固液混合发动机燃面退移速率提升途径研究进展  

Research Progress of Regression Rate Enhancement for Hybrid Rocket Motor

作　　者：刘林林[1] 李波标 王印 胡松启[1] LIU Lin-lin;LI Bo-biao;WANG Yin;HU Song-qi(Science and Technology on Combustion,Internal Flow and Thermo-Structure Laboratory,Northwestern Polytechnical University,Xi′an 710072,China)

机构地区：[1]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

出　　处：《推进技术》2022年第12期1-9,共9页Journal of Propulsion Technology

基　　金：国家自然科学基金(51976175,51606157)。

摘　　要：从经典的燃烧边界层理论出发,通过对高分子聚合物燃面退移速率理论表达式的讨论分析,提出降低固体燃料热分解气化所需热量和强化高温燃气向燃面传热均是燃面退移速率提升的技术途径,进而从燃料配方优化、燃气流动优化和采用液化燃料三个方面综述了国内外在燃面退移速率提升方法上所做的有益尝试,并对这些方法的优缺点进行了评述,可为后续燃面退移速率提升技术研究提供必要参考。Starting with the classical boundary layer of combustion theory,both decreasing the thermal decomposition energy and strengthening the heat transfer from high temperature combustion gases to burning surface were the efficient ways to improve regression rate based on the analysis of regression rate theoretical expression of polymer fuels in this paper.Then useful attempts to improve the regression rate at home and abroad were reviewed in terms of fuel formulation optimization,combustion gases flow optimization and using liquefying fuel,and the advantages and disadvantages of these methods were also discussed,which could provide a reference for the follow-up regression rate improvement studies.

关 键 词：固液混合发动机 燃面退移速率 高分子聚合物燃料 燃烧边界层 液化燃料 

分 类 号：V436[航空宇航科学与技术—航空宇航推进理论与工程]