分段式固体火箭发动机内部流动不稳定性数值分析

推进技术 ›› 2013, Vol. 34 ›› Issue (1): 95-100.

分段式固体火箭发动机内部流动不稳定性数值分析

王健儒,何国强,李强,晁侃

西北工业大学航天学院,陕西西安 710072;西北工业大学航天学院,陕西西安 710072;西北工业大学航天学院,陕西西安 710072;西安航天动力技术研究所,陕西西安 710025

发布日期:2021-08-15
作者简介:王健儒(1978—),男,博士生,高级工程师,研究领域为固体运载动力技术。E-mail:Wjr104zah@sina.com

Numerical Analysis of Flow Instability in Segmented SRM

College of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China;College of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China;College of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China;Xi’an Institute of Aerospace Propulsion, Xi’an 710025, China

Published:2021-08-15

摘要/Abstract

摘要： 采用大涡模拟技术,针对某分段式固体火箭发动机开展了发动机燃面退移0mm,160mm和280mm三个时刻下发动机燃烧室内部流动不稳定现象的数值分析,获得了三个典型时刻燃烧室内压强可能的振荡特性。计算结果表明,在发动机点火初期燃烧室内流动不稳定性主要由表面涡脱落导致；随着燃面的退移,端面限燃层暴露在燃气中,由于端面包覆结构残余的影响,燃烧室内流动不稳定性主要由障碍涡脱落决定,且与点火初期相比,压强振荡的频率逐步减小。 

关键词: 分段发动机;大涡模拟;流动不稳定;涡脱落

Abstract: In order to investigate the flow instability in a segmented SRM(solid rocket motor), numerical analyses based on LES(large eddy simulation) were carried out for a potential pressure oscillation characteristics in the chamber when the burning surface regression was at 0 mm, 160 mm and 280 mm,respectively. The numerical results indicate that initial stage flow instability is mostly caused by the parietal vortex-shedding in the chamber shortly after the motor firing. As the burning surface regresses continuously, the restrictors expose to the hot gases. The chamber flow instability is mostly induced by the obstacle vortex-shedding generated due to the effects of the residual annular thermal protection. Correspondingly, the frequency of pressure oscillation is decreased gradually as compared with that of initial stage. 

Key words: Segmented SRM; LES; Flow or aerodynamic instability; Vortex-shedding

王健儒,何国强,李强,晁侃. 分段式固体火箭发动机内部流动不稳定性数值分析[J]. 推进技术, 2013, 34(1): 95-100.

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