报告内容摘要：

Clearance flow is crucial in compressors. It causes loss and unsteadiness, and can directly trigger the extreme unsteady flow phenomenon, such as spike-type stall inception. The work provides steady Reynolds averaged Navier-Stokes Equations (RANS) and unsteady Improved Delayed Detached Eddy Simulation (IDDES) calculations of the flow field for two different types of compressors: Deutschen Zentrums für Luft- und Raumfahrt (DLR, Germany Aerospace Center) subsonic compressor stator and Notre Dame (ND) transonic compressor rotor. Both of these compressors are single row axial compressors. To improve the rotor performance, circumferential groove casing treatment (CGCT) is carried out. The effect of a single circumferential groove casing treatment on ND transonic compressor rotor is investigated numerically. The effect of the groove at different axial locations on the flow field is studied in detail and the stall margin improvement is analyzed. The present results show that the groove close to the leading edge plays a crucial role in stabilizing the near stall flow structures and, hence, improves the stall margin. The groove at the mid-section of the blade chord can help exchange and transfer momentums between different directions, and suppress the flow unsteadiness, leading to increased efficiency in rotor performance and extended operation range. The groove located near the blade trailing edge has limited effects on the stall margin improvement and may cause additional penalty in the efficiency. Based on the understanding of the casing treatment mechanism, the use of the number of grooves is optimized. The results indicate better performance with optimized CGCT.

报告人简介：石可 博士

石可，2003-2007年就读于清华大学航天航空学院工程力学系工程热物理专业，获学士学位。2007-2013年就读于清华大学航天航空学院工程力学系流体力学专业，获博士学位。博士期间主要从事航空发动机压气机内部流动的数值计算及机匣处理流动控制研究工作。2013年8月至今，在美国印第安纳州圣母大学叶轮机械实验室从事博士后研究工作，研究内容包括涡轮和压气机的气动性能、气膜冷却、转静叶排干涉和流动损失机理的数值研究，跨音速压气机气动性能及流动结构的实验研究，数值格式的开发和验证工作。

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