翼型
前沿
曲率
空气动力学
气体压缩机
GSM演进的增强数据速率
点(几何)
加速度
职位(财务)
流量(数学)
航程(航空)
机械
几何学
数学
物理
工程类
航空航天工程
计算机科学
经典力学
人工智能
经济
财务
作者
Guanhua Yang,Limin Gao,Haohao Wang,Longrui Chang
出处
期刊:International journal of turbo & jet-engines
[De Gruyter]
日期:2022-05-27
标识
DOI:10.1515/tjj-2021-0054
摘要
Abstract Leading edge (LE) plays a prominent role in compressor flow. The asymmetric leading edge (ASYLE) has shown superiorities to symmetric LE in blade aerodynamic performance. However, the influencing rules of ASYLE design parameters are still ambiguous. In this work, numerical calculations were conducted to investigate the influencing effects of LE point curvature and position. The results show that the operating range of ASYLE blades expand with the decrease of LE point curvature, which helps to moderate LE flow acceleration, while the LE point position mainly affects the operating range. It is also revealed that the SSLE curvature peak is supposed to be close to LE point, and the maximum value of PSLE curvature should be restricted.
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