Dual Cavity Scramjet Operability and Performance Study

Many studies have been conducted showing the benefits of using cavity flame holding and axial fuel distribution techniques to improve combustion in supersonic flow paths. These studies have primarily focused on using a single cavity within the flow path. Dual flame holding cavities may provide additional benefits and increased combustor performance. The purpose of this study is to compare the operability and performance of a dual cavity supersonic combustor with that of a single cavity over various flight conditions, equivalence ratios, and fuel injection schemes. Experimental and numerical approaches will be used to explore the effects of various fueling schemes for both single and dual cavities. Discrete flight conditions from Mach 3.5 to 5.0 at flight dynamic pressures from approximately 500 to 2000 psf were studied. The objectives of this study include: 1) investigate the effects of adding a second cavity to a scramjet flow path, and 2) determine and analyze the performance and operability of the dual cavity for various conditions. Measurements including streamwise pressure distribution profiles, peak and exit pressure ratios, and stream thrust have been obtained. Results suggest a significant increase in performance using a dual cavity flame holder.