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AERODYNAMIC CHARACTERISTICS OF SUPERCRITICAL OUTLET GUIDE VANES AT LOW REYNOLDS NUMBER CONDITIONS

机译：低雷诺数条件下超临界出口导向叶片的空气动力学特性

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As a part of an innovative aerodynamic design concept for a single stage low pressure turbine, a high turning outlet guide vane is required to remove the swirl from the hot gas. The airfoil of the vane is a highly loaded compressor airfoil that has to operate at very low Reynolds numbers (Re ～ 120,000). Recently published numerical design studies and experimental analysis on alternatively designed airfoils showed that blade profiles with an extreme front loaded pressure distribution are advantageous for low Reynolds number conditions. The advantage even holds true for an increased inlet Mach number at which the peak Mach number on the airfoils reaches and exceeds the critical conditions (M{sub}(ss) > 1.0). This paper discusses the effect of the inlet Mach number and Reynolds number on the cascade performance for both a controlled diffusion airfoil (CDA) (called baseline) and a numerically optimized front loaded airfoil. The results show that it is advantageous to design the profile with a fairly steep pressure gradient immediately at the front part in order to promote early transition or to prevent too large laminar - even shock induced - separations with the risk of a bubble burst. Profile Mach number distributions and wake traverse data are presented for design and off-design conditions. The discussion of Mach number distributions and boundary layer behavior is supported by numerical results obtained from the blade-to-blade flow solver MISES.
机译：作为单级低压涡轮机的创新空气动力学设计概念的一部分，需要高转动出口导向叶片以从热气体中除去涡流。叶片的翼型是高负荷的压缩机翼型，其必须在非常低的雷诺数（RE〜120,000）上运行。最近公布的数值设计研究和对可替代设计的翼型的实验分析表明，具有极端前部负载压力分布的叶片轮廓对于低雷诺数条件是有利的。优点甚至保持翼型上的峰值马赫数的增加的入口马赫数，并且超过临界条件（M {sub}（ss）> 1.0）。本文讨论了入口马赫数和雷诺数对控制扩散翼型（CDA）（称为基线）的级联性能的影响和数值优化的前负载翼型。结果表明，在前部门立即使用相当陡峭的压力梯度设计轮廓是有利的，以促进早期过渡或防止太大的层状休克诱导 - 与气泡爆裂的风险分离。概况Mach编号分布和唤醒遍历数据适用于设计和非设计条件。通过从叶片到叶片流动件误法获得的数值结果支持马赫数分布和边界层行为的讨论。

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