Rotary Intakes for Scramjet-like Hypersonic Engines

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C. MacLeod et al. (2020), JBIS, 73, pp.85-96

Refcode: 2020.73.85
Keywords: Scramjet, Pulse detonation engine, ASPIRE, Hypersonic, Propulsion, Pellets, Inlet, Mixing, Air, Fuel

This paper reports further results of a theoretical study into an innovative scramjet-like hypersonic propulsion system. The method, named ASPIRE, aims to overcome one of the main limitations of the traditional scramjet cycle – poor mixing and therefore inadequate combustion of air and fuel. The proposed system achieves this by redirecting the main airflow, injecting encapsulated or localised fuel throughout the engine-duct mixing volume and then switching the main airflow back on – this then engulfs and mixes with the fuel. The results presented here focus on the structure and design of the intake system for such an engine and demonstrate its behaviour using CFD simulation and modelling. A roadmap of further work is also discussed.

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