THERMOCHEMICAL EXPLORATION OF A CAVITY BASED SUPERSONIC COMBUSTOR WITH LIQUID KEROSENE FUEL

P. Manna; Ramesh Behera; Debasis Chakraborty

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THERMOCHEMICAL EXPLORATION OF A CAVITY BASED SUPERSONIC COMBUSTOR WITH LIQUID KEROSENE FUEL

机译：液态煤油燃料的基于腔的超音速燃烧器的热化学探索

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Thermochemical exploration of a liquid hydrocarbon fueled scram jet combustor is presented. Three dimensional Navier Stokes equations alongwith K-ε turbulence model and single step kerosene-air reaction kinetics are solved using commercial software. Various combustor configurations with different fuel injection cavities are analyzed. Simulations capture all the essential features of the flow field. Good comparisons between computational and experimental surface pressure form the basis for further analysis. Parametric studies have been carried out with different droplet diameters to study its effect in the flow development. The numerical simulation also confirmed the experimental observation that the threshold value of length-to-depth ratio for cavity characterization is different for reacting and non-reacting flows.

机译：提出了一种液态碳氢燃料的急燃式燃烧室的热化学探索。使用商业软件求解了三维Navier Stokes方程以及K-ε湍流模型和单步煤油-空气反应动力学。分析具有不同燃料喷射腔的各种燃烧器构造。模拟捕获了流场的所有基本特征。计算和实验表面压力之间的良好比较构成了进一步分析的基础。已经用不同的液滴直径进行了参数研究，以研究其在流动发展中的作用。数值模拟也证实了实验观察，用于表征腔的长度与深度之比的阈值对于反应流和非反应流是不同的。

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来源
《Journal of Aerospace Sciences and Technologies》 |2007年第4期|p.246-258|共13页
作者
P. Manna; Ramesh Behera; Debasis Chakraborty;
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作者单位

Computational Combustion Dynamics Division, Directorate of Computational Dynamics, Defence Research and Development Laboratory (DRDL), Kanchanbagh Post, Hyderabad-500 058, India;

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原文格式 PDF
正文语种 jpn
中图分类航天（宇宙航行）;
关键词
scramjet; cavity; liquid injection; upstream interaction;

机译：超燃冲压;腔;注液;上游相互作用;

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THERMOCHEMICAL EXPLORATION OF A CAVITY BASED SUPERSONIC COMBUSTOR WITH LIQUID KEROSENE FUEL

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