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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.6 pt.A; 20050606-09; Reno-Tahoe,NV(US) >AERODYNAMIC CHARACTERISTICS OF SUPERCRITICAL OUTLET GUIDE VANES AT LOW REYNOLDS NUMBER CONDITIONS
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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流叶片的气动特性

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摘要

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_(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：作为用于单级低压涡轮机的创新空气动力学设计概念的一部分，需要高转弯的出口导向叶片以消除热气体中的涡流。叶片的翼型是高负荷的压缩机翼型，必须以非常低的雷诺数（Re〜120,000）运行。最近发表的数值设计研究和替代设计的机翼的实验分析表明，具有极高的前端载荷压力分布的叶片轮廓对于低雷诺数条件是有利的。对于增加的进气马赫数，甚至在翼型上的峰值马赫数达到并超过临界条件（M_（ss）> 1.0）时，该优势甚至仍然成立。本文讨论了受控扩散翼型（CDA）（称为基准）和数值优化前载荷翼型的进气口马赫数和雷诺数对叶栅性能的影响。结果表明，有利的是在前部立即设计具有相当陡峭的压力梯度的轮廓，以促进早期过渡或防止过大的层流-甚至是由震动引起的分离，而有气泡破裂的风险。针对设计和非设计条件，提供了轮廓马赫数分布和尾流遍历数据。马赫数分布和边界层行为的讨论得到了从叶片到叶片流动求解器MISES获得的数值结果的支持。

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