压气机转子叶尖局部削薄对性能的影响  

Influence of compressor rotor blade tip squealer on performance

作　　者：刘儒骏 曹传军 翟志龙 周拜豪 LIU Rujun;CAO Chuanjun;ZHAI Zhilong;ZHOU Baihao(AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 200241,China;AECC Sichuan Gas Turbine Research Establishment,Chengdu 610500,China)

机构地区：[1]中国航发商用航空发动机有限责任公司,上海200241 [2]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》2024年第1期37-42,共6页Gas Turbine Experiment and Research

摘　　要：转子叶尖局部削薄可以提升叶轮局部性能,提高效率和压比,广泛应用在航空发动机及燃气轮机的压气机叶片中。选取大涵道比涡扇发动机高压压气机中间级转子叶片为研究对象,对其三维模型进行了多种形式的叶尖局部削薄,并采用数值模拟方法研究了在不同深度、高度和宽度的削薄条件下叶片气动性能的变化。结果表明,叶尖削薄能够改善气动性能。同时,叶尖削薄深度越大,沿弦长方向越长,对气动性能越有利。Blade tip squealer can improve partial performance,efficiency,and pressure ratio of the impeller,which has been widely applied to compressor blades of aero-engines and gas turbines.The middle stage blade of the high-pressure compressor of a high bypass ratio turbofan engine was taken for numerical simulation,applied with different blade tip squealers,in order to investigate the aero performance change affected by different squealer depth,height,and width.The simulation results reveal that the blade tip squealer has a positive influence on the aero performance of compressor.Meanwhile,the deeper and the longer the squealer is,the better aero performance the blade would gain.

关 键 词：航空发动机 压气机转子 叶尖削薄 气动性能 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]