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硼粒子直径对点火位置及燃烧效率的影响研究
引用本文:霍东兴,陈林泉,刘霓生,叶定友.硼粒子直径对点火位置及燃烧效率的影响研究[J].固体火箭技术,2004,27(4):272-275.
作者姓名:霍东兴  陈林泉  刘霓生  叶定友
作者单位:中国航天科技集团公司四院,西安,710025
基金项目:国家重点实验室基金资助项目(00JS60.3.3.HT4101).
摘    要:采用颗粒轨道模型对非壅塞固冲发动机补燃室内不同直径硼粒子的点火及燃烧进行了数值模拟。其中,气相反应简化为一种等效气体的燃烧,硼粒子与O2的燃烧反应模型采用涡耗散模型。硼粒子的点火过程采用King模型,燃烧过程采用化学动力学控制的燃烧模型。结果表明,直径较小的硼粒子能够在补燃室头部点火,且能随气流旋转,驻留时间较长,燃烧较为充分,直径较大的硼粒子与此相反。

关 键 词:固体火箭冲压发动机  补燃室  硼粒子  两相流  燃烧流场
文章编号:1006-2793(2004)04-0272-04
修稿时间:2004年10月9日

Effects of boron particles diameter on ignition position and combustion efficiency
Abstract:Ignition and combustion processes of boron particles with different diameters in unchoked solid rocket ramjets were simulated by the particle trajectory model. The gas phase of fuel-gas was simplified as an equivalent combustible gas, and the reaction rate with O_2 was calculated by the eddy-dissipation model. The processes of ignition and the combustion of boron particles were modeled by King model and kinetic-limited rate model respectively. The results show that the smaller particles can be ignited in the head-end of afterburning chamber, the combustion of the smaller particles is sufficient because of their rotation and long residence time. The performances of the larger particles are opposite to these results.
Keywords:solid rocket ramjet  afterburning chamber  boron particles  two-phase flow  combustion flow field
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