摘要
在两相流模型基础上建立了固冲发动机掺混段上硅基绝热层的冲蚀模型。对某一工况下的某型进气道发动机补燃室的冲蚀率进行了计算。为了减弱燃气流的烧蚀影响,对发动机提出了两种改型设计方案,通过影响相邻进气道之间的流场改善发动机的局部烧蚀状况。数值模拟结果表明在轴向上存在距离差的前后布置的进气道间,后进气道两侧的烧蚀较前进气道严重。另一方面,适当提高空气出口速度可以减小发动机的气动冲蚀效应。
The insulator, in ramjet＇ s afterburning chamber, works in a serious condition. Its ablation model has been established based on two-phase-flow model. With this model, a ramjet interior flow field has been numerically simulated under a certain working condition. In order to improve insulator performance, two methods has been argued. Compared with the numerical simulation results of these methods, it is found that the distance between two neighbor inlets affects ablation rate and this makes the insulator by side of backward inlet be more seriously ablated than insulator around forward inlet. On the other side, the numerical simulation result shows that a certain velocity enhancement of air would alleviate the insulator ablation.
出处
《弹箭与制导学报》
CSCD
北大核心
2012年第3期125-128,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
作者简介
李理（1983-），男，四川彭州人，博士研究生，研究方向：固体火箭冲压发动机流场仿真。
