Four stinger injectors arrayed at s/D -6:7 were tested in a Mach 2.44 supersonic combustor with a 1.66° diverging section at T0 = 2060 K. Wall pressure and gas sampling measurements confirmed the ability of the multiple stinger injectors to improve combustor performance. Wall pressure and gas sampling measurements confirmed the ability of the multiple stinger injectors to improve combustor performance. For ψ̎0:3, the combustion region was limited in the diverging section of the combustor, so the combustor was operated in the scramjet mode. For this mode, compared with the airflow between the multiple circular injectors, the airflow much more easily passed between the djacent stinger injectors due to the low blockage effect. As a result, the pressure thrust in the stinger case was 5% higher than that in the circular case. The effects of the injector port shape became unclear when the precombustion shock waves appeared far upstream of the injectors (dual-mode scramjet operation). The fuels from the multiple injectors were uniformly distributed in the span-wise direction, and combustor performance was mainly dominated by the change in airflow momentum flux and disturbance due to the precombustion shock wave.
|ジャーナル||Transactions of the Japan Society for Aeronautical and Space Sciences|
|出版ステータス||Published - 2017|
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