A Novel Method for Reducing Tip Clearance Leakage of Turbine

摘要：

A novel method for reducing tip clearance leakage of turbine was presented using backward vortex generators (BVGs) in this paper. In order to reduce tip leakage flow, the gas flows into BVGs from pressure side of blade and flows out of blade tip with high speed in the inverse-direction of leakage flow, driven by the pressure difference between pressure surface and blade tip. Numerical simulations of typical turbine cascade in millimeter scale with and without B VGs were performed and the influences ofB VGs on mass of leakage flow and circumferential load were analyzed. The results show that mass of leakage flow decreases by 3.3％ and circumferential load increases by 6.2％ in typical entrance condition. Moreover, the smaller the inlet mach number is, the better the effect of reducing mass of leakage flow is; the larger the inlet mach number is, the more improvement of circumferential load is. As inlet mach number increases, the improvement of turbine efficiency affected by B VGs grows more.

关键词： aerospace propulsion turbine tip clearance leakage flow backward vortex generators circumferential load turbine efficiency

作者: Chuanjun Cao Guoping Huang Chen Xia

作者单位: College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics Nanjing, P.R.China

会议类型: 国际会议

会议名称: The 3rd International Symposium on Jet Propulsion and Power Engineering(第三届喷气推进与动力工程国际会议 ISJPPE)

会议地点: 南京

会议语种:英文

页码: 44-51

在线出版日期: 2010-09-13（万方平台首次上网日期，不代表论文的发表时间）