Adaptive Mesh Encryption Method For Block Structure And Its Application In Initiation Propagation Of Supersonic Combustible Gas

This paper studied the detonation initiation with hot jet in supersonic combustiable mixtures with a combination of numerical simulation and experimental method, for the research purpose of detonation initiation with hot jet in scramjet combustors. The open-code programme AMROC of block-structured adaptive mesh refinement method was adopted for the further development and a small-scale nested parallel system was established to realize the two-dimension numerical simulation of detonation initiation with hot jet in supersonic combustiable mixtures.Two-dimension numerical simulation of detonation initiation with hot jet in supersonic combustiable mixtures was investigated and at the same time a comparison research was set up of detonation initiation with hot jet in static combustiable mixtures. With the help of muture knowledge of detonation combustion in static gas, the phenomenon in detonation initiation with hot jet in supersonic combustiable mixtures should be analyzed easily.The whole process of detonation initiation with hot jet in static combustiable mixtures was investigated by the numbers through the two-dimension numerical simulation.At the same time the calculation considered the effects of various parameters,including the diameter of hot-jet tube, the highness of pipeline and the distance between the hot-jet tube and the left wall and the rules of detonation initiation with hot jet in static combustiable mixtures under the condition of various parameters were gained. The whole process of detonation initiation with hot jet in supersonic combustiable mixtures was investigated by the numbers through the two-dimension numerical simulation.At the same time the calculation considered the effects of various parameters,including the diameter of hot-jet tube, the highness of pipeline and the rules of detonation initiation with hot jet in supersonic combustiable mixtures under the condition of various parameters were gained. The parameter of time was added to the boundary condition to contronl the hot jet to realize detonation reinitiation.The rule of detonation reinitiation and stabilizing control of hot jet in supersonic combustiable mixtures was found. The programme of block-structured adaptive mesh refinement method was adoptd to realize the precise simulation in multi-level grid.Some precise structures in the combustion field were found. Detonation initiation with hot jet in supersonic combustiable mixtures was investigated with high-speed schileren equipment and the phenomenon of boundary layer seperation was found because of the viscosity.