长时间小过载条件下发动机流场特征及绝热层烧蚀分析

推进技术 ›› 2013, Vol. 34 ›› Issue (8): 1071-1076.

长时间小过载条件下发动机流场特征及绝热层烧蚀分析

刘洋¹,吴育飞¹,李江¹,何国强¹,张仁军²,王善金²

西北工业大学燃烧、热结构与内流场重点实验室,陕西西安 710072;西北工业大学燃烧、热结构与内流场重点实验室,陕西西安 710072;西北工业大学燃烧、热结构与内流场重点实验室,陕西西安 710072;西北工业大学燃烧、热结构与内流场重点实验室,陕西西安 710072;中国航天科工集团第九总体研究部,湖北武汉 430040;中国航天科工集团第九总体研究部,湖北武汉 430040

发布日期:2021-08-15
作者简介:刘洋 (1979—),男,博士,副教授,研究领域为固体火箭发动机燃烧、流动和热结构。E-mail:liuyang802@nwpu.edu.cn
基金资助:
国家自然科学基金资助项目NSFC(51276150)。

Flow Field and Ablation Mode Analysis of Insulator under Low Acceleration with Long Operation Time Conditions for Solid Rocket Motor

Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory,Northwestern Polytechnical University,Xi’an 710072,China;Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory,Northwestern Polytechnical University,Xi’an 710072,China;Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory,Northwestern Polytechnical University,Xi’an 710072,China;Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory,Northwestern Polytechnical University,Xi’an 710072,China;The 9th Design Department of China Aerospace Science & Industry Corporation, Wuhan 430040,China;The 9th Design Department of China Aerospace Science & Industry Corporation, Wuhan 430040,China

Published:2021-08-15

摘要/Abstract

摘要： 以揭示固体火箭发动机在飞行条件下绝热层的异常烧蚀特性为目的,针对小过载、长作用时间条件下大长径比流道的发动机开展了三维两相流场的数值模拟研究,详细分析了发动机内流道内不同区域的颗粒聚集特征,并结合发动机失效部位处绝热层的烧蚀形貌进行了失效模式分析,针对性地提出了改进措施。研究结果表明:(1)不同过载条件下发动机内颗粒聚集和分布状态受过载大小和发动机流道结构共同作用且影响规律复杂,所引起的绝热层异常烧蚀模式和机理不同,特别是小过载长作用时间条件下的异常烧蚀需要引起设计者重视。(2)颗粒聚集在绝热层表面的换热或冲蚀都将引起绝热层局部烧蚀加剧,形成的“凹坑或凹槽”烧蚀形貌会造成颗粒的二次聚集效应,进而加剧烧蚀过程。(3)通过增加发动机旋转动作和局部绝热层加厚,可以提高发动机的飞行安全性。 

关键词: 固体火箭发动机;绝热层;烧蚀;高过载 

Abstract: Focusing on the abnormal ablation of insulator of the solid rocket motor under flight condition, the three-dimensional two phase numerical simulation of a certain larger long diameter ratio tactical missile solid rocket motor under low acceleration-long duration condition was carried on. And the two phase flow characteristic of different area in the solid rocket motor flow path was analyzed. According to the ablation profiles of insulator and the detail of flow characteristic near the failure point, the insulator ablation characteristic and disabled mode were discussed and some improvment methods were brought forward. The results show that:(1) The particle concentration distribution and two phase flow characteristic in the solid rocket motor are decided by the acceleration direction and magnitude as well as geometry feature of flow path jointly. Then the ablation mechanism and failure mode are complicated and the abnormal ablation of insulator under low acceleration short duration condition must be considered. (2) The aggradation of particles on the insulator surface results in the forced heat transfer and particle erosion promotes ablation of insulator. And the groove and concave on the insulator surface resulting from particle erosion may focalize the particles and quicken the insulator ablation farther. (3) By making the solid rocket motor spinning or thickening the insulator locally, the flight safety can be improved. 

