首页|天然气层流燃烧特性的实验与数值计算

天然气层流燃烧特性的实验与数值计算

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在定容弹中试验测量了压力分别为0.1、0.2、0.3 MPa,当量比范围为0.7~1.4,温度分别为300、350、400 K,O2体积分数分别为15%、18%、21%,CO2体积分数分别为0%、10%、20%,H2O体积分数分别为0%、10%、20%工况条件下天然气(0.9甲烷/0.07乙烷/0.03丙烷,摩尔分数)的火焰发展特性以及层流燃烧速度.同时,利用敏感性分析等方法构建了天然气的简化反应机理(40种组分和189个反应),并对其层流燃烧速度进行了数值计算.结果表明:当当量比由0.7提升至1.4时,天然气的层流燃烧速度先升高后降低,其峰值在当量比1.1附近;层流燃烧速度随着初始温度、O2体积分数的增多或初始压力、CO2及H2O体积分数的减少而逐渐得到提升.构建的天然气简化反应机理可以较好的预测层流燃烧速度随当量比变化的整体趋势;但是,部分工况下预测值略低于试验值.
Simulation and experiment on the laminar combustion characteristics of natural gas
The flame propagation characteristics and laminar combustion speeds of natural gas(0.9 methane/0.07 ethane/0.03 propane,mole fraction)were experimentally tested in the constant volume bomb under the conditions of the pressures of 0.1,0.2,0.3 MPa,the equivalence ratios range of 0.7-1.4,the temperatures of 300,350,400 K,the contents of O2 of 15%,18%,21%,the contents of CO2 and H2O of 0%,10%,20%.Meanwhile,the simplified reaction mechanism of natural gas(including 40 species and 189 reactions)was constructed by sensitivity analysis and other methods,and the laminar combustion speeds of natural gas were calculated numerically.The results showed that as the equivalent ratio increased from 0.7 to 1.4,the laminar combustion speeds of natural gas rose and then declined,and the peak appears near the equivalent ratio was 1.1;With the increase of initial temperature and the content of O2 or the decrease of initial pressure,the contents of CO2 and H2O,the laminar combustion speeds gradually increased.The simplified reaction mechanism of natural gas constructed hereto can better predict the overall trends of the laminar combustion speed with the equivalent ratio.However,the predicted values were slightly lower than the experimental values under certain conditions.

natural gaslaminar combustion speedconstant volume bombsimplified reaction mechanismsensitivity analysis

党嘉莹、曾文、陈潇潇、谷午、胡二江、马宏宇

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沈阳航空航天大学航空发动机学院,沈阳 110136

西安交通大学动力工程多相流国家重点实验室,西安 710049

中国航发沈阳发动机研究所,沈阳 110015

天然气 层流燃烧速度 定容弹 简化反应机理 敏感性分析

国家科技重大专项

2017-Ⅲ-0006-0031

2024

航空动力学报
中国航空学会

航空动力学报

CSTPCD北大核心
影响因子:0.59
ISSN:1000-8055
年,卷(期):2024.39(2)
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