可控扩散叶型吸力面峰值等熵马赫数位置对叶栅气动性能影响
Effect of Positions of Peak Isentropic Mach Number on Suction Surface of Controlled Diffusion Airfoils on Aerodynamic Performance of Cascades
陈晓洁 1周正贵 1曾凌霄1
作者信息
- 1. 南京航空航天大学能源与动力学院,江苏南京 210016
- 折叠
摘要
通常亚音压气机叶型表面等熵马赫数分布符合可控扩散规律,并且吸力面峰值马赫数位置靠前叶栅气动性能较好.采用自动优化方法,设计出给定吸力面峰值等熵马赫数位置可控扩散叶型,分析此位置对叶栅气动性能的影响规律.研究结果表明:对于可控扩散转子和静子叶型,在设计工况下,当吸力面峰值等熵马赫位置位于0.20倍轴向弦长时,吸力面附面层沿流程快速发展,造成叶栅损失大幅增加;当吸力面峰值等熵马赫数位置为0.10～0.15倍轴向弦长时,设计进气角近似位于叶栅低损失进气角范围中,且低损失范围内损失较低.
Abstract
The isentropic Mach number distribution on the airfoil surface of a subsonic compressor generally complies with the law of controlled diffusion,and the aerodynamic performance of cascades in front peak Mach number position on the suction surface is satisfactory.Designs a controlled diffusion airfoils with given suction surface peak isentropic Mach number position by automatic optimization technique,and analyzes the effect of its positions on the aerodynamic performance of the cascades.The results show that the controlled diffusion rotor and stator airfoils,when the peak isentropic Mach position of the suction surface is 0.20,times the axial chord length under the design condition,the boundary layer of the suction surface develops rapidly along the flow,resulting in a large increase in cascade loss.When the position of the peak isentropic Mach number on the suction surface is ranging from 0.10 to 0.15 times the axial chord length,the inlet angle at design point is approximately in the middle of the operating range,and lower loss is expected in the operating range.
关键词
压气机/叶栅/负载分布/可控扩散叶型/优化设计Key words
compressor/cascade/load distribution/controlled diffusion airfoil/optimization design引用本文复制引用
基金项目
国家科技重大专项项目(2017-Ⅱ-0001-0013)
出版年
2024
国家科技期刊平台
NSTL
万方数据