涡轮机械
涡扇发动机
跨音速
气体压缩机
计算机科学
曲率
涡轮机
计算流体力学
轴流压缩机
叶尖间隙
空气动力学
航空航天工程
工程类
数学
几何学
作者
Sercan Acarer,Ünver Özkol
出处
期刊:International journal of turbo & jet-engines
[De Gruyter]
日期:2019-05-27
卷期号:36 (2): 137-146
被引量:2
标识
DOI:10.1515/tjj-2016-0083
摘要
Abstract The two-dimensional streamline curvature through-flow modeling of turbomachinery is still a key element for turbomachinery preliminary analysis. Basically, axisymmetric swirling flow field is solved numerically. The effects of blades are imposed as sources of swirl, work input/output and entropy generation. Although the topic is studied vastly in the literature for compressors and turbines, combined modeling of the transonic fan and the downstream splitter of turbofan engine configuration, to the authors’ best knowledge, is limited. In a prior study, the authors presented a new method for bypass fan modeling for inverse design calculations. Moreover, new set of practical empirical correlations are calibrated and validated. This paper is an extension of this study to rapid off-design analysis of transonic by-pass fan systems. The methodology is validated by two test cases: NASA 2-stage fan and GE-NASA bypass fan case. The proposed methodology is a simple extension for streamline curvature method and can be applied to existing compressor methodologies with minimum numerical effort.
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