可控转速机匣起始位置对跨声速压气机转子流动稳定性的影响  

Effect of the Starting Position of the Controllable Speed Casing on the Flow Stability for a Transonic Compressor Rotor

作　　者：赵佳诣 吴宛洋 钟兢军 ZHAO Jiayi;WU Wanyang;ZHONG Jingjun(Merchant Marine College,Shanghai Maritime University,Shanghai 201306,China;School of Mechanical Engineering,Shanghai Dianji University,Shanghai 201306,China)

机构地区：[1]上海海事大学商船学院,上海201306 [2]上海电机学院机械学院,上海201306

出　　处：《工程热物理学报》2024年第5期1341-1349,共9页Journal of Engineering Thermophysics

基　　金：国家自然科学基金重点和青年基金项目(No.52236005,No.51906134);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：机匣处理的几何结构参数将对其扩稳机制和扩稳能力产生影响。本文针对可控转速机匣中可转动环段的起始位置对跨声速压气机转子流动稳定性的影响开展数值研究。结果表明,当可转动环段的起始位置从叶顶尾缘开始逐渐向上游移动的过程中,可转动环段作用范围的扩展使叶顶流场处于逆压流动的范围扩大,通流条件恶化,但由于同时也降低了叶尖负荷,稳定工作的流量范围得以扩大。而当起始位置继续向上游移动至20%轴向弦长和叶顶前缘处时,可转动环段能够分别完成对泄漏涡破碎后流体和来流主流的轴向加速,降低激波/泄漏涡干涉强度的同时削弱了堵塞效应,转子流动稳定性得到有效改善,特别是当起始位置位于叶顶前缘时,稳定工作裕度提高了52.56%。The geometric parameter for the casing treatment has a impact on the stability expansion mechanism and capacity.The effect of the starting position of the rotatable ring in controllable speed casing on the flow stability for a transonic compressor rotor was studied numerically in the present paper.The results indicate that when the starting position moves upstream from the tip trailing edge,the range of action of the rotatable ring is extended,leading to larger reverse pressure flow field and worse fow condition.However,because it reduces the blade tip load at the same time,the stable operating range is expanded.When the starting position continues to move upstream to 20%axial chord length and the leading edge of blade tip,the rotatable ring accelerates the axial fow of the fluid of broken leakage vortex and the incoming mainstream,reducing the interaction intensity between the shock wave/leakage vortex and weakening the blockage effect.The flow stability is effectively improved,especially when the starting position is located at the leading edge of blade tip,the stable operating margin is increased by 52.56%.

关 键 词：可控转速机匣 起始位置 跨声速压气机转子 叶顶泄漏流 流动稳定性 

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]