Abstract
A plasma jet (PJ) torch igniter with a novel configuration in a scramjet combustor was developed, and ignition tests of the new torch were conducted in supersonic flow. Two PJ torches with different feedstocks were arranged in a straight line in the direction of flow. A H 2/N 2 PJ (H 2 mole fraction was 0.30) was selected for the upstream PJ, and an O 2 PJ was selected for the downstream PJ. This combination (H 2/N 2–O 2 PJs) had many advantages to other combinations and it compared with N 2–N 2 PJs. The experiment was conducted using an intermittent suction-type wind tunnel and a two-dimensional contoured nozzle. The Mach number of the main flow was 2.3. The total temperature and total pressure of the main flow were those of the room condition. Three kinds of fuels (H 2, C 2H 4, and CH 4) at room temperature were tested. The fuel was injected normal to the main stream at the sonic speed from the orifice located upstream of the twin PJs. In experimental results, the twin PJs developed in this paper showed that ignition in supersonic flow was successful for both fuels of H 2 and hydrocarbon, even at the lowest electric power input to the PJs (about 2.5 kW in total for two torches). Moreover, the superiority of the H 2/N 2–O 2 PJs to the N 2–N 2 PJs was shown for all fuels, though basic flow structure formed by injection of twin PJs was same.
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