Numerical investigation of the auto-ignition of transient hydrogen injection in supersonic airflow

Bing Liu; Jian An; Fei Qin; Guo Qiang He; Duo Zhang; Su li Wu; Lei Shi; Rui Li

doi:10.1016/j.ijhydene.2019.07.215

Numerical investigation of the auto-ignition of transient hydrogen injection in supersonic airflow

Bing Liu, Jian An, Fei Qin, Guo Qiang He, Duo Zhang, Su li Wu, Lei Shi, Rui Li

School of Astronautics

Research output: Contribution to journal › Article › peer-review

23 Scopus citations

Abstract

The auto-ignition process in high Mach number airflow is performed by Large Eddy Simulation. The predictions are in good agreement with experiment. The temporal and spatial analysis of the auto-ignition process are carried out. The results show that the auto-ignition process can be divided into five stages in terms of time sequence, and there are three regions in space at the steady state. It is also found that the maximum mass fraction of HO₂ is one of the best indicators to see whether the scramjet working on high Mach number reaches steady state, and the flame stabilization is dominated by auto-ignition. The heat release rate of different combustion modes is calculated. It reveals that the supersonic combustion mode dominates in all stages and regions, but premixed combustion mode dominates only in transient auto-ignition stage and the auto-ignition region.

Original language	English
Pages (from-to)	25042-25053
Number of pages	12
Journal	International Journal of Hydrogen Energy
Volume	44
Issue number	45
DOIs	https://doi.org/10.1016/j.ijhydene.2019.07.215
State	Published - 20 Sep 2019

Keywords

Heat release rate
Large eddy simulation
Supersonic flow
Transient auto-ignition

UN SDGs

This output contributes to the following UN Sustainable Development Goals (SDGs)

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10.1016/j.ijhydene.2019.07.215

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title = "Numerical investigation of the auto-ignition of transient hydrogen injection in supersonic airflow",

abstract = "The auto-ignition process in high Mach number airflow is performed by Large Eddy Simulation. The predictions are in good agreement with experiment. The temporal and spatial analysis of the auto-ignition process are carried out. The results show that the auto-ignition process can be divided into five stages in terms of time sequence, and there are three regions in space at the steady state. It is also found that the maximum mass fraction of HO2 is one of the best indicators to see whether the scramjet working on high Mach number reaches steady state, and the flame stabilization is dominated by auto-ignition. The heat release rate of different combustion modes is calculated. It reveals that the supersonic combustion mode dominates in all stages and regions, but premixed combustion mode dominates only in transient auto-ignition stage and the auto-ignition region.",

keywords = "Heat release rate, Large eddy simulation, Supersonic flow, Transient auto-ignition",

author = "Bing Liu and Jian An and Fei Qin and He, {Guo Qiang} and Duo Zhang and Wu, {Su li} and Lei Shi and Rui Li",

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year = "2019",

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doi = "10.1016/j.ijhydene.2019.07.215",

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T1 - Numerical investigation of the auto-ignition of transient hydrogen injection in supersonic airflow

AU - Liu, Bing

AU - An, Jian

AU - Qin, Fei

AU - He, Guo Qiang

AU - Zhang, Duo

AU - Wu, Su li

AU - Shi, Lei

AU - Li, Rui

PY - 2019/9/20

Y1 - 2019/9/20

N2 - The auto-ignition process in high Mach number airflow is performed by Large Eddy Simulation. The predictions are in good agreement with experiment. The temporal and spatial analysis of the auto-ignition process are carried out. The results show that the auto-ignition process can be divided into five stages in terms of time sequence, and there are three regions in space at the steady state. It is also found that the maximum mass fraction of HO2 is one of the best indicators to see whether the scramjet working on high Mach number reaches steady state, and the flame stabilization is dominated by auto-ignition. The heat release rate of different combustion modes is calculated. It reveals that the supersonic combustion mode dominates in all stages and regions, but premixed combustion mode dominates only in transient auto-ignition stage and the auto-ignition region.

AB - The auto-ignition process in high Mach number airflow is performed by Large Eddy Simulation. The predictions are in good agreement with experiment. The temporal and spatial analysis of the auto-ignition process are carried out. The results show that the auto-ignition process can be divided into five stages in terms of time sequence, and there are three regions in space at the steady state. It is also found that the maximum mass fraction of HO2 is one of the best indicators to see whether the scramjet working on high Mach number reaches steady state, and the flame stabilization is dominated by auto-ignition. The heat release rate of different combustion modes is calculated. It reveals that the supersonic combustion mode dominates in all stages and regions, but premixed combustion mode dominates only in transient auto-ignition stage and the auto-ignition region.

KW - Heat release rate

KW - Large eddy simulation

KW - Supersonic flow

KW - Transient auto-ignition

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SN - 0360-3199

VL - 44

SP - 25042

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JO - International Journal of Hydrogen Energy

JF - International Journal of Hydrogen Energy

IS - 45

ER -

Numerical investigation of the auto-ignition of transient hydrogen injection in supersonic airflow

Abstract

Keywords

UN SDGs

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