A Comparative Performance Analysis of the Novel TurboAux Engine with a Turbojet Engine, and a Low-Bypass Ratio Turbofan Engine with an Afterburner

Presented herein is a comparative performance analysis of novel turbofan engine with an auxiliary combustion chamber, nicknamed the TurboAux engine, against turbojet and low bypass ratio afterburner presented. The adaption low-bypass but secondary in annular chamber for thrust augmentation. envisioned desire to facilitate clean burning fuel at temperatures higher than main air exiting low-pressure compressor. study starts by analyzing its without segment attached. In parallel, conventional mixing counterpart are analyzed, also segment. A simple optimization performed identify optimal ‘fan’ pressure ratios series (0.1 1.5). fan their corresponding adapted demonstrate varying configurations engine. formulation results attempt make case charter aircrafts efficient close-air-support aircrafts. yielded increased augmentation, cost spike consumption. This trade-off requires more in-depth investigation further ascertain TurboAux’s utility.