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Experimental Investigation and Performance Simulation Development of a Valved Pulsejet Engine | ||
| Journal of Heat and Mass Transfer Research | ||
| دوره 12، شماره 2 - شماره پیاپی 24، بهمن 2025، صفحه 271-286 اصل مقاله (1.07 M) | ||
| نوع مقاله: Full Length Research Article | ||
| شناسه دیجیتال (DOI): 10.22075/jhmtr.2025.35703.1628 | ||
| نویسندگان | ||
| Mohsen Sadeghi1؛ Elyas Lekzian* 1؛ Shahaboddin Kharazmi* 2؛ Mohammad Hossein Khalesi2 | ||
| 1Faculty of New Sciences and Technologies, Semnan University, Semnan, 35131-19111, Iran | ||
| 2Faculty of Mechanical Engineering, Semnan University, Semnan, 35131-19111, Iran | ||
| تاریخ دریافت: 01 آبان 1403، تاریخ بازنگری: 27 دی 1403، تاریخ پذیرش: 27 بهمن 1403 | ||
| چکیده | ||
| The objective of the present study is to conduct an empirical and theoretical investigation of a liquid-fueled laboratory hobby scale pulsejet engine. This engine comprises an inlet and air intake valve, combustion chamber, exhaust pipe, connecting semi-cone, igniter, and fuel injector. It is capable of ignition, stable combustion, and thrust production with a combustion chamber length to a total length ratio of 0.14. The operating frequency of this engine is 56 Hz, and the valves can function for 10 minutes. Experimental tests have demonstrated that the thickness of the valves significantly impacts the stable combustion of the engine. Empirical data indicate that the operating pressure ratio of the combustion chamber to ambient pressure is approximately 1.63. The average thrust of the engine is 140 Newtons, and the fuel mass flow rate is 15.9 grams per second. A performance simulation program for this engine has been developed using MATLAB software. Validation of the results shows the utmost 5/1% discrepancy between the simulation and experimental data. The simulation indicates that increasing the chamber pressure ratio from 1.5 to 2.5 results in a nearly sixfold increase in thrust. With an increase in the chamber pressure ratio, specific fuel consumption decreases. The simulation also shows that an increase in the engine's exhaust temperature leads to a reduction in thrust. Additionally, the sensitivity of thrust reduction to an increase in exhaust duct temperature is higher at elevated combustion chamber pressures. Furthermore, increasing the ratio of the combustion chamber diameter to the exhaust duct diameter results in an increase in thrust relative to the engine's baseline thrust. The specific fuel consumption of the engine increases with the combustion chamber diameter. | ||
| کلیدواژهها | ||
| Pulse-jet engine؛ Fabrication and test؛ Thrust؛ Specific fuel consumption | ||
| مراجع | ||
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