particle swarm optimization method in this study. The optimum specific thrust, sT, value is reached by staying within the optimization constraints. When the total temperature of the cooling section is examined, a temperature above the freezing temperature of the air is obtained. A very high sT value, 451 N.s/kg is obtained at the hypersonic flight Mach Number (5 Mach) as a result of optimization. By the investigation, it is concluded that specific fuel consumption, SFC, reduces % 5.3 and sT increases % 5.6 dependent on preburner exit total temperature, PETT, change from 2100 K to 1400 K. Based on total temperature decrease at cooling section,T_cooling, change from 100 K to 500 K, it is seen that by the investigation, SFC increases %23.7 and sT increases % 13.1. It is seen that SFC reduces by % 6.3 and sT increases by % 35.9 depending on afterburner exit total temperature, AETT, change from 2000 K to 2300 K. It is observed that SFC reduces % 10.5 and sT increases % 11.7 dependent on total pressure ratio of turbine, π_t , change from 0.9 to 0.1.

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