| Citation: | MENG Yan, SHEN Lixin, JIANG Chaohu, et al. Impact of nozzle area ratio on performance of small turbojet engines[J]. Journal of Aerospace Power, 2025, 40（X）：20250110 doi: 10.13224/j.cnki.jasp.20250110
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To investigate the impact of nozzle exit area variations on small turbofan engine performance, a 100 daN-class engine across 33 000 r/min to 60 000 r/min speed range under constant speed and constant fuel flow conditions was studied. A mathematical model was developed to quantify the coupling effects between engine parameters, and an optimization strategy was proposed. The results showed that at 54 000 r/min, reducing the equivalent area ratio (EAR) from 1.240 to 0.850 increased the static thrust by 107%, raised the exhaust gas temperature (EGT) by 400 K, and decreased the specific fuel consumption (SFC) by 10.6%. Under constant fuel flow conditions, decreasing EAR led to a 14.8% reduction in speed, a 4% decrease in thrust, a 121 K increase in EGT, and a 6% rise in SFC. Analysis revealed that at EAR of 0.925, SFC was minimized within the 60—80 daN thrust range, indicating the best matching between fuel combustion and gas expansion. Compared with high EAR (1.240), operating with low EAR (0.850—0.925) reduced SFC by 10%—20%, with a 300 K increase in EGT. The optimal operating range was identified as EAR of 0.925—1.000, corresponding to static thrust of 60—80 daN and EGT of 800—950 K. In this range, SFC can be reduced by 15%—20%, static thrust increased by 30%—40%, while EGT remained within material resistance range. These findings could offer valuable insights for adaptive nozzle design and real-time control in unmanned aerial vehicle propulsion systems.
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