参数化导翼转角失速控制方法的实验验证

IF 1.1 Q4 ENGINEERING, MECHANICAL Journal of the Global Power and Propulsion Society Pub Date : 2022-04-12 DOI:10.33737/jgpps/152238
Gabriel Mondin, W. Riéra, P. Duquesne, X. Ottavy
{"title":"参数化导翼转角失速控制方法的实验验证","authors":"Gabriel Mondin, W. Riéra, P. Duquesne, X. Ottavy","doi":"10.33737/jgpps/152238","DOIUrl":null,"url":null,"abstract":"Corner separation is known to limit the operability of aeronautical compressors. Dedicated control devices such as guide fins are envisioned to reduce its negative effects. This paper presents a methodology based on RANS (Reynolds-Averaged Navier-Stokes) computations enabling to select guide fins efficient for that purpose. This methodology is applied to a reference case of linear compressor cascade operating at low Mach number (∼0.11). A set of 17 parameters is used to define two design spaces of interest, from which guide fins are generated. From then, an automated process generates and merges an unstructured mesh built around each guide fin with a fixed, structured mesh of reference representing a single channel of the cascade. Finally, RANS results on the resulting hybrid mesh are obtained using the Computational Fluid Dynamics solver elsA. This set up has proven successful in evaluating automatically hundreds of guide fins of various shapes. Several geometries illustrate the diversity of the design space. A selection of guide fins is then evaluated experimentally. Evolutions of the losses downstream of the cascade are compared to their respective RANS predictions, and to the reference case without guide fin. These experimental results validate the implemented methodology and show encouraging results in terms of loss redistribution brought by the control device.","PeriodicalId":53002,"journal":{"name":"Journal of the Global Power and Propulsion Society","volume":null,"pages":null},"PeriodicalIF":1.1000,"publicationDate":"2022-04-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Experimental validation of a corner stall control methodology using parametrised guide fins\",\"authors\":\"Gabriel Mondin, W. Riéra, P. Duquesne, X. Ottavy\",\"doi\":\"10.33737/jgpps/152238\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"Corner separation is known to limit the operability of aeronautical compressors. Dedicated control devices such as guide fins are envisioned to reduce its negative effects. This paper presents a methodology based on RANS (Reynolds-Averaged Navier-Stokes) computations enabling to select guide fins efficient for that purpose. This methodology is applied to a reference case of linear compressor cascade operating at low Mach number (∼0.11). A set of 17 parameters is used to define two design spaces of interest, from which guide fins are generated. From then, an automated process generates and merges an unstructured mesh built around each guide fin with a fixed, structured mesh of reference representing a single channel of the cascade. Finally, RANS results on the resulting hybrid mesh are obtained using the Computational Fluid Dynamics solver elsA. This set up has proven successful in evaluating automatically hundreds of guide fins of various shapes. Several geometries illustrate the diversity of the design space. A selection of guide fins is then evaluated experimentally. Evolutions of the losses downstream of the cascade are compared to their respective RANS predictions, and to the reference case without guide fin. These experimental results validate the implemented methodology and show encouraging results in terms of loss redistribution brought by the control device.\",\"PeriodicalId\":53002,\"journal\":{\"name\":\"Journal of the Global Power and Propulsion Society\",\"volume\":null,\"pages\":null},\"PeriodicalIF\":1.1000,\"publicationDate\":\"2022-04-12\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Journal of the Global Power and Propulsion Society\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.33737/jgpps/152238\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q4\",\"JCRName\":\"ENGINEERING, MECHANICAL\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Journal of the Global Power and Propulsion Society","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.33737/jgpps/152238","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q4","JCRName":"ENGINEERING, MECHANICAL","Score":null,"Total":0}
引用次数: 0

