A study on the enhancement of supersonic mixing by using RMP shaped injector with shock generator and cavity

Recently, supersonic mixing is very important not only for SCRAM-jet engine, but also for Pulse Detonation Engine. The present authors would emphasize that ramp shaped injector has many merits for supersonic mixing especially to reduce total pressure loss. But it is difficult to establish high mixing rate by using ramp shaped injector only. In the present study, we use shock generator and cavity with ramp shaped injector in order to establish high mixing rate. Experimental studies on supersonic mixing phenomena of ramp shaped injector with shock generator and cavity were conducted. The configuration of experimental model has three patterns. A: ramp shaped injector only. B: ramp shaped injector with shock generator. C: ramp shaped injector and cavity. Supersonic wind tunnel was used for the experiments. The free stream Mach number is 4.0, total pressure is 1.3MPa and total temperature is 287K on average. As a secondary gas, Helium gas was injected at sonic speed from the ramp shaped injector. Its total pressure is 0.4MPa and total temperature is 287K on average. In the experiments, flow pattern on the wall surface was revealed by the oil flow technique and the flow field of the slotted injection was visualized by the Shlieren method. Also volume fraction has been measured.