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CLC number: V43

On-line Access: 2020-10-15

Received: 2019-08-24

Revision Accepted: 2020-02-13

Crosschecked: 2020-07-15

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Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Yong-chao Sun

https://orcid.org/0000-0002-1825-9032

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Journal of Zhejiang University SCIENCE A 2020 Vol.21 No.10 P.848-858

http://doi.org/10.1631/jzus.A1900419


Numerical study on cavity ignition process in a supersonic combustor


Author(s):  Yong-chao Sun, Zun Cai, Tai-yu Wang, Ming-bo Sun, Cheng Gong, Yu-hui Huang

Affiliation(s):  Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China; more

Corresponding email(s):   caizun1666@163.com

Key Words:  Ignition process, Cavity, Supersonic combustor, Numerical study


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Yong-chao Sun, Zun Cai, Tai-yu Wang, Ming-bo Sun, Cheng Gong, Yu-hui Huang. Numerical study on cavity ignition process in a supersonic combustor[J]. Journal of Zhejiang University Science A, 2020, 21(10): 848-858.

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year="2020",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A1900419"
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%T Numerical study on cavity ignition process in a supersonic combustor
%A Yong-chao Sun
%A Zun Cai
%A Tai-yu Wang
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%A Cheng Gong
%A Yu-hui Huang
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T1 - Numerical study on cavity ignition process in a supersonic combustor
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A1 - Yu-hui Huang
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Abstract: 
Large eddy simulations (LESs) of cavity ignition processes were performed in a 2D ethylene-fueled supersonic combustor with a single rear-wall-expansion cavity based on OpenFOAM. The ethylene combustion was modelled using a 35-step with 20-specie ethylene chemical mechanism, which had been validated by CHEMKIN calculations. The effect on the ignition process of different ignition sites inside the cavity was then studied. It was found that the rear region of the cavity floor is an optimized ignition site where successful ignitions will be achieved. According to different ignition behaviors, two flame extinguishing modes could be identified: blown-off extinguishing mode and flow dissipation extinguishing mode. Blown-off extinguishing mode mainly occurred after ignition near the cavity shear layer, in which the initial flame was blown off directly due to the high speed of the supersonic core flow. Flow dissipation extinguishing mode is likely to occur after ignition near the front and middle cavity floor as a result of severe turbulent dissipations and limited chemical reactions. The study indicates that the movement routine of the initial flame is important for the ignition process, including both moving towards a favorable flow field and forming a large heat release region along the movement.

超声速燃烧室内凹腔点火过程的数值研究

目的:超燃冲压发动机的点火过程是超声速燃烧领域的重要课题之一.目前,针对超燃冲压发动机燃烧室点火过程的研究以实验研究为主,数值研究则相对较少.本文旨在基于大涡模拟研究点火位置对点火过程的影响,并在此基础上分析导致点火失败的原因.
创新点:1. 基于大涡模拟,研究点火位置对点火过程建立的影响; 2. 发现了流动耗散和直接吹熄两种熄火模式.
方法:1. 基于CHEMKIN,选择合适的化学反应机理; 2. 在简化化学反应机理的基础上,利用大涡模拟研究不同点火位置对点火过程的影响; 3. 分析数值仿真数据,寻找能成功实现点火的点火位置,并探讨导致点火失败的因素.
结论:1. 在凹腔后缘处点火可以成功实现发动机点火; 2. 发现了两种点火失败的模式,即流动耗散模式和直接吹熄模式; 3. 流动耗散模式主要发生在凹腔前缘和凹腔中部,而直接吹熄模式主要发生在剪切层中.

关键词:点火过程;凹腔;超声速燃烧室;数值模拟

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

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