Experimental investigation of the dynamics of turbulent separation bubbles

湍流分离气泡动力学的实验研究

• 批准号: 386285-2010
• 负责人: Weiss, Julien
• 金额: $ 1.75万
• 依托单位: École de technologie supérieure
• 依托单位国家: 加拿大
• 项目类别: Discovery Grants Program - Individual
• 财政年份: 2013
• 资助国家: 加拿大
• 起止时间: 2013-01-01 至 2014-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=528806
• 关键词: Experimental; investigation; dynamics; turbulent; separation

The performance of aerodynamic systems like aircraft wings and turbomachinery blades is very dependent on the behavior of the layer of fluid that is very close to the system's solid surface. This layer of fluid, called a boundary layer, can separate and reattach to the surface depending on the general flow conditions. On aircraft wings, boundary layer separation is related to the dangerous phenomenon of aerodynamic stall, in which the wing lift decreases abruptly when the boundary layer separates from the wing surface. In gas turbines, compressor operation is limited by a similar phenomenon (compressor surge), whereas on turbine blades, boundary layer separation and reattachment can generate a "hot-spot" that is detrimental to the blade material and can reduce its lifetime.

飞机机翼和涡轮机械叶片等空气动力系统的性能非常依赖于离系统固体表面非常近的流体层的行为。这层流体被称为边界层，根据一般的流动条件，可以分离和重新附着到表面。在飞机机翼上，边界层分离与气动失速的危险现象有关，即当边界层从机翼表面分离时，机翼升力突然减小。在燃气轮机中，压缩机的运行受到类似现象(压缩机喘振)的限制，而在涡轮叶片上，边界层分离和重新连接会产生一个“热点”，对叶片材料不利，并可能降低其使用寿命。