Mixing Performance of Swirler Enhanced Solid Rocket Ramjet

Yongcheng Tao, Jiming Cheng, Xi-ping Feng, Desheng He, Zihai Duan
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Abstract

In order to enhance the mixing of gas and air in the afterburning chamber of the solid rocket ramjet and improve the combustion efficiency, a swirl mixing device placed at the inlet exit of the solid rocket ramjet is designed. The accuracy of the swirl flow field calculation method was verified by the cold flow test of the solid rocket ramjet with swirler. A velocity uniformity coefficient based on the axial velocity distribution in the afterburning chamber was proposed. The influence of different blade angles and blade numbers of the swirl device on the flow field in the solid ramjet was numerically simulated, and the velocity uniformity coefficient and the total pressure recovery coefficient were used to evaluate the mixing performance of the afterburning chamber. The results show that the improved swirler designed in this paper can reduce the total pressure loss in the afterburning chamber through structural optimization. The blade angle of the swirling device affects the mixing effect of the afterburning chamber. When the blade angle varies from -30 ° to 30 °, the maximum difference in mixing effect is 7.20%. The six blades swirl device with a blade angle of 20° has the best mixing performance to improve the afterburning chamber. The mixing performance can be improved by up to 4.30%, and the total pressure loss can be reduced by 1.70%.
旋流增强型固体火箭冲压发动机的混合性能
为了增强固体火箭冲压发动机加力燃烧室内气体与空气的混合,提高燃烧效率,设计了一种放置在固体火箭冲压发动机进气道出口的涡流混合装置。通过带旋流器的固体火箭冲压发动机冷流试验,验证了旋流场计算方法的准确性。提出了一种基于加力室轴向速度分布的速度均匀系数。数值模拟了旋流装置不同叶片角度和叶片数对固体冲压发动机流场的影响,并利用速度均匀系数和总压恢复系数来评价加力燃烧室的混合性能。结果表明,本文设计的改进型旋流器通过结构优化可以降低加力室的总压损失。旋流装置的叶片角度影响加力燃烧室的混合效果。当叶片角度在-30°~ 30°范围内变化时,混合效果的最大差异为7.20%。叶片角为20°的六叶旋流装置混合性能最好,改善了加力燃烧室。混合性能可提高4.30%,总压损失可降低1.70%。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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