Experimental investigation shows that ejector nozzles enhance thrust and reduce fuel consumption in micro-turbojet engines, highlighting improved infrared characteristics.
In this study, the axisymmetric nozzle for the SW300B micro-turbojet engine is redesigned as an axisymmetric ejector nozzle, rectangular nozzle, rectangular ejector nozzle, rectangular lobed nozzle, and rectangular lobed ejector nozzle. The flow rate, thrust, fuel consumption rate, and infrared radiation (IR) characteristics of the micro-turbojet engine with each of the above-mentioned six nozzle types are studied experimentally. The effect of the ejector nozzle type on the aerodynamic performance and IR characteristics of the engine is then analyzed. The findings of this study reveal that ejector nozzles enhance the total flow rate of the engine, increase thrust, and reduce thrust-specific fuel consumption (TSFC). Under test conditions, the pumping characteristics of the rectangular lobed ejector nozzle are the strongest. Using this nozzle type, the ejector secondary-to-primary flow ratio reaches 48.65%, the engine thrust rises by 13.64%, and the TSFC falls by 12.02%. Moreover, the rectangular ejector nozzle effectively balances the thrust performance and IR characteristics of the engine. Compared to the turbojet engine with the rectangular lobed ejector nozzle, the thrust of the engine with the rectangular ejector nozzle is 4.7% higher. Additionally, the IR signature of the engine with the rectangular ejector nozzle is significantly lower than that with the axisymmetric ejector nozzle. In the 0° and 30° directions on the vertical detection plane, the IR characteristics fall by 20.2% and 47.7%, respectively.
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Shi et al. (2025) studied this question.
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