进气道流向伸缩对燃烧室入口总压恢复的影响

Impact of Air Inlet Flow Expansion on Total Pressure Recovery of Combustor Inlet

采用进气道流向伸缩的方法,对某高超声速飞行器进气道弯道及隔离段流场开展了数值模拟计算,获取了不同伸缩量对应的总压云图、马赫数云图和燃烧室入口总压恢复。通过对比发现,在Ma=5的巡航速度下,随着进气道向下游的伸展,燃烧室入口总压恢复系数呈现先升高后降低的趋势,当伸缩量为30mm时,燃烧室入口总压恢复系数可达到0.2484,比零偏移时提升了0.4%。通过对特定高超飞行器进气道采用流向伸缩的方法得到了最优总压恢复系数,为其他研究者在飞行器进气道优化设计方向提供了一种新型且有效的方法。

The flow field at the inlet elbow and isolator of a hypersonic vehicle was numerically simulated by using the inlet flow direction expansion method, and the total pressure contour, Mach number contour and the total pressure recovery at the inlet of the combustor corresponding to different expansion were obtained. By comparison, it is found that at the cruising speed of Ma=5, the total pressure recovery coefficient at the combustor inlet increases firstly and then decreases with the expansion of the inlet to the downstream. When the expansion is 30 mm, the total pressure recovery coefficient at the inlet of the combustor can reach 0.2484, which is 0.4% higher than that of the zero offset.The optimal total pressure recovery coefficient is obtained by using the method of flow direction expansion for a particular hypersonic vehicle inlet, which provides a new and effective method for other researchers in the direction of aircraft inlet optimization design.