激波管煤油燃料点火特性研究进展 *

推进技术 ›› 2018, Vol. 39 ›› Issue (7): 1455-1463.

激波管煤油燃料点火特性研究进展 *

姚峰,刘建忠,周禹男,何勇

浙江大学能源清洁利用国家重点实验室，浙江杭州 310027,浙江大学能源清洁利用国家重点实验室，浙江杭州 310027,浙江大学能源清洁利用国家重点实验室，浙江杭州 310027,浙江大学能源清洁利用国家重点实验室，浙江杭州 310027

发布日期:2021-08-15
作者简介:姚峰，男，硕士，研究领域为含能材料。 E-mail: yaofeng@zju.edu.cn 通讯作者:刘建忠，男，博士，教授，研究领域为能源清洁利用与高效转化。

Research Progresson Ignition Characteristicsof Kerosenein ShockTube

State Key Laboratory of Clean Energy Utilization，Zhejiang University，Hangzhou 310027，China,State Key Laboratory of Clean Energy Utilization，Zhejiang University，Hangzhou 310027，China,State Key Laboratory of Clean Energy Utilization，Zhejiang University，Hangzhou 310027，China and State Key Laboratory of Clean Energy Utilization，Zhejiang University，Hangzhou 310027，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究煤油的点火特性，国内外采用激波管实验方法，探究了不同因素对煤油的点火延迟时间的影响。本文综述了激波管煤油燃料点火特性研究进展，介绍了激波管的设计与实验要点以及液、气相煤油在激波管中点火特性的研究。结果表明，温度、压力、当量比等因素对煤油的点火特性有着复杂的影响，对目前研究中存在的问题与不足进行了归纳总结，对未来研究的重点进行展望。

关键词: 煤油；激波管；实验设计；点火特性；综述

Abstract: The influence of different factors on ignition delay time of kerosene was investigated in shocktube in order to study ignition characteristics of kerosene. Research progress of ignition characteristics of kerosenein shock tube was reviewed. First the key points of shock tube design and experiments were introduced，and then an overview of researches on ignition characteristics of kerosene droplet and kerosene vapor was covered. The re.sults of these studies show that the parameters related to the reaction kinetics，such as temperature，pressure andequivalence ratio have a complicated effect on ignition characteristics of kerosene. After summarizing the existingproblems and shortcomings in the researches，the perspectives in further works were also proposed.

Key words: Kerosene；Shock tube；Experimental design；Ignition characteristics；Review

姚峰,刘建忠,周禹男,何勇. 激波管煤油燃料点火特性研究进展 *[J]. 推进技术, 2018, 39(7): 1455-1463.

YAO Feng,LIU Jian-zhong,ZHOU Yu-nan,HE Yong. Research Progresson Ignition Characteristicsof Kerosenein ShockTube[J]. Journal of Propulsion Technology, 2018, 39(7): 1455-1463.

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