吸力面负曲率的渐缩流道跨音速涡轮叶栅流场与性能研究  

Investigation on the Flow Field and Performance of a Highly Loaded Transonic Turbine Cascade With a Negative Curvature Suction Side

作　　者：赵巍[1,2] 刘宁[1,3] 吴冰[1,3] 赵庆军[1,2] 徐建中[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院轻型动力重点实验室,北京100190 [3]中国科学院大学,北京100190

出　　处：《工程热物理学报》2015年第9期1884-1888,共5页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51006098);国家重点基础研究发展计划(973计划)(No.2010CB227302)

摘　　要：为了降低高负荷跨音速涡轮叶片流动损失,本文提出了一种在吸力面无遮盖段存在内凹型线的渐缩流道跨音速涡轮新叶型。新叶型可通过改进常规跨音速涡轮的叶型得到。数值模拟结果表明采用新叶型的平面叶栅与原叶型的相比总压损失系数降低了29.7%。通过分析新叶型的几何特征及其激波、膨胀波与压缩波的特点,揭示了新叶型使损失降低的内部流动机理。新叶型不仅能够减少气动损失,而且能够降低叶片排气的周向不均性,减小对下游叶片排边界层的非定常影响。In order to reduce the shock related losses of highly-loaded transonic turbines, u novel turbine blade profile is presented in this paper. The blade profile features that it establishes a convergent blade passage and has a negative curvature uncovered suction side. Numerical simulation shows that a reduction of 29.7% in the total pressure loss coefficient can be obtained after such a blade profiled is applied to a traditional turbine cascade. The blade profile geometrical characteristics and properties of shocks, expansion and compression waves are analyzed, which helps to reveal the flow physics of the loss reduction. In addition to reducing the aerodynamic losses the blade profile can improve the uniformity of its exit flow, and the downstream blade rows would then suffer less unsteady effects from it.

关 键 词：跨音速涡轮 负曲率 激波 膨胀波 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]