Effects of gas state equation on n-dodecane jet combustion

QIN Wenjin; LU Dengbiao; LIU Hao

doi:10.13224/j.cnki.jasp.2020.01.008

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Effects of gas state equation on n-dodecane jet combustion

更新时间：2026-07-07

- Effects of gas state equation on n-dodecane jet combustion
- Vol. 35, Issue 1, Pages: 66-74(2020)
- 作者机构：
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2020.01.008
  CLC：
- Published：2020
- 稿件说明：
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秦文瑾, 卢登标, 刘浩. 气体状态方程对正十二烷射流燃烧的影响[J]. 航空动力学报, 2020, 35(1): 66-74.

doi: 10.13224/j.cnki.jasp.2020.01.008
秦文瑾, 卢登标, 刘浩. 气体状态方程对正十二烷射流燃烧的影响[J]. 航空动力学报, 2020, 35(1): 66-74. DOI： 10.13224/j.cnki.jasp.2020.01.008.

doi: 10.13224/j.cnki.jasp.2020.01.008 DOI：

摘要

选取正十二烷作为航空煤油的替代燃料，应用大涡数值模拟方法和详细化学反应动力学相结合的方法对该燃料在超临界环境下的射流燃烧进行计算，研究其射流、燃烧及排放特性。重点考察了气体状态方程对射流形态、贯穿距、温度、混合分数等的影响。结果表明:理想气体和真实气体状态方程对仿真得到的射流贯穿距和宏观形态影响不大，而真实气体状态方程可以更好地反映在超临界环境下的液体燃料射流内部特征，如混合分数、温度；燃烧方面，仿真的点火延迟与实验存在10%的误差，火焰浮起长度、火焰形态、碳烟等均得到很好的预测，NOx与OH分布与温度场具有高度一致性。

Abstract

The n-dodecane was selected as an alternative fuel of aviation kerosene in this study. Its jet combustion characteristics under supercritical condition were studied by using large eddy simulation and detailed chemical reaction kinetics. The effects of gas state equations on jet morphology

penetration

temperature

and mixing fraction were also investigated. The simulation results showed that ideal gas and real gas state equations had negligible effect on the jet penetration and macroscopic shape

while the real gas state equation had advantage to reflect the liquid fuel jet characteristics under supercritical condition

such as mixing fraction and temperature. In terms of combustion

there was an error of 10% between the simulated ignition delay and the experiment

the flame lift-off length

flame shape and soot were also well predicted

and the distribution of NOx and OH was highly consistent with the temperature field.

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Large eddy simulation of cryogenic jet under supercritical pressure based on OpenFOAM

Analysis of n⁃dodecane spray jet by proper orthogonal decomposition

Large eddy simulation on the staggered tube bundle of the compact precooler

Study on opposed mixing flow in circumferential intake

引用格式：王庆宇,刘琪麟,赖焕新.高亚声速喷流近场的流-声关联［J］.航空动力学报,2020,35(12):2532-2542.WANG Qingyu,LIU Qilin,LAI Huanxin.Flow-acoustics correlations in near-fields of high subsonic jet［J］.Journal of Aerospace Power,2020,35(12):2532-2542.Flow-acoustics correlations in near-fields of high subsonic jet

Related Author

Yuhang LI

Baoyuan WU

Yi WANG

Lixin ZHOU

Wenjin QIN

Lihui XU

Dengbiao LU

Hao LIU

Related Institution

National Key Laboratory of Science and Technology on Liquid Rocket Engines，Xi'an Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation

Academy of Aerospace Propulsion Technology，China Aerospace Science and Technology Corporation

Beijing Aerospace Institute for Metrology and Measurement Technology， China Academy of Launch Vehicle Technology， China Aerospace Science and Technology Corporation

School of Mechanical Engineering， University of Shanghai for Science and Technology

Research Institute of Aero-engine,Beijing University of Aeronautics and Astronautics

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