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Performance Study of Separate Exhaust Innovative Turbofan Engine Configurations with the Control Mechanism of a Baseline Engine | ||
| AUT Journal of Mechanical Engineering | ||
| دوره 8، شماره 3، 2024، صفحه 257-272 اصل مقاله (1.29 M) | ||
| نوع مقاله: Research Article | ||
| شناسه دیجیتال (DOI): 10.22060/ajme.2024.23154.6107 | ||
| نویسندگان | ||
| Elyas Lekzian* ؛ Reza Modanlou | ||
| Department of Aerospace, Faculty of New Sciences and Technologies, Semnan University, Semnan, Iran | ||
| چکیده | ||
| In the current paper, an aero-thermodynamic solver is employed to simulate the performance of innovative turbofan engine layouts. The main aim is to investigate the key parameters such as thrust, specific fuel consumption (SFC), and engine efficiency. The innovative engine configurations are integrated with a base engine referred to as engine type 1. Engine type 2 is constructed by adding a secondary combustion chamber, while engine type 3 incorporates a secondary inner bypass. Engine type 4 benefits from a secondary chamber and an inner bypass duct simultaneously. Flat rate analysis shows that engine type 1 turbine inlet temperature can increase up to 1708.5 K under ISA+30 conditions. Additionally, the cruise thrust of engine type 2 can be enhanced by up to 77% with a penalty of 20% increase in SFC. An optimum reference inner bypass ratio is achieved for engine type 3, which simultaneously maximizes thrust and minimizes SFC. For Engine Type 4, when the sum of reference inner and outer bypass ratios equals 5.1, and the combustion chamber temperature matches that of the baseline engine, it produces 17% higher cruise thrust than engine type 1. Besides, engine type 4 has a higher cruise thrust at M=0.8 among all engine types. Engine type 2 and type 4 have higher flat rate performance (ISA+40). Engine type 3 has the highest overall efficiency, while engine type 2 demonstrates the lowest efficiency. | ||
| کلیدواژهها | ||
| Aero-Thermodynamic Solver؛ Second Bypass؛ Secondary Combustion Chamber؛ Performance؛ Flat Rate | ||
| مراجع | ||
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