Flame propagation and flashback characteristics in a kerosene fueled supersonic combustor equipped with strut/wall combined fuel injectors
Flame propagation and flashback characteristics in a kerosene fueled supersonic combustor equipped with strut/wall combined fuel injectors
复制标题
配备支柱/壁组合喷油器的煤油燃料超音速燃烧器中的火焰传播和闪回特性
DOI：
10.1016/j.ast.2019.105303
复制
发表时间：
2019
影响因子：
5.6
通讯作者：
Bao Wen
中科院分区：
文献类型：
--
作者：
Zhang Junlong;Chang Juntao;Wang Zi'ao;Gao Lin;Bao Wen
本文观察了液体煤油燃料超音速燃烧器中的火焰传播特性。采用支柱/壁联合喷油方案实现多级燃油喷射，并采用薄支柱作为火焰稳定器。在Ma=2.8的条件下进行了一系列实验和数值模拟。为了表征火焰传播过程中的火焰特性，采用高速摄影和压力测量来记录数据。在此基础上，分析了实验过程中火焰面积和马赫数分布的变化，并根据数值结果讨论了流场特性。结果表明，随着当量比的增大，核心火焰向主流扩散，火焰宽度增大。对火焰传播引起的芯焰和壁焰的火焰回火现象进行了检测和分析。然后，研究了超音速燃烧室中燃烧与流动的相互作用，并在此基础上揭示了火焰回火现象的机理。数值结果表明，边界层内回流区和低速区的产生是火焰回火的诱发机制。通过本文的研究，深入了解了超音速气流中的火焰传播过程，在此基础上可以进一步优化燃烧性能。
Flame propagation characteristics in a liquid kerosene fueled supersonic combustor were observed in this paper. The strut/wall combined fuel injection scheme was used to achieve the multi-staged fuel injection, and the thin strut was also adopted as the flame holder. A series of experiments and numerical simulations were carried out in the condition of Ma= 2.8. In order to represent the flame characteristics during the flame propagation process, high-speed photography and pressure measurement were taken to record the data. Based on the basic date, the variation of flame area and Mach number distributions during the experimental process were analyzed, and the flowing field characteristics were also discussed according to the numerical results. Results indicated that the core flame would diffuse to the primary flow with the increasing of equivalence ratio, enlarging the flame width. The flame flashback phenomenon of both core flame and wall flame, induced by the flame propagation, was detected and analyzed. Then, the interaction between combustion and flowing in the supersonic combustor was investigated, based on which, the mechanism of flame flashback phenomenon was also revealed. Numerical results showed that the generation of recirculation and low-speed region in boundary layer was the inducing mechanism of flame flashback. With the investigations in this paper, a depth understanding of the flame propagation process in supersonic airflow was achieved, based on which, a further optimization of combustion performance could be conducted.