A 3D numerical study of LO2/GH2 supercritical combustion in the ONERA-Mascotte Test-rig configuration

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• 作者：Abdelkrim Benmansour ; Abdelkrim Liazid…
• 关键词：Rocket engine ; non ; premixed combustion ; supercritical regime ; H2 ; O2 flame ; transport properties
• 刊名：Journal of Thermal Science
• 出版年：2016
• 出版时间：February 2016
• 年：2016
• 卷：25
• 期：1
• 页码：97-108
• 全文大小：1,660 KB
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• 作者单位：Abdelkrim Benmansour (1)
  Abdelkrim Liazid (1)
  Pierre-Olivier Logerais (2)
  Jean-Félix Durastanti (2)
  
  1. Laboratory LTE, ENP-Oran, BP 1523, El Mnaouer Oran, 31000, Algeria
  2. Université de Paris-Est, CERTES, IUT de Sénart, rue Georges Charpak, 77567, Lieusaint, France
  
• 刊物类别：Physics and Astronomy
• 刊物主题：Physics
  Mechanics, Fluids and Thermodynamics
  Engineering Fluid Dynamics
  Engineering Thermodynamics and Transport Phenomena
  Chinese Library of Science
  
• 出版者：Science Press, co-published with Springer-Verlag GmbH
• ISSN：1993-033X

文摘

Cryogenic propellants LOx/H2 are used at very high pressure in rocket engine combustion. The description of the combustion process in such application is very complex due essentially to the supercritical regime. Ideal gas law becomes invalid. In order to try to capture the average characteristics of this combustion process, numerical computations are performed using a model based on a one-phase multi-component approach. Such work requires fluid properties and a correct definition of the mixture behavior generally described by cubic equations of state with appropriated thermodynamic relations validated against the NIST data. In this study we consider an alternative way to get the effect of real gas by testing the volume-weighted-mixing-law with association of the component transport properties using directly the NIST library data fitting including the supercritical regime range. The numerical simulations are carried out using 3D RANS approach associated with two tested turbulence models, the standard k-Epsilon model and the realizable k-Epsilon one. The combustion model is also associated with two chemical reaction mechanisms. The first one is a one-step generic chemical reaction and the second one is a two-step chemical reaction. The obtained results like temperature profiles, recirculation zones, visible flame lengths and distributions of OH species are discussed. Keywords Rocket engine non-premixed combustion supercritical regime H2-O2 flame transport properties