冲压发动机高硅氧/酚醛燃烧室热防护层实验研究

推进技术 ›› 2013, Vol. 34 ›› Issue (1): 76-80.

冲压发动机高硅氧/酚醛燃烧室热防护层实验研究

李志永,郑日恒,李立翰,陈平,侯昊晟

中国航天科工集团三十一研究所高超声速冲压发动机技术重点实验室,北京 100074;中国航天科工集团三十一研究所高超声速冲压发动机技术重点实验室,北京 100074;中国航天科工集团三十一研究所高超声速冲压发动机技术重点实验室,北京 100074;中国航天科工集团三十一研究所高超声速冲压发动机技术重点实验室,北京 100074;西北工业大学航空学院,陕西西安 710072

发布日期:2021-08-15
作者简介:李志永(1975—),男,硕士,高级工程师,研究领域为冲压发动机被动热防护。E-mail:zhiylee@163.com

Experimental Investigation on Heat-Resistant Layer of High Silica Phenolic Composites in Ramjet Chamber

Science and Technology on Scramjet Laboratory,The 31st Research Institute of CASIC,Beijing 100074,China;Science and Technology on Scramjet Laboratory,The 31st Research Institute of CASIC,Beijing 100074,China;Science and Technology on Scramjet Laboratory,The 31st Research Institute of CASIC,Beijing 100074,China;Science and Technology on Scramjet Laboratory,The 31st Research Institute of CASIC,Beijing 100074,China;Aeronautics College,Northwestern Polytechnical University,Xi’an 710072,China

Published:2021-08-15

摘要/Abstract

摘要： 高硅氧/酚醛树脂基复合材料具有成型工艺简单和成本低的特点,被广泛地应作固体火箭发动机的防热材料。为了探索高硅氧/酚醛树脂基复合材料应用于冲压发动机燃烧室被动热防护结构,对高硅氧/酚醛树脂基复合材料大尺度冲压发动机燃烧室热防护层进行了实验研究。研究结果表明,冲压发动机燃烧室热防护层能工作到300s,高硅氧/酚醛热防护层能够适应其恶劣的工作环境要求。同时,通过实验研究也表明,更长工作时间之后,由于冲压发动机燃烧室工作温度的不均匀,导致酚醛树脂基体的分解与增强的高硅氧纤维熔融不同步,且热解、碳化后的形态和性能都会发生较大的变化,由此会导致其尺寸收缩、力学性能降低、导热系数增加,更长时间工作容易产生裂纹、分层等问题。针对这些问题,提出了进一步研究的建议。本项研究对于发展成型工艺简单和成本低的冲压发动机燃烧室热防护结构具有重要的价值。

关键词: 冲压喷气发动机;燃烧室;热防护;试验研究

Abstract: With the advantage of simple process and low cost, high silica phenolic composite has been used as SRM thermal protection material. In order to investigate its application in ramjet thermal protection, heat-resistant layer of high silica phenolic composites in large scale ramjet chamber has been designed and experimental studied. The results show that high silica phenolic composites is adaptive to work properly up to 300 seconds in the harsh environment of ramjet chamber. Due to non-uniform temperature distribution of ramjet chamber, phenolic carbonization is non-synchronous with high silica fiber fusion, and crack and delamination of heat-resistant layer of high silica phenolic composites after working longer time(＞300s) can occure.High silica phenolic composites form and performance changes greatly after pyrolysis and carbonization. For these problems, proposals are made and measures are suggested. This research is valuabe for simplifing process and reducing cost of the thermal structure in ramjet chamber.

Key words: Ramjet engine;Combustion chamber；Thermal protection; Experimental investigation

李志永,郑日恒,李立翰,陈平,侯昊晟. 冲压发动机高硅氧/酚醛燃烧室热防护层实验研究[J]. 推进技术, 2013, 34(1): 76-80.

参考文献

[1] 李志永,李立翰,郑日恒,等.针刺预制体分层对燃烧室C/C-SiC热防护结构的影响[J].推进技术,1,2(5).(LI Zhi-yong, LI Li-han, ZHENG Ri-heng,et al.Effects of Delemination of Needled Proform on Thermal Insulation of C/C-SiC Chamber[J].Journal of Propulsion Technology, 1,2(5).)
[2] 任加万,谭永华.冲压发动机燃烧室热防护技术[J].火箭推进,6,2(4).
[3] 郑日恒.冲压发动机技术的发展方向与评论[J].飞航导弹,2004,(1).
[4] 刘兴洲．飞航导弹动力装置[M] .北京:宇航出版社,1992.
[5] 刑继发.世界导弹与航天发动机大全[M] .北京:军事科学出版社,1999.
[6] 于翘.材料与工艺(下)[M] .北京:宇航出版社,1993.
[7] 李成功,傅恒志,于翘.航空航天材料[M].北京:国防工业出版社,2002.
[8] 王思民,周旭,何洪庆.高硅氧/酚醛喷管扩张段的温度场计算与测定[J].推进技术,1990,(5).(WANG Si-min, ZHOU Xu, HE Hong-qing.Calculation and Mesurement of Temperature Field in Silica Phenolics Lining of Divergent[J].Journal of Propulsion Technology, 1990,(5).)
[9] 蔡体敏,王思民.高硅氧增强塑料烧蚀模型中热解层厚度的探讨[J].推进技术,1989,(1).(CAI Ti-min, WANG Si-min.A Discussion on the Thickness of Pyrolysis Layer in the Ablation Model for Silica Phenolics Composites Material[J].Journal of Propulsion Technology, 1989,(5).)
[10] 徐善玮,侯晓,张宏安.固体火箭发动机内绝热层烧蚀质量损失计算[J].固体火箭技术,3,6(3).
[11] 孙冰,林小树,刘小勇.硅基材料烧蚀模型研究[J].宇航学报,2003,24(3) .
[12] 李敏剑,严聪.绝热层材料烧蚀机理与选材原则分析[J].飞航导弹,2009,9.
[13] 江伟辉,周健儿,胡行方,等.烧蚀防热材料的显微结构研究[J].无机材料学报,2002,17(6).
[14] 张宗强,匡松连,尚龙,等.树脂基复合材料长时间烧蚀防热的应用研究[J].宇航材料工艺,7,6.
[15] 闫联生,傅立坤,刘晓红.树脂基防热材料烧蚀性能表征的探讨[J].固体火箭技术,3,6(2).