An Experimental Study on Shock Induced Combustion of Isolated Regions of Hydrogen-oxygen Mixtures PDF Download
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Author: Michael Anthony Valentino
Publisher:
ISBN:
Category :
Languages : en
Pages : 246
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Author: Michael Anthony Valentino
Publisher:
ISBN:
Category :
Languages : en
Pages : 246
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Author: M. Valentino
Publisher:
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Category :
Languages : en
Pages :
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Author: Donald Gustaf Stenmark
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ISBN:
Category : Combustion
Languages : en
Pages : 194
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 974
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ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 636
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Author:
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Category : Dissertation abstracts
Languages : en
Pages : 784
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Author: Reed W. Forehand
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ISBN:
Category :
Languages : en
Pages : 56
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Shock tubes are as close to an ideal reactor as most modern experiments can attain to examine chemical kinetics. As reaction temperatures drop, homogeneous combustion within a shock tube begins to exhibit inhomogeneous modes, which in a typical Hydrogen-Oxygen system are expressed as deflagration to detonation transition. Experimental results of such a system in the University of Central Florida’s low-pressure shock tube have been collected through end and side-wall imaging to analyze flame structure and chemical kinetics. The purpose of this work is to conduct a baselining of these results using both chemical and computational fluid dynamics modeling. The model will use the Siemens STAR-CCM+ computational fluid dynamics software in order to accurately simulate the system. A seven-step reaction mechanism will be used to accurately capture initialization, propagation, and termination of the combustion within an implicit unsteady, three-dimensional, direct eddy simulation solution on a well-conditioned mesh. The end goal of this study is to create a lightweight model of hydrogen-oxygen combustion with a shock tube for baselining purposes. Both a two- and three- dimensional model were applied in this effort. The simulation results indicate good conditioning and agreement with the experimental results, although some combustion phenomena are not captured as well as a higher fidelity, significantly more computationally expensive model would.
Author: K. P. Rickson
Publisher:
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Category :
Languages : en
Pages :
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 628
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 492
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