摘要

众所周知,角分离会限制航空压缩机的可操作性。专用的控制装置,如导向翅片,可以减少其负面影响。本文提出了一种基于RANS(Reynolds Averaged Navier-Stokes)计算的方法,能够选择高效的导流片。该方法适用于在低马赫数(~0.11)下运行的线性压缩机叶栅的参考情况。一组17个参数用于定义两个感兴趣的设计空间,从中生成导向翅片。从那时起,一个自动化过程生成并合并了围绕每个导向翅片构建的非结构化网格,以及代表叶栅单个通道的固定的结构化参考网格。最后,使用计算流体动力学求解器elsA获得了所得混合网格的RANS结果。事实证明,这种设置成功地自动评估了数百个不同形状的导向翅片。几种几何形状说明了设计空间的多样性。然后通过实验对导向翅片的选择进行评估。将叶栅下游损失的演变与其各自的RANS预测进行比较,并与没有导向翅片的参考情况进行比较。这些实验结果验证了所实现的方法,并在控制设备带来的损失再分配方面显示出令人鼓舞的结果。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
查看原文
分享 分享
微信好友 朋友圈 QQ好友 复制链接
本刊更多论文
Experimental validation of a corner stall control methodology using parametrised guide fins
Corner separation is known to limit the operability of aeronautical compressors. Dedicated control devices such as guide fins are envisioned to reduce its negative effects. This paper presents a methodology based on RANS (Reynolds-Averaged Navier-Stokes) computations enabling to select guide fins efficient for that purpose. This methodology is applied to a reference case of linear compressor cascade operating at low Mach number (∼0.11). A set of 17 parameters is used to define two design spaces of interest, from which guide fins are generated. From then, an automated process generates and merges an unstructured mesh built around each guide fin with a fixed, structured mesh of reference representing a single channel of the cascade. Finally, RANS results on the resulting hybrid mesh are obtained using the Computational Fluid Dynamics solver elsA. This set up has proven successful in evaluating automatically hundreds of guide fins of various shapes. Several geometries illustrate the diversity of the design space. A selection of guide fins is then evaluated experimentally. Evolutions of the losses downstream of the cascade are compared to their respective RANS predictions, and to the reference case without guide fin. These experimental results validate the implemented methodology and show encouraging results in terms of loss redistribution brought by the control device.
求助全文
通过发布文献求助,成功后即可免费获取论文全文。 去求助
来源期刊
Journal of the Global Power and Propulsion Society
Journal of the Global Power and Propulsion Society Engineering-Industrial and Manufacturing Engineering
CiteScore
2.10
自引率
0.00%
发文量
21
审稿时长
8 weeks
期刊最新文献
Thermodynamic performance study of simplified precooled engine cycle with coupling power output Direct multi-fidelity integration of 3D CFD models in a gas turbine with numerical zooming method A novel performance adaptation method for aero-engine matching over a wide operating range Swirling flow field reconstruction and cooling performance analysis based on experimental observations using physics-informed neural networks Flow physics during durge of an axial-centrifugal compressor
×
引用
GB/T 7714-2015
复制
MLA
复制
APA
复制
导出至
BibTeX EndNote RefMan NoteFirst NoteExpress
×
×
提示
您的信息不完整,为了账户安全,请先补充。
现在去补充
×
提示
您因"违规操作"
具体请查看互助需知
我知道了
×
提示
现在去查看 取消
×
提示
确定
0
微信
客服QQ
Book学术公众号 扫码关注我们
反馈
×
意见反馈
请填写您的意见或建议
请填写您的手机或邮箱
已复制链接
已复制链接
快去分享给好友吧!
我知道了
×
扫码分享
扫码分享
Book学术官方微信
Book学术文献互助
Book学术文献互助群
群 号:481959085
Book学术
文献互助 智能选刊 最新文献 互助须知 联系我们:info@booksci.cn
Book学术提供免费学术资源搜索服务,方便国内外学者检索中英文文献。致力于提供最便捷和优质的服务体验。
Copyright © 2023 Book学术 All rights reserved.
ghs 京公网安备 11010802042870号 京ICP备2023020795号-1