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首页> 外文会议>1st International conference on green propellant for space propulsion >USE OF NATURAL GAS IN ROCKET PROPULSION
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USE OF NATURAL GAS IN ROCKET PROPULSION

机译：天然气在火箭推进中的应用

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摘要

The possibility of using Liquid Methane - Oxygen or Liquid Natural Gas - Oxygen for launcher propulsion systems is actually a very interesting alternative to the traditional propulsion system, both for their "green" propellants characteristics and the good performance they may provide. Another interesting issue, for which these propellants are looked at with interest, is the possibility of designing a new kind of completely reusable boosters.rnIn this paper, some results about the behaviour of these two propellants are presented. In particular, our attention is focused on the theoretical performance (i.e. ISP, T chamber, P chamber) as well as chemical behaviour, especially soot formation and production of policyclic aromatic compounds. Soot formation can occur due to cracking phenomena since liquid hydrocarbons may be used for engine cooling. This issue is a key point for the reusability of the system since coke deposition in the cooling system ducts can drastically increase the costs of refurbishment of reusable boosters. Moreover, cracking and soot formation inside the combustion chamber, due to poor reactants mixing, can increase radiative heat transfer. In the first part of this paper results about theoretical performance, obtained under the equilibrium hypothesis, will be presented. These computations are done using the NASA CEA400 code. We consider different chamber reactants temperature, pressure (i.e: 50, 75 and 100 arm, all over the critical pressure) and expansion ratio (ER=100,150,200, 250, 300). In the second part of the paper we are concerned about kinetic behaviour of the system in the combustion chamber. To do this, we use the CHEMKIN? and DSMOKE software tools. All the conditions considered in the equilibrium computations, are simulated again with these tools to assess the effect of finite-rate kinetics on chemistry.
机译：实际上，使用液态甲烷-氧气或液态天然气-氧气作为发射器推进系统的可能性实际上是传统推进系统的一种非常有趣的替代方法，因为它们具有“绿色”推进剂特性，并且可以提供良好的性能。有趣地研究这些推进剂的另一个有趣的问题是设计一种新型的完全可重复使用的助推器的可能性。本文提出了有关这两种推进剂性能的一些结果。特别是，我们的注意力集中在理论性能（即ISP，T室，P室）以及化学行为，尤其是烟灰的形成和多环芳族化合物的生产上。由于液态烃可用于发动机冷却，因此会因破裂现象而形成烟尘。这个问题是系统可重用性的关键点，因为冷却系统管道中的焦炭沉积会大大增加可重用增压器的翻新成本。此外，由于不良的反应物混合，在燃烧室内部的破裂和烟灰形成会增加辐射热传递。在本文的第一部分中，将介绍在平衡假设下获得的有关理论性能的结果。这些计算使用NASA CEA400代码完成。我们考虑不同的反应室反应物温度，压力（即在整个临界压力下分别为50、75和100臂）和膨胀比（ER = 100,150,200,250,300）。在本文的第二部分中，我们关注燃烧室中系统的动力学行为。为此，我们使用CHEMKIN？和DSMOKE软件工具。使用这些工具再次模拟平衡计算中考虑的所有条件，以评估有限速率动力学对化学的影响。

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  • 会议地点 Noordwijk(NL)
  • 作者

    F.Cuoco; C. Bruno;

  • 作者单位

    University of Rome "La Sapienza" Dep. of Mechanics and Aeronautics Via Eudossiana 18, 00184 Rome (Italy) Tel: **39 6 44585272, **39 6 44585280, Fax:**39 6 4881759 francesco@pcginevra.ing.uniroma1.it;

    rnUniversity of Rome "La Sapienza" Dep. of Mechanics and Aeronautics Via Eudossiana 18, 00184 Rome (Italy) Tel: **39 6 44585272, **39 6 44585280, Fax:**39 6 4881759 c.bruno(g),dma.ing.uniroma1.it;

  • 会议组织
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 空气动力学;
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