轴对称结构RBCC燃烧室超燃模态燃烧性能研究 -- 西北工业大学,2014,32(1):29-34
论文:2014,Vol:32,Issue(1):29-34
引用本文:
汤祥, 何国强, 秦飞. 轴对称结构RBCC燃烧室超燃模态燃烧性能研究[J]. 西北工业大学
Tang Xiang, He Guoqiang, Qin Fei. Investigation on Combustion Performance of Axisymmetric RBCC Combustor in Scramjet Mode[J]. Northwestern polytechnical university

轴对称结构RBCC燃烧室超燃模态燃烧性能研究
汤祥, 何国强, 秦飞
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
摘要:
针对以支板火箭作为点火和火焰稳定源,燃料支板喷射燃料的轴对称结构RBCC燃烧室,采用数值模拟和直连试验的方法研究了不同燃烧室构型下燃料喷射方案的变化对超燃模态燃烧性能的影响。结果表明:在燃料支板结合壁面喷射方式下,随着燃料支板喷射量的增加,燃烧室的性能逐渐提升;燃料支板结合中心支板喷射方式下的燃烧性能要优于燃料支板结合壁面喷射的性能;凹腔的加入能在一定程度上促进燃料的燃烧,提升燃烧性能,其内推力是燃料支板结合后向台阶作用下的1.1倍;燃料支板高度的增加可增强燃料与空气的燃烧组织效果,燃烧室产生的推力能完全抵消支板高度增加带来的阻力损失。
关键词:    轴对称    RBCC    超燃模态    燃烧性能   
Investigation on Combustion Performance of Axisymmetric RBCC Combustor in Scramjet Mode
Tang Xiang, He Guoqiang, Qin Fei
Science and Technology on Combustion, Internal Flow and Thermal-structure Laboratory, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
The numerical simulation and direct-connection experiments were carried out to investigate the impact of the variation of injection schemes on the combustion performance of axisymmetric RBCC combustor with different configurations in scramjet mode,in which the strut-rocket was used as the means of ignition source and flameholding and the fuel was injected from the fuel-pylon. The results and their analysis indicated that:(1) the combustor performance upgraded gradually as the quantity of fuel-pylon injection increased in the manner of fuel-pylon injection with wall injection;(2) compared with the scheme of fuel injection of fuel-pylon and wall,the combination of fuel-pylon injection with central strut injection achieved higher combustion performance;(3) the joint of fuel-pylon with cavity could promote combustion and could get better combustion performance; thus the inner thrust is 1. 1 times as the thrust of fuel-pylon with rearward facing step;(4) the increase in the height of fuel-pylon enhanced the combustion organization between fuel and air while the thrust generated by combustor could offset the resistance loss of pylon completely.
Key words:    carbon dioxide    combustion    combustors    computer simulation    experiments    fuels    ignition    Mach number    oxygen    pressure    pressure distribution    ramjet engines    rockets    schematic diagrams    temperature distribution    axisymmetric    combustion performance    RBCC    scramjet mode   
收稿日期: 2013-04-23     修回日期:
DOI:
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作者简介: 汤祥(1987-),西北工业大学博士研究生,主要从事航空宇航推进理论与工程研究。
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