Abstract
The characteristics of a dual-inlet side-dump combustor configuration suitable for ducted rocket missiles was investigated by injecting a liquid fuel (JP-4) into the two rectangular inlet ducts upstream of the dump plane. Cold flow water tunnel simulations were obtained by injecting small air bubbles into the inlet arms of a plexiglas model and illuminating these by a high intensity slit light source. Combustor performance was obtained by testing a similar stainless steel model on a combustor thrust rig. Combustion efficiency, combustor total pressure loss, lean blow-out limits, combustor pressure oscillations, and surface heating patterns were obtained. A threedimensional computer code using the k-e turbulence model was used to predict the corresponding cold flowfields with good agreement.
Published Version
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call