超声速燃烧室氢气强迫点火过程实验

推进技术 ›› 2012, Vol. 33 ›› Issue (4): 547-558.

超声速燃烧室氢气强迫点火过程实验

龚诚,孙明波,张顺平,梁剑寒

国防科学技术大学高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科学技术大学高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科学技术大学高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科学技术大学高超声速冲压发动机技术重点实验室,湖南长沙 410073

发布日期:2021-08-15
作者简介:龚诚(1986—),男,硕士生,研究领域为高超声速推进技术。E-mail:gongcheng0903@126.com
基金资助:
国家自然科学基金(91016028；50906098；91116001)。

Experimental Study on the Forced Ignition of Hydrogen in a Supersonic Combustor

Science and Technology on Scramjet Laboratory, National University of Defence Technology, Changsha 410073, China;Science and Technology on Scramjet Laboratory, National University of Defence Technology, Changsha 410073, China;Science and Technology on Scramjet Laboratory, National University of Defence Technology, Changsha 410073, China;Science and Technology on Scramjet Laboratory, National University of Defence Technology, Changsha 410073, China

Published:2021-08-15

摘要/Abstract

摘要： 模拟飞行Ma=4.0的超燃冲压发动机的燃烧室进口条件,在直连式试验台上对超燃冲压发动机氢气火花塞点火过程进行了研究。通过高速摄影与高速纹影捕捉了点火过程初始火焰发展与流程波系演化过程。结果表明,初始火焰传播受高速对流、湍流火焰传播和自点火多种机制控制,凹腔结构不仅提供低速环境,还在初始火焰传播过程中具有能量反馈和质量反馈(活化分子)作用,促进剪切层内火焰的发展。

关键词: 超燃冲压发动机;强迫点火;火花塞;氢气

Abstract: The spark ignition process of hydrogen was investigated in a direct-connect supersonic combustor. The entrance parameter of combustor corresponds to Scramjet flight Mach number 4.0. The spark ignition process was observed by the high speed camera and Schlieren system. Experimental results have shown that the process of the early flame is controlled by several different mechanism of high speed convection, turbulent flame propagation and self-ignition. The cavity does not only offer a low speed environment, but also forms a feedback mechanism of the heat and active radical species which promote the upstream propagation in the shear layer.

Key words: Scramjet; Forced ignition; Spark; Hydrogen

龚诚,孙明波,张顺平,梁剑寒. 超声速燃烧室氢气强迫点火过程实验[J]. 推进技术, 2012, 33(4): 547-558.