叶尖小翼周向参数对高负荷压气机级叶顶流动的影响  

The Influence of Circumferential Parameters of Tip Winglets on the Tip Flow of a High-load Compressor Stage

作　　者：赵傲 吴宛洋 胡义 钟兢军 ZHAO Ao;WU Wanyang;HU Yi;ZHONG Jingjun(Merchant Marine College,Shanghai Maritime University,Shanghai 201306,China)

机构地区：[1]上海海事大学商船学院,上海201306

出　　处：《工程热物理学报》2025年第2期429-437,共9页Journal of Engineering Thermophysics

基　　金：国家自然科学基金重点项目(No.52236005);航空发动机及燃气轮机基础科学中心重点项目(No.P2022-B-II-007-001)。

摘　　要：通过在转子叶尖加装叶尖小翼可以减小泄漏流动对压气机失速带来的负面影响。本文研究了不同周向分布的叶尖小翼对高负荷压气机级性能和流场结构的影响,叶尖小翼通过削弱泄漏流的负轴向动量达到了减少泄漏流质量流量的目的,从而使泄漏涡的发展受到了抑制。对比分析后得到了叶尖小翼最佳的最宽位置,对于本文研究的高负荷压气机级,该位置约为25%弦长处。随着叶尖小翼周向宽度的增大,其对泄漏流和流动损失的抑制作用也逐渐增大。最优方案可以使压气机级失速裕度提升29.18%,泄漏流质量流量减少7.66%。The negative impact of leakage flow on compressor stall can be reduced by installing tip winglet at the rotor tip.This paper investigates the influence of tip winglets with different circumferential distributions on the performance and flow field structure of the high-load compressor stage.Tip winglets reduce the tip leakage mass flow rate by weakening the negative axial momentum of the leakage flow,thereby suppressing the development of the leakage vortex.After comparative analysis,the optimal widest position of the tip winglet is obtained.For the high-load compressor stage studied in this paper,this position is approximately at 25%chord length.As the circumferential width of the tip winglets increases,their inhibitory effect on leakage flow and flow loss gradually increases.The optimal case can increase the stall margin of the compressor stage by 29.18%and reduce the leakage mass flow rate by 7.66%.

关 键 词：高负荷压气机级 叶顶流动 叶尖小翼 周向参数 数值研究 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]