Mixing and combustion characteristics in a cavity-based supersonic combustor with different injection schemes
Mixing and combustion characteristics in a cavity-based supersonic combustor with different injection schemes
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不同喷射方案腔式超音速燃烧室的混合与燃烧特性
DOI：
10.1016/j.actaastro.2019.02.012
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发表时间：
2019-06
影响因子：
3.5
通讯作者：
Yu Jiangfei
中科院分区：
文献类型：
--
作者：
Song Xiliang;Wang Hongbo;Sun Mingbo;Cai Zun;Liu Chaoyang;Yu Jiangfei
在低当量比条件下（来流马赫数Ma = 2.52，滞止压力P0 = 1.65 MPa，滞止温度T0 = 1600 K），对不同喷射方式下乙烯燃料超燃冲压发动机凹腔燃烧室的混合和燃烧特性进行了实验和数值研究。数值模拟得到的壁压分布与实验数据吻合较好。数值计算结果还表明，多孔情况下有更高的混合效率和燃烧效率比单孔情况。此外，在实验中观察到，火焰基座不稳定在一个固定的位置。在单孔情况下，火焰基在凹腔前缘和后缘之间剧烈振荡，并且在不同的喷射压力下，火焰基的振荡是相似的。在多孔情况下，火焰底部轻微振荡的空腔剪切层的前缘下游和振幅与较低的喷射压力大于那些与较高的喷射压力。
Mixing and combustion characteristics in an ethylene fueled cavity-based scramjet combustor with different injection schemes are investigated experimentally and numerically in low equivalence ratio conditions, with inflow conditions of Ma = 2.52, stagnation pressureP0= 1.65 MPa and stagnation temperatureT0= 1600 K. The wall-pressure distributions obtained by numerical simulations are in fairly good agreement with the experimental data. The numerical results also indicate that multiple-orifice cases have higher mixing efficiencies and combustion efficiencies than single-orifice cases. In addition, it is observed in the experiments that flamebases are not stabilized in a fixed position. In single-orifice cases, the flamebases oscillate dramatically between the cavity leading edge and trailing edge, and the oscillations are similar for different injection pressures. In multiple-orifice cases, the flamebases oscillate slightly in the cavity shear layer just downstream of the leading edge and the amplitudes with lower injection pressure are larger than those with higher injection pressure.
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DOI：
--
发表时间：
1997-04
期刊：
--
影响因子：
--
作者：
J. Bardina;P. Huang;T. Coakley
通讯作者：
J. Bardina;P. Huang;T. Coakley
后壁膨胀腔超燃冲压发动机燃烧室火焰稳定实验
影响因子：
7.2
作者：
Zun Cai;Xiaobin Zhu;Ming-Bo Sun;Zhenguo Wang
通讯作者：
Zhenguo Wang
影响因子：
1.9
作者：
E. T. Curran
通讯作者：
E. T. Curran
DOI：
10.1177/0954410014523744
发表时间：
2014-02
期刊：
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
影响因子：
--
作者：
Wei Huang
通讯作者：
Wei Huang
向后台阶双模式燃烧室混合与燃烧的数值探索
影响因子：
3.5
作者：
Huang, Wei;Li, Lang-quan;Liao, Lei
通讯作者：
Liao, Lei