科研之友
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摘要
An assessment of the ignition characteristics of several silane/hydrogen combustion models under conditions that are relevant to hypersonic combustion applications is presented. Numerical predictions of silane/hydrogen ignition characteristics are compared to experimental measurements of explosion limits and shock-tube ignition delay times. Furthermore, the ignition properties of silane/hydrogen mixtures are evaluated at conditions extracted from representative streamlines calculated in a computational-fluid-dynamics simulation of a model scramjet configuration tested at the Alliant Techsystems/General Applied Science Laboratory at Mach 10. It is found that the analyzed silane chemical kinetic models are extremely sensitive to temperature and pressure at key combustor conditions. Moreover, the presence of many inconsistencies between experiments and chemical models show that the current knowledge of silane combustion pathways is not sufficient to perform accurate computational-fluid-dynamics simulations of hypersonic combustors. The uncertainties associated with many silane/hydrogen experiments suggest that new accurate measurements at relevant conditions are needed to improve the predictive properties of silane models.
- 出版日期2014-10
