Abstract The initiation and stabilization of detonation combustion of kerosene vapor in a supersonic air flow entering an expanding axisymmetric nozzle with a coaxial central body is numerically studied. Calculations are based on a reduced kinetic model of combustion, which includes 68 reactions for 44 components. Enthalpy and entropy of components are determined using approximating polynomials from the NASA database. A hydrodynamic model is based on two-dimensional unsteady Euler equations for an axisymmetric flow of a multicomponent reacting gas. Calculations are performed using the Godunov finite-difference scheme and its $$\beta$$ β -modification of improved accuracy on smooth solutions. The flow parameters that ensure the steady detonation combustion of kerosene vapor in the nozzle under consideration are determined. The detonation combustion of kerosene has higher thrust than hydrogen combustion, but is noticeably inferior with regard to specific thrust. The calculations are performed on the “Lomonosov" supercomputer at the Lomonosov Moscow State University.

中文翻译：

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煤油蒸汽在膨胀喷嘴中爆轰燃烧的数值模拟

摘要 数值研究了进入同轴中心体膨胀轴对称喷管的超音速气流中煤油蒸汽爆燃的引发和稳定问题。计算基于简化的燃烧动力学模型，其中包括 44 种组分的 68 次反应。组件的焓和熵是使用来自 NASA 数据库的近似多项式确定的。流体动力学模型基于多组分反应气体轴对称流动的二维非定常欧拉方程。计算是使用 Godunov 有限差分方案和它的 $$\beta$$ β - 改进平滑解的精度来执行的。确定了确保所考虑的喷嘴中煤油蒸汽稳定爆燃的流动参数。煤油爆轰燃烧的推力比氢燃烧大，但比推力明显较差。计算是在罗蒙诺索夫莫斯科国立大学的“罗蒙诺索夫”超级计算机上进行的。