Pan Hongliang , Lin Binbin , Ye Jinying

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018-2870951

In order to improve RBCC engine’s specific impulse in the case of a high propellant consumption by inserted rocket in RBCC ejector mode, thrust augmentation relies on secondary fuel burning with incoming air. Because of complex mechanism in flow and combustion in ejector mode, effective ejection and secondary burning has to be matched in coupling with the primary rocket jet, incoming airflow and configuration of ramjet combustor. In the paper three-dimensional CFD and ground direct-connect experiments have been undertaken to study effects of combustion organization on ejection and engine performance. A steady burning and thermal choke have been realized through pylon and cavity aided combustion organization in a range of 0.4~0.8kg/s of rocket flow rate at flight Ma2. It is found that bypass ratio is not a unique seeking factor for high engine performance in ejector mode. RBCC engine performance improvements rely on a thermal choke position downstream rather than on a bypass ratio. The feasibility to improve specific impulse has also been studied through increase of secondary fuel equivalence ratio by means of rocket throttling.

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In Categories: HiSST 2018, Hypersonic Propulsion, Propulsion Systems and Components
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