Evaluation of Impinging Stream Vortex Chamber Concepts for Liquid Rocket Engine Applications

摘要

Vortex Chamber Concept (ISVC), has been tested with gel propellants at AMCOM at Redstone Arsenal, Alabama. A version of this concept for the liquid oxygen Rocket-based combined-cycle engines (RBCC) being considered at NASA for future-generation launch vehicles feature clusters of small rocket thrusters as part of the engine components. Depending on specific RBCC concepts, these thrusters may be operated at various operating conditions including power level and/or propellant mixture ratio variations. To pursue technology developments for future launch vehicle, MSFC is examining vortex chamber concepts for the subject cycle engine as well as small thruster chamber applications. Past studies indicated that the vortex chamber schemes potentially have a number of advantages over conventional chamber methods. Due to the nature of the vortex flow, relatively cooler propellant streams tend to flow along the chamber wall. Hence, the thruster chamber can be operated without the need of any cooling techniques. This vortex flow also creates strong turbulence, which promotes the propellant mixing process.