Maximum Thickness Location Selection of High Subsonic Axial Compressor Airfoils and Its Effect on Aerodynamic Performance

Solidity and camber angle are key parameters with a primary effect on airfoil diffusion. Maximum thickness location has a considerable impact on blade loading distribution. This paper investigates correlations of maximum thickness location, solidity, and camber angle with airfoil performance to choo...

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Autores principales:	Chuansijia Tao, Xin Du, Jun Ding, Yizhou Luo, Zhongqi Wang
Formato:	article
Lenguaje:	EN
Publicado:	Frontiers Media S.A. 2021
Materias:	high subsonic compressor blade profile maximum thickness location solidity prediction model database General Works A
Acceso en línea:	https://doaj.org/article/992813af981f4d6e8b4cafc3d7eff49b
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spelling	oai:doaj.org-article:992813af981f4d6e8b4cafc3d7eff49b2021-11-22T04:35:17ZMaximum Thickness Location Selection of High Subsonic Axial Compressor Airfoils and Its Effect on Aerodynamic Performance2296-598X10.3389/fenrg.2021.791542https://doaj.org/article/992813af981f4d6e8b4cafc3d7eff49b2021-11-01T00:00:00Zhttps://www.frontiersin.org/articles/10.3389/fenrg.2021.791542/fullhttps://doaj.org/toc/2296-598XSolidity and camber angle are key parameters with a primary effect on airfoil diffusion. Maximum thickness location has a considerable impact on blade loading distribution. This paper investigates correlations of maximum thickness location, solidity, and camber angle with airfoil performance to choose maximum thickness location quickly for compressor airfoils with different diffusion. The effects of maximum thickness location, solidity, and camber angle on incidence characteristics are discussed based on abundant two-dimensional cascade cases computed through numerical methods. Models of minimum loss incidence, total pressure loss coefficient, diffusion factor, and static pressure rise coefficient are established to describe correlations quantitatively. Based on models, dependence maps of total pressure loss coefficient, diffusion factor, and static pressure rise coefficient are drawn and total loss variation brought by maximum thickness location is analyzed. The study shows that the preferred selection of maximum thickness location can be the most forward one with no serious shock loss. Then, the choice maps of optimal maximum thickness location on different design conditions are presented. The optimal maximum thickness locates at 20–35% chord length. Finally, a database of optimal cases which can meet different loading requirements is provided as a tool for designers to choose geometrical parameters.Chuansijia TaoXin DuJun DingJun DingYizhou LuoZhongqi WangFrontiers Media S.A.articlehigh subsonic compressorblade profilemaximum thickness locationsolidityprediction modeldatabaseGeneral WorksAENFrontiers in Energy Research, Vol 9 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	high subsonic compressor blade profile maximum thickness location solidity prediction model database General Works A
spellingShingle	high subsonic compressor blade profile maximum thickness location solidity prediction model database General Works A Chuansijia Tao Xin Du Jun Ding Jun Ding Yizhou Luo Zhongqi Wang Maximum Thickness Location Selection of High Subsonic Axial Compressor Airfoils and Its Effect on Aerodynamic Performance
description	Solidity and camber angle are key parameters with a primary effect on airfoil diffusion. Maximum thickness location has a considerable impact on blade loading distribution. This paper investigates correlations of maximum thickness location, solidity, and camber angle with airfoil performance to choose maximum thickness location quickly for compressor airfoils with different diffusion. The effects of maximum thickness location, solidity, and camber angle on incidence characteristics are discussed based on abundant two-dimensional cascade cases computed through numerical methods. Models of minimum loss incidence, total pressure loss coefficient, diffusion factor, and static pressure rise coefficient are established to describe correlations quantitatively. Based on models, dependence maps of total pressure loss coefficient, diffusion factor, and static pressure rise coefficient are drawn and total loss variation brought by maximum thickness location is analyzed. The study shows that the preferred selection of maximum thickness location can be the most forward one with no serious shock loss. Then, the choice maps of optimal maximum thickness location on different design conditions are presented. The optimal maximum thickness locates at 20–35% chord length. Finally, a database of optimal cases which can meet different loading requirements is provided as a tool for designers to choose geometrical parameters.
format	article
author	Chuansijia Tao Xin Du Jun Ding Jun Ding Yizhou Luo Zhongqi Wang
author_facet	Chuansijia Tao Xin Du Jun Ding Jun Ding Yizhou Luo Zhongqi Wang
author_sort	Chuansijia Tao
title	Maximum Thickness Location Selection of High Subsonic Axial Compressor Airfoils and Its Effect on Aerodynamic Performance
title_short	Maximum Thickness Location Selection of High Subsonic Axial Compressor Airfoils and Its Effect on Aerodynamic Performance
title_full	Maximum Thickness Location Selection of High Subsonic Axial Compressor Airfoils and Its Effect on Aerodynamic Performance
title_fullStr	Maximum Thickness Location Selection of High Subsonic Axial Compressor Airfoils and Its Effect on Aerodynamic Performance
title_full_unstemmed	Maximum Thickness Location Selection of High Subsonic Axial Compressor Airfoils and Its Effect on Aerodynamic Performance
title_sort	maximum thickness location selection of high subsonic axial compressor airfoils and its effect on aerodynamic performance
publisher	Frontiers Media S.A.
publishDate	2021
url	https://doaj.org/article/992813af981f4d6e8b4cafc3d7eff49b
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_version_	1718418176423755776

Maximum Thickness Location Selection of High Subsonic Axial Compressor Airfoils and Its Effect on Aerodynamic Performance

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