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Secondary Flow Spanwise Deviation Model for the Stators of NASA Middle Compressor Stages

机译：Nasa中压缩机级定子的二次流动斜向偏差模型

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摘要

A model of the spanwise variation of deviation for stator blades is presented. Deviation is defined as the difference between the passage mean flow angle and the metal angle at the outlet of a blade element of an axial compressor stage. The variation of deviation is taken as the difference above or below that predicted by blade element, (i.e., two-dimensional) theory at any spanwise location. The variation of deviation is dependent upon the blade camber, solidity and inlet boundary layer thickness at the hub or tip end-wall, and the blade channel aspect ratio. If these parameters are known or can be calculated, the model provides a reasonable approximation of the spanwise variation of deviation for most compressor middle stage stators operating at subsonic inlet Mach numbers.

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作者
Roberts, W. B.; Sandercock, D. M.;
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年度 1984
页码 p.1-40
总页数 40
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
Compressor blades; Deviation; Mathematical models; Secondary flow; Stators; Turbocompressors; Aspect ratio; Blade tips; Boundary layers; Calculus of variations; Camber; Hubs; Prediction analysis techniques;

机译：压缩机叶片;偏差;数学模型;二次流;定子;涡轮压缩机;纵横比;叶尖;边界层;变化微积分;曲面;轮毂;预测分析技术;

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Secondary Flow Spanwise Deviation Model for the Stators of NASA Middle Compressor Stages

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