动叶前缘小翼对跨声速压气机稳定性的影响  

Influence of rotor leading edge winglet on the stability of transonic compressor

作　　者：韩少冰 李铮 钟兢军 HAN Shaobing;LI Zheng;ZHONG Jingjun(Naval Architecture and Ocean Engineering College,Dalian Maritime University,Dalian 116026,Liaoning China;Merchant Marine College,Shanghai Maritime University,Shanghai 201306,China)

机构地区：[1]大连海事大学船舶与海洋工程学院,辽宁大连116026 [2]上海海事大学商船学院,上海201306

出　　处：《华中科技大学学报(自然科学版)》2025年第1期158-164,共7页Journal of Huazhong University of Science and Technology(Natural Science Edition)

基　　金：国家自然科学基金资助项目(52236005,51406021);航空发动机及燃气轮机基础科学中心资助项目(P2022-BII-007-001).

摘　　要：为了进一步扩大轴流压气机稳定裕度,以跨声速压气机NASA Stage35为研究对象,采用经过数值校核的数值模拟方法分析了动叶前缘小翼的扩稳机理,讨论了动叶前缘小翼对跨声速压气机性能及内部流动特征的影响.研究结果表明:动叶前缘小翼均使得压气机峰值效率有所降低,合适长度的动叶前缘小翼能够在保持近失速工况附近压气机级压比和效率基本不变的情况下,使稳定裕度增加14.96%.与原型压气机相比,前缘小翼使得动叶叶顶弦长增加,近前缘处叶顶负荷降低,从而降低了叶顶泄漏涡强度及激波/泄漏涡相互作用造成的流动堵塞,提高了压气机工作稳定性.前缘小翼造成压气机峰值效率降低的原因是前缘小翼使叶顶泄漏流对动叶吸力面及端壁区分离流体的吹除作用减弱.In order to further expand the stability margin of the axial compressor,taking the transonic compressor NASA(National Aeronautics and Space Administration)Stage35 as the research object,the expansion mechanism of the rotor leading edge winglet was studied by using the numerical simulation method after numerical verification,and the effects of leading edge winglet on transonic compressor performance and internal flow were discussed in detail.The research results show that all leading edge winglet cases reduce the peak efficiency of the compressor.The suitable length leading edge winglet of the rotor blade can increase its stability margin by 14.96%while keeping the compressor stage pressure and efficiency basically unchanged near the near-stall operating condition.Compared with the prototype compressor,the leading edge winglet increases the blade tip chord of rotor,and the blade tip load near the leading edge is reduced,thereby reducing the tip leakage vortex intensity and the flow blockage caused by the shock wave/tip leakage vortex interaction,and improving the working stability of the compressor.The reason for the decrease in peak efficiency of the compressor caused by the leading edge winglet is that the leading edge winglet weakens the blowing effect of the tip leakage flow on the separation fluid of the suction surface and end wall area of the rotor blade.

关 键 词：动叶前缘小翼 跨声速压气机 间隙泄漏涡 稳定裕度 旋涡结构 

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]