 Performance evaluation of multicombustor engine for Mach3+-Level propulsion systemLi Deng, Min Chen, Hailong Tang and Jiyuan Zhang Energy, 2024, vol. 295, issue C Abstract: Turbine-based combined cycles are widely considered as a propulsion system for hypersonic vehicles. The inadequate performance of turbine-based engines has resulted in thrust traps, thereby limiting the development of turbine-based combined cycles. To satisfy the performance requirements over a wide speed range, a novel Mach 3+-level multicombustor engine is proposed, and its performance potential is investigated, where an intermediate bypass burner reheats the core airflow to generate more cycle work and the second bypass duct heated by a bypass afterburner provides the main source of the engine thrust at high Mach numbers. Results show that the multicombustor engine extends the flight envelope from Mach 2.5 to 3.5 and increases the thrust by 32% compared with the conventional engine. The application of an intermediate bypass burner reduces the turbine pressure ratio by 43%, thereby reducing the number of turbine stages. The concept of a multicombustor engine is promising for designing the power systems of hypersonic vehicles. Keywords: Thrust trap; Mach 3+-level propulsion system; Multicombustor engine; Intermediate bypass burner; Bypass afterburner (search for similar items in EconPapers) Downloads: (external link) Related works: Export reference: BibTeX RIS (EndNote, ProCite, RefMan) HTML/Text Persistent link: https://EconPapers.repec.org/RePEc:eee:energy:v:295:y:2024:i:c:s0360544224007643 DOI: 10.1016/j.energy.2024.130992 Access Statistics for this article Energy is currently edited by Henrik Lund and Mark J. Kaiser More articles in Energy from Elsevier |
Is your work missing from RePEc? Here is how to contribute.
Questions or problems? Check the EconPapers FAQ or send mail to .
EconPapers is hosted by the
School of Business at Örebro University.