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[1]徐唯栋,金平,蔡国飙.不均匀喷注对火箭发动机点火过程的影响研究[J].火箭推进,2018,44(05):21-31.
　XU Weidong,JIN Ping,CAI Guobiao.Effect of inhomogeneous injection on ignition process of rocket engine[J].Journal of Rocket Propulsion,2018,44(05):21-31.
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不均匀喷注对火箭发动机点火过程的影响研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 44 期数: 2018年05期 页码: 21-31 栏目: 研究与设计 出版日期: 2018-10-31
Title:
Effect of inhomogeneous injection on ignition process of rocket engine
文章编号:
1672-9374(2018)05-0021-11
作者:
徐唯栋; 金平; 蔡国飙
北京航空航天大学 宇航学院,北京 100191
Author(s):
XU Weidong; JIN Ping; CAI Guobiao
School of Astronautics, Beihang University, Beijing 100191, China
关键词:
喷注流量不均;  点火压力峰;  高空点火过程;  液氧/甲烷火箭发动机;  瞬态仿真
Keywords:
inhomogeneous injection;  ignition pressure peak;  ignition process of high altitude;  LOX/CH4 rocket engine;  transient simulation
分类号:
V434-34
文献标志码:
A
摘要:
高空点火瞬态过程是液氧/甲烷火箭发动机工作过程中流动非常复杂、燃烧很不稳定的阶段。为了验证喷注流量不均是否为导致点火压力峰升高的重要因素,采用瞬态仿真对该过程进行数值模拟。在无喷注不均的情况下,得到了推力室各特征截面的温度和压力分布的时序演化,以及推力室侧壁及喷注器面上给定测点的压力分布时序,揭示了高空点火过程中着火点的位置特征及压力波在喷注器面的振荡过程。接下来设置了喷注流量不均的多种工况,发现喷注流量不均不会改变推力室侧壁最大压力峰值,只是改变最大压力峰值位置,但却明显增强了压力波对喷注器面的冲击,尤其使以隔板为界的内圈喷嘴所受的平均最大压力峰值达到了推力室稳态压力的30倍,从而验证了喷注流量不均是引起点火烧蚀的一个重要因素。
Abstract:
The transient ignition process of high altitude is a very complicated stage with complex flow and unstable combustion in LOX/CH4 rocket engine.In order to verify whether the inhomogeneous injection is one of the most important reasons causing the increased high ignition pressure peak, the transient numerical method is used to simulate the process.Under the condition of homogeneous injection, the temporal evolutions of temperature and pressure distribution on each specified cross-section of the thrust chamber are obtained, as well as the temporal evolution of pressure at the given measuring points on the injection panel and the side-wall of thrust chamber.The position characteristics of ignition and the oscillation process of pressure wave on the injection panel are revealed during the high-altitude ignition process.Then, with different settings of inhomogeneous injection, it is found that the inhomogeneous injection does not change the maximum pressure peak on the side-wall of thrust chamber, but only changes its position.However, the impact of pressure wave on the injection panel is significantly enhanced.In particular, the average maximum pressure peak experienced by the inner ring nozzles bounded by the diaphragm reaches 30 times of steady pressure in the thrust chamber.Therefore, it is verified that the inhomogeneous injection is an important factor causing the ignition ablation.

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备注/Memo

收稿日期:2018-03-07
作者简介: 徐唯栋(1993—),男,硕士,研究领域为液氧/甲烷火箭发动机燃烧仿真

更新日期/Last Update: 1900-01-01