Unified analysis of internal flowfield in an integrated rocket ramjet engine. II: Ramjet sustainer

The flow and combustion dynamics in the ramjet sustainer of an integrated rocket-ramjet (IRR) engine are investigated systematically. The physical model includes the entire engine flowpath, from the freestream in front of the inlet to the exit of the exhaust nozzle. The flowfield obtained previously is used as the initial condition for the present analysis, so that the complete operation history of the engine can be obtained. Various physiochemical processes dictating the engine internal flow development and flame behavior are examined. Emphasis is placed on the interactions between the inlet and combustion dynamics, as well as the overall engine performance. The key mechanisms for driving and sustaining the flow oscillations are explored. In addition, the acoustic wave structures in the engine flowpath are identified.