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首页> 外文会议>AIAA applied aerodynamics conference;AIAA aviation forum >Influence of near-leading edge curvature on the performance of aero-engine intake lips at high-incidence
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Influence of near-leading edge curvature on the performance of aero-engine intake lips at high-incidence

机译：高入射时近前缘曲率对航空发动机进气唇性能的影响

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摘要

This paper describes the investigation into the flow over the lip of subsonic engine intakes at incidence, focusing on the shock wave-boundary layer interaction occurring over the inner lip. A baseline geometry is considered along with two variations, characterised by a sharper and a blunter intake highlight (i.e.: nacelle leading edge) respectively. Results to date reveal a relatively benign interaction for the baseline model, with small or no shock-induced separation reported under on-design conditions, which correspond to typical takeoff or climb circumstances. The alternative geometries reveal a considerable influence of near-highlight curvature on the flow development. In particular, a blunter nose leads to the formation of a larger supersonic region, terminated by a consequently stronger shock, which shows a greater degree of shock-induced separation and increased total pressure losses and unsteadiness. The sharp nose, on the other hand, resulted in the compression occurring via three separate shock-waves, all of which weak. Overall, none of the three intake geometries showed inherently unsteady behaviour. However, this is expected to occur as the engine flow demand increases. Further testing is in progress to assess off-design performance and to produce a complete operational envelope for intakes at incidence.
机译：本文描述了对亚音速发动机进气口在进气口上的流动进行的研究，重点是在内唇上发生的冲击波-边界层相互作用。考虑了基线几何形状以及两个变化，分别以更锐利和更钝的进气亮点（即：机舱前缘）为特征。迄今为止的结果表明，基线模型的相互作用相对较好，在设计条件下（与典型的起飞或爬升情况相对应）报告了很小或没有激振引起的分离。可供选择的几何形状揭示了近高曲率对流动发展的相当大的影响。特别地，钝头导致形成较大的超音速区域，并由此产生更强的冲击力，从而显示出更大程度的冲击力导致的分离，并增加了总压力损失和不稳定性。另一方面，锋利的鼻子导致压缩是通过三个单独的冲击波发生的，所有这些冲击波都很弱。总体而言，三个进气口几何形状均未显示出固有的不稳定行为。但是，预计这会随着发动机流量需求的增加而发生。正在进行进一步测试，以评估非设计性能并为事故发生时的摄入量提供完整的运行范围。

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