For rotating detonation engines, the high-pressure region behind the detonation causes backflow into the plenum, making it difficult to properly design injectors to achieve the target pressure balance due to blockage of a part of the injector area during engine operation. In this paper, we present the pressure and thrust measurement of a rotating detonation engine with two different triplet injectors (fuel injector diameters of 0.8 mm and 1.0 mm) using gaseous methane, gaseous ethylene, and gaseous oxygen. The detonation wave propagation velocity with the fuel injector diameter of 0.8 mm was approximately 200 m/s higher than that with the fuel injector diameter of 1.0 mm. Combustor pressures and specific impulses were almost identical for both fuel injector diameters in this study. For our evaluation of the extent to which the available injector area can be utilized during engine operation, the effective injector area ratio was defined as the ratio of the plenum pressure during burn time to the pre-ignition value. Regardless of fuel species and fuel injector orifice diameter, the effective injector area ratio decreased proportionally with the ratio of combustor pressure to pre-ignition plenum pressure. This result implies that the pressure balance between the upstream plenum pressure and the combustor pressure can be roughly determined taking the effect of backflow into consideration.

对于旋转爆震发动机，爆震后的高压区域导致回流进入气室，由于在发动机运行期间一部分喷油器区域的阻塞，使得难以正确设计喷油器以实现目标压力平衡。在本文中，我们介绍了使用两种气态甲烷，气态乙烯和气态氧气的旋转爆震发动机的压力和推力测量结果，该发动机具有两个不同的三重态喷油嘴（喷油嘴直径分别为0.8 mm和1.0 mm）。燃料喷射器直径为0.8 mm时的爆炸波传播速度比燃料喷射器直径为1.0 mm时的爆炸波传播速度高约200 m / s。在本研究中，两种燃料喷射器直径的燃烧器压力和特定脉冲几乎相同。为了评估发动机工作期间可利用的可用喷射器面积的程度，将有效喷射器面积比定义为燃烧时间期间的增压压力与点火前值的比值。不管燃料种类和燃料喷射器孔的直径如何，有效喷射器面积比都随着燃烧器压力与点火前气室压力之比成比例地减小。该结果暗示，可以考虑回流的影响来大致确定上游气室压力与燃烧器压力之间的压力平衡。有效喷射器面积比与燃烧室压力与点火前气室压力之比成比例地降低。该结果暗示，可以考虑回流的影响来大致确定上游气室压力与燃烧器压力之间的压力平衡。有效喷射器面积比与燃烧室压力与点火前气室压力之比成比例地降低。该结果暗示，可以考虑回流的影响来大致确定上游气室压力与燃烧器压力之间的压力平衡。