叶顶间隙对某涡轮级流场及气动性能影响的数值研究  

Numerical Investigation on the Effect of Tip Clearance on a Turbine Stage Flow-field and Aerodynamic Performance

作　　者：周治华[1] 陈绍文[1] 兰云鹤 王松涛[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江省哈尔滨市150001

出　　处：《中国电机工程学报》2015年第5期1176-1182,共7页Proceedings of the CSEE

基　　金：国家自然科学基金(51206035;51121004)~~

摘　　要：采用数值模拟方法,对某涡轴发动机高压涡轮的其中一级进行了三维流场计算,通过对比分析均匀和非均匀间隙条件下的流场和气动参数分布,探讨了不同间隙形式时的叶顶泄漏流动情况、以及流场变化对涡轮级气动性能的影响。结果表明:随着间隙高度的增加,叶顶泄漏高损失区与上通道涡高损失区相结合,新的大尺度分离结构形成引起损失增加,当间隙高度为1.2 mm时的总效率降幅达到5个百分点;前缘附近间隙增加对损失的不利影响要小于尾缘,降低尾缘附近的间隙高度至0.3 mm可以有效提高总效率约1个百分点;通过控制叶顶不同区域的间隙高度,可以对间隙内泄漏流体速度进行有效控制,减小间隙内堵塞从而提高总性能。Three-dimensional numerical method was adopted to study the flow field and aerodynamic performance of a high pressure turbine stage of a turbo-shaft engine. The flow characteristics and aerodynamic parameters were compared under uniform and non-uniform tip clearance. The influence of tip leakage flow and the flow-field changes on dynamic performance of gas turbine with different gap forms was also discussed. The results show that the high-loss region closed to the tip gradually incorporates with the high-lose region of the upper passage vortex increased with the tip clearance. The new large scale separation structure leads to increased losses and the total efficiency reduces by 5% when the clearance height is 1.2 mm. Increasing the tip clearances near the leading edge has less adverse effect on loss than that of near the trailing edge. Reducing the tip clearance to 0.3 mm near the trailing edge can effectively improve the total efficiency about 1%. As a result, controlling the tip clearance in different regions of blade tip can effectively control the leakage flow rate and reduces blockage in the gap for improving the total performance in the gas turbine.

关 键 词：涡轮 非均匀间隙 间隙泄露流 数值研究 

分 类 号：TH113[机械工程—机械设计及理论]