Numerical Simulation of Pulse Detonation Rocket-Induced MHD Ejector (PDRIME) Concepts for Advanced Propulsion Systems.

摘要

The primary goal of this research project has been to use high resolution numerical methods to explore reactive and magnetohydrodynamic (MHD) flow phenomena as a means of potentially improving the performance of hypersonic propulsion through a range of alternative and innovative combined- cycle concepts, such as the Pulse Detonation Rocket-Induced MHD Ejector (PDRIME) Concept. Such a combined cycle propulsion concept has the potential to achieve improved system performance over conventional rockets or pulse detonation rocket engine (PDRE) concepts in a range of flight conditions, via temporal energy bypass from a pulse detonation rocket to an MHD augmented component. These studies constitute an assessment of the potential improvements possible through PDRIME concepts via detailed numerical simulations as well as simplified modeling. On the basis of both simplified modeling and highly resolved simulations, an optimization of system level configuration has been explored in detail. Beyond the PDRIME explorations, based on discussions with Dr. Birkan, as part of this grant our research group has also examined fundamental resolution of detonation instabilities with complex reaction kinetics and the potential influence of an applied magnetic field on the reactive flow, in addition to experiments relevant to acoustical lycoupled coaxial jet instabilities in rocket chambers.