为了探索在一定补燃室长度条件下进气道直径大小对固冲发动机内流场的影响,采用了标准k-∈湍流模型和组分输运模型数值模拟了一设计的固冲火箭发动机摻混燃烧过程的内流场。结果表明:在一定补燃室长度和进出口条件下,存在一最佳进气道直径,能使空气与燃气完全掺混燃烧。在文中模拟条件下的最佳进气道直径为30mm。

In order to research different diameters of air inlet pipe's influences to the inside flow field of a solid rocket ramjet engine on a certain length of the afterburning chamber, this paper simulated the mixing and burning conditions in the afterburning chamber of a designed solid rocket ramjet engine by using the standard k¯€ model and the species transport model. The results shows that under a certain length of the afterburning chamber and a certain in and out condition, there exists a corresponding diameter of the air inlet pipe, which can make the mixing and burning situation in the afterburning chamber best of all. Under the simulated condition in this paper the most suitable diameter is 30mm.