Key words: Solid propellant rocket motor (SRM); Insulator; Ablation; High acceleration

刘洋,吴育飞,李江,何国强,张仁军,王善金. 长时间小过载条件下发动机流场特征及绝热层烧蚀分析[J]. 推进技术, 2013, 34(8): 1071-1076.

LIU Yang¹, WU Yu-fei¹, LI Jiang¹, HE Guo-qiang¹, ZHANG Ren-jun², WANG Shan-jin². Flow Field and Ablation Mode Analysis of Insulator under Low Acceleration with Long Operation Time Conditions for Solid Rocket Motor[J]. Journal of Propulsion Technology, 2013, 34(8): 1071-1076.

参考文献

[1] Jayant S Sabnis, Frederik Jde Jong, Howard J Gibeling.Calculation of Particle Trajectories in Solid-Rocket Motors with Arbitrary Acceleration[J].Journal of Propulsion and Power,1992,8(5).
[2] 何国强,王国辉,蔡体敏,等.过载条件下固体发动机内流场数值模拟[J].推进技术,2002,3(3),182-185.(HE Guo-qiang, WANG Guo-hui, CAI Ti-min, et al.Numerical Simulation on 3-D Two-Phase Flow Field in SRM with Acceleration Load[J].Journal of Propulsion Technology,2002,3(3),182-185.)
[3] 李江, 何国强, 秦飞,等.高过载条件下绝热层烧蚀实验方法研究(I)方案论证及数值模拟[J].推进技术, 2003,4(6):315-318.(LI Jiang, HE Guo-qiang, QIN Fei,et al.Study of Experimental Method for Ablation of Insulation of SRM with Acceleration (I)[J].Journal of Propulsion Technology, 2003,4(6):315-318.)
[4] 李江, 何国强, 陈剑,等.高过载条件下绝热层烧蚀实验方法研究(II)收缩管聚集法[J].推进技术, 2004,5(2):196-198.(LI Jiang, HE Guo-qiang, CHEN Jian, et al.Study of Experimental Method for Ablation of Insulation of SRM with Acceleration (II) Convergent Tube Experimental Method[J].Journal of Propulsion Technology, 2004,5(2):196-198.)
[5] 刘洋.高过载固体发动机内流场模拟试验技术[D].西安:西北工业大学, 2004.
[6] 李江, 刘洋, 娄永春, 等.颗粒冲刷对绝热层烧蚀影响的实验研究 [J].推进技术,2006,7(1):71-74.(LI Jiang, LIU Yang, LOU Yong-chun,et al.Experimental Investigation for the Influence of Particle on Insulation Erosion[J].Journal of Propulsion Technology, 2006,7(1):71-74.)
[7] 刘洋,李江,何国强,等.颗粒冲刷条件下三元乙丙绝热材料烧蚀特性实验[J].推进技术, 2010,1(5):612-617.(LIU Yang, LI Jiang, HE Guo-qiang,et al.Experiment on Ablation Characteristic of EPDM Insulator under Particles Erosion Condition[J].Journal of Propulsion Technology,2010,1(5):612-617.)
[8] 刘洋,李江, 杨飒,等.过载条件下三元乙丙绝热材料烧蚀机理和模型研究(I):烧蚀机理分析[J].固体火箭技术, 2011,4(2):229-233.
[9] 杨飒, 何国强, 李江,等.模拟过载条件下EPDM绝热材料烧蚀模型(II):考虑炭层孔隙结构的颗粒侵蚀模型 [J].固体火箭技术, 2011,4(3):349-353.
[10] 刘洋, 何国强, 李江,等.聚集状态下凝相颗粒的收集与测量[J].推进技术,2005,6(5):477-480.(LIU Yang, HE Guo-qiang, LI Jiang,et al.Collection and Measurement Condensed Particle under Aggregation Condition[J].Journal of Propulsion Technology, 2005,6(5):477-480.)