Numerical Investigation on Flow and Heat Transfer Characteristics of Blade Tip Gap in Gas Turbines

摘要：

　　The leakage flow and heat transfer characteristics of the gas turbine rotor tip without shroud is extremely complicated,especially with the effect of the larger transverse pressure gradient and the higher temperature of the gas.And it will lead to flow efficiency reduction and the gas turbine blade ablated possibly.In this paper,the rotor in the first stage of GE-E3 engine high pressure turbine is taken as the object to investigate the flow and heat transfer characteristics at the blade tip,and the different influence on the leakage flow,heat transfer and film cooling performance at the tip caused by different groove depth,blowing ratio,cooling holes quantity and size is studied.The results show that the squealer tip changes the flow structure in the tip clearance,reduces the leakage flow and changes the distribution of heat transfer coefficient,and the heat transfer coefficient on the tip surface increases with the groove depth,and it is especially obvious when the groove is relatively deeper.When the film cooling holes arranged along the mean camber line,the separation line on the tip surface always deflects towards the suction side as the blowing ratio,the quantity or the diameter of the film cooling holes increases.The cooling effect is the best in this paper when the blowing ratio is 1.0.Although the average cooling effect is still increasing,the rise is very limited and the cooling air begins to separate from the surface.

关键词： Gas turbine Tip leakage flow Heat transfer Film cooling

作者: Qinghua Deng Jun Li Zhenping Feng

作者单位: Institute of Turbomachinery,Xian Jiaotong University,Xian,Shaanxi,710049,P.R.China;Collaborative I Institute of Turbomachinery,Xian Jiaotong University,Xian,Shaanxi,710049,P.R.China

会议类型: 国际会议

会议名称: The 5th International Symposium on Jet Propulsion and Power Engineering(第五届喷气推进与动力工程国际会议)

会议地点: 北京

会议语种:英文

页码: 1-8

在线出版日期: 2014-09-15（万方平台首次上网日期，不代表论文的发表时间）