采用不同航空煤油反应机理模拟模型燃烧室两相燃烧流场  

Numerical Simulation of Two-Phase Combustion Fields in a Model Combustor Using Two Different Chemical Reaction Mechanisms of Jet Fuel

作　　者：王慧汝 金捷[2] 

机构地区：[1]中国航空发动机研究院有限公司,北京100028 [2]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《燃气涡轮试验与研究》2013年第4期22-27,共6页Gas Turbine Experiment and Research

摘　　要：基于火焰面模型,采用两个不同的航空煤油化学反应机理(Kundu反应机理和亚琛反应机理),对模型燃烧室内三维两相燃烧流场进行了数值模拟,比较了两个反应机理燃烧流场计算结果的异同,并结合充分搅拌反应器模型进行了分析。通过与实验结果的比较,初步考察了两个反应机理模拟实际燃烧室燃烧流场的能力。结果表明:在给定工况条件下(工况1,马赫数0.160,来流温度537 K,总油气比0.004 8,常压;工况2,马赫数0.155,来流温度523 K,总油气比0.0100,常压),两个反应机理均能准确预测模型燃烧室的温度场和CO2排放量;亚琛反应机理在工况1时,可准确预测NO排放量,在工况2时,预测值高于实验值,而Kundu反应机理预测的NO排放量在两个工况下均与实验值差别较大。Based on flamelets model, three dimensional two phase combustion flowfields in a model combus-tor were simulated using two different chemical reaction mechanisms of jet fuel （Kundu mechanism and Aachen mechanism）. Similarities and differences of simulation results were compared and analyzed through simulations of perfectly stirred reactor. Meanwhile, the capability of reproducing combustion flowfields of the practical combustor with these two mechanisms was investigated by comparison with the experimental data. The results show that in the given conditions （condition1, inlet Mach 0.160, temperature 537 K, fuel-air ratio 0.004 8, atmospheric pressure;condition 2, inlet Mach 0.155, temperature 523 K, fuel-air ratio 0.010 0, atmo-spheric pressure）, temperature and CO2 emissions were accurately predicted by two mechanisms. Good predic-tion of NO emissions was obtained at condition 1 while overprediction at condition 2 by the Aachen mecha-nism. However, large discrepancies of calculated NO emissions and experimental data were observed by the Kundu mechanism at two conditions.

关 键 词：航空发动机燃烧室 火焰面模型 航空煤油 化学反应机理 充分搅拌反应器 两相燃烧 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]