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Preliminary analysis of scramjet engines based on engineering models

机译：基于工程模型的超燃冲压发动机的初步分析

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摘要

A mathematical model for analyzing two-dimensional scramjets was developed. The inlet was modeled with the oblique shockwave relationships. The combustor and nozzle were treated with quasi-one-dimensional flow assumption and finite rate chemistry was also considered for hydrogen-air combustion, with a separate mixing model. The viscous flow effects were taken into account estimating the skin friction coefficient and the heat flux through the walls. Experiments were used to validate the model, with overall good agreement. Next, numerical simulations were performed to study how selected flow properties vary as freestream velocity increases from 2.0 to 2.5 km/s, with a correspondent flight altitude of 30 km. Two baseline scramjet configurations were investigated, each one with a different combustor geometry. Firstly, fuel-air equivalence ratio effects were investigated. This study revealed that the equivalence ratio has a substantial influence on major combustor flow properties but only a moderate influence on ignition position. These effects were attenuated as freestream velocity increases. Following, comparisons were made between the two different scramjets considering the effects of the combustor geometry. Flow properties showed moderate changes between one configuration to another. The most pronounced difference was found in the maximum pressure position. Also, the differences found were attenuated as freestream velocity increases. (C) 2015 Elsevier Masson SAS. All rights reserved.
机译：建立了用于分析二维超燃冲压发动机的数学模型。入口是用倾斜冲击波关系建模的。对燃烧器和喷嘴进行了准一维流动假设处理，并且还考虑了氢气和空气燃烧的有限速率化学反应，并采用了单独的混合模型。考虑了粘性流动效应，以估计皮肤摩擦系数和通过壁的热通量。实验用于验证模型，总体上吻合良好。接下来，进行了数值模拟，以研究选定的流动特性如何随自由流速度从2.0增加到2.5 km / s而变化，相应的飞行高度为30 km。研究了两种基线超燃冲压发动机配置，每种配置都有不同的燃烧室几何形状。首先，研究了燃料-空气当量比的影响。这项研究表明，当量比对主要燃烧室的流动特性有很大的影响，而对点火位置的影响很小。这些影响随着自由流速度的增加而减弱。接下来，在两种不同的超燃冲压发动机之间进行了比较，考虑了燃烧室几何形状的影响。流动特性显示出一种配置与另一种配置之间的适度变化。在最大压力位置发现了最明显的差异。另外，发现的差异随着自由流速度的增加而减弱。 （C）2015 Elsevier Masson SAS。版权所有。

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  • 来源
    《Aerospace science and technology》 |2015年第12期|256-268|共13页
  • 作者

    Rolim Tiago C.; Toro Paulo G. P.;

  • 作者单位

    Inst Estudos Avancados, Div Aerotermodinam & Hiperson, BR-12228001 Sao Paulo, Brazil;

    Inst Estudos Avancados, Div Aerotermodinam & Hiperson, BR-12228001 Sao Paulo, Brazil;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Propulsion; Hypersonics; Scramjets;

    机译：推进;超人格;超燃冲压发动机;

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