The spray and combustion characteristics of a liquid-fueled ramjet combustor were experimentally analyzed. RJ-1J fuel was injected transversely into a subsonic hot vitiation airstream from a round injection ori ce. The penetration of the liquid jet under hot air ow conditionswas larger than that calculated by the empirical equation obtained under room-temperature air ow conditions. A V-shaped gutter was attached to the center of the combustor for ame holding. Two different arrangements of the gutter and the fuel injector were tested. In one, the fuel was injected perpendicular to the gutter axis, and in the other, the fuel was injected parallel to the axis. In regard to perpendicular fuel injection, a region with a temperature higher than 1500K was observed at the center of the combustor; this region was long and narrow in the direction of the fuel injection. The high-temperature region reached the bottomwall due to involvement of the fuel in the wake region of the fuel injector and the liquid column. In regard to parallel injection, the high-temperature region covered the major part of the cross section of the combustor except in the vicinity of the bottom wall; the measured combustion ef ciencies were higher than those for perpendicular fuel injection. Pilot fuel injection from the gutter was found to be a very effective method for improving combustion characteristics. In addition, it was found that the fuel dispersion in the direction of the injection of the high-temperature fuel, which simulates the regenerative cooling of a ramjet combustor, was lower than that of the low-temperature fuel due to fuel evaporation.
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Inamura et al. (2001) studied this question.
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