Combustion stabilizations in a liquid kerosene fueled supersonic combustor equipped with an integrated pilot strut
Combustion stabilizations in a liquid kerosene fueled supersonic combustor equipped with an integrated pilot strut
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配备集成先导支柱的液体煤油燃料超音速燃烧器中的燃烧稳定性
DOI：
10.1016/j.ast.2018.02.035
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发表时间：
2018-06
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;Shi Wen;Hou Wenxin;Bao Wen
对新设计的整体式先导杆进行了数值和实验研究。整体先导支板由两个相邻的浅空腔小支板组成，在超声速燃烧室中实现喷油和保焰。采用数值模拟方法对先导支板内流道内的流动特性进行了评价，结果表明，超声速燃烧室内流道内存在低速区，低速区局部等效比适合燃烧。然后，在Ma= 5、滞止状态T = 1270 K、P = 1.20 MPa的飞行条件下进行了一系列实验。实验结果表明，先导支板内部流道中产生先导火焰，在此基础上，从支板侧壁喷射的主燃料被点燃，在整个燃烧室中形成全局火焰。主燃料的燃烧导致在支柱出口处的热阻塞。此外，热阻塞有利于先导火焰的自稳定。采用先导支板持焰燃烧组织策略，使超声速燃烧室火焰全局稳定在0.15 ~ 0.75的较宽等效比范围内，并对不同等效比下的燃烧特性进行了分析。实验结果表明，采用带内腔先导支板的综合燃烧组织方法是可行的，并取得了良好的燃烧性能。
The numerical and experimental investigations have been conducted to test a newly designed integrated pilot strut. The integrated pilot strut consists of two neighboring small strut with shallow cavities, with the help of which, the fuel injection and flame holding are achieved in the supersonic combustor. The flowing characteristics in the internal flow duct of the pilot strut are evaluated with the numerical simulation method, results proving that a lower speed zone generates in the internal flow duct in the supersonic combustor and the local equivalence ratio in the low speed zone is suitable for combustion. Then, a series of experiments have been conducted in the flight condition of Ma= 5, with stagnation state T t= 1270 K, P t= 1.20 MPa. Experimental results show that a pilot flame generates in the internal flow duct of the pilot strut, based on which, the main fuel injected from the sidewall of the strut is ignited, and the global flame is established in the whole combustor. The combustion of the main fuel leads to a thermal chocking at the exit of the strut. Further, the thermal chocking is beneficial to the self-stabilization of the pilot flame. With the combustion organization strategy of the pilot strut flame holding, the global flame is stabilized in a wide range of equivalence ratio changing from 0.15 to 0.75 in the supersonic combustor, and the combustion characteristics in different equivalence ratios are analyzed in this paper. The integrated combustion organization approach by the pilot strut with internal cavities is demonstrated feasible and a high combustion performance is obtained.
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影响因子：
1.9
作者：
Nathan R. Grady;R. Pitz;C. Carter;K. Hsu;Chaitanya Godke;S. Menon
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作者：
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通讯作者：
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影响因子：
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作者：
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影响因子：
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作者：
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通讯作者：
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