低雷诺数压气机叶型损失机理及优化研究  

Loss mechanism and optimization of low Reynolds number compressor airfoil

作　　者：常哲铭 尹红顺 王子登 郝玉扬 CHANG Zhe-Ming;YIN Hong-shun;WANG Zi-deng;HAO Yu-yang(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2022年第5期14-20,共7页Gas Turbine Experiment and Research

摘　　要：以亚声速压气机叶型为研究对象,通过数值模拟方法研究了不同雷诺数状态下压气机叶型流场结构和损失特性。通过调节叶型的弯度分布和最大厚度位置,获得了前加载和后加载两种新叶型。研究结果表明,随着雷诺数的降低,叶型表面开始出现层流分离泡,层流分离泡尺寸较小时,对叶型性能的影响较小。层流分离泡尺寸随雷诺数的降低逐渐增大,较大的层流分离泡将诱发叶型吸力面出现大分离,尾缘堆积大量低能流体,损失急剧增加。前加载叶型能够使转捩提前发生,在高、低雷诺数状态下都能使叶型损失降低,但对低雷诺数条件下损失的改善更为明显。Taking a subsonic compressor blade profile as the research object,the flow field structure and loss characteristics of the compressor blade profile at different Reynolds numbers were studied by numerical simulation.By adjusting the camber distribution and the position of the maximum thickness of the blade,two new blade profiles,front loading and after loading were obtained.The results show that with the decrease of Reynolds number,laminar separation bubbles begin to appear on the blade surface,when the laminar separation bubble size is small,the impact on blade performance is small.The size of laminar separation bubble increases with the decrease of Reynolds number.Large laminar separation bubbles will induce large separation on the suction surface of the blade profile,and a large amount of low-energy fluid is accumulated at the trailing edge,resulting in a sharp increase in losses.The results show that the front loading blade profile can make the transition happen in advance,and the loss of profile can be reduced at both high and low Reynolds numbers,and the improvement of loss at low Reynolds number is more obvious.

关 键 词：航空发动机 压气机 弯度分布 低雷诺数 叶型损失 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]