A study on integrated aerodynamic-ramp-injector/gas-portfire in a supersonic combustor: Part two, experimental aspects

Experimental study of a novel integrated flush-wall aero-ramp fuel injector/gas-portfire for supersonic combustion applications has been conducted. In the experiments, ethylene was injected through the fuel injector at jet to freestream momentum flux ratios (q) ranging from 2.1 - 4. 5. Color schlieren and surface oil-flow visualization pictures were taken in the vicinity of the injectors to obtain a qualitative assessment of the injector fio wf i elds. In hot flow experiments, the aerodynamic ramp injector with 2×2 holes was investigated as baseline injector. 7 different combined aerodynamic ramp injector experiments were conducted for high equivalence (nearly 1. 0). Results of the experiments showed that the fuel from aero-ramp was mixed up fastly and had a strong interaction with the plume of gas portfire. In the condition of which the simulating flight Mach number is 5, a successful combustion was demonstrated by observing wall-static pressure rise in the combustor. Both subsonic and supersonic combustion modes were observed with ethylene fuel. One-dimensional performance analysis of the test data indicates that combustion efficiencies were 0. 56 ∼0. 94. It is the first time that the integration of an aero-ramp injector/gas-portfire for supersonic combustion has been studied in a paper. It was concluded that this novel injection scheme for supersonic combustion is applicable.