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Article: Aerodynamic mechanism of blade end bending technique

TitleAerodynamic mechanism of blade end bending technique
葉片端彎技術機理探討
Authors
Issue Date1988
PublisherZhongguo Hangkong Xuehui (中國航空學會)
Citation
Journal of Aerospace Power, 1988, v. 3 n. 3, p. 219-222 How to Cite?
航空動力學報 (Hangkong Dongli Xuebao), 1988, v. 3 n. 3, p. 219-222 How to Cite?
Abstract本文首次以數值計算,理論分析以及試驗分析的綜合手段探討葉片端彎的氣動機理,分析表明;端彎會導致整個流場再分布,主流場變化可能是影響葉片性能改進的重要因素。
Blade end-bend is a new technique to improve the performance of compressors. A comprehensive study of two multistage compressors has been completed with numerical calculation, theoretical analysis and experimental investigation. It is shown that the end-bend causes redistribution of the whole flowfield,and the changes of characteristics in main flow region may be a vital factor to improve the engine performance. A comparative study of several end-bend patterns shows that the character of redistribution differs for each from other. It is important to choose the end-bend pattern suitable for the specific compressor.
Persistent Identifierhttp://hdl.handle.net/10722/161618
ISSN
2015 SCImago Journal Rankings: 0.280

 

DC FieldValueLanguage
dc.contributor.authorHuang, L-
dc.contributor.authorWei, XL-
dc.contributor.authorPeng , ZY-
dc.date.accessioned2012-09-04T08:43:44Z-
dc.date.available2012-09-04T08:43:44Z-
dc.date.issued1988-
dc.identifier.citationJournal of Aerospace Power, 1988, v. 3 n. 3, p. 219-222-
dc.identifier.citation航空動力學報 (Hangkong Dongli Xuebao), 1988, v. 3 n. 3, p. 219-222-
dc.identifier.issn1000-8055-
dc.identifier.urihttp://hdl.handle.net/10722/161618-
dc.description.abstract本文首次以數值計算,理論分析以及試驗分析的綜合手段探討葉片端彎的氣動機理,分析表明;端彎會導致整個流場再分布,主流場變化可能是影響葉片性能改進的重要因素。-
dc.description.abstractBlade end-bend is a new technique to improve the performance of compressors. A comprehensive study of two multistage compressors has been completed with numerical calculation, theoretical analysis and experimental investigation. It is shown that the end-bend causes redistribution of the whole flowfield,and the changes of characteristics in main flow region may be a vital factor to improve the engine performance. A comparative study of several end-bend patterns shows that the character of redistribution differs for each from other. It is important to choose the end-bend pattern suitable for the specific compressor.-
dc.languagechi-
dc.publisherZhongguo Hangkong Xuehui (中國航空學會)-
dc.relation.ispartofJournal of Aerospace Power-
dc.relation.ispartof航空動力學報 (Hangkong Dongli Xuebao)-
dc.titleAerodynamic mechanism of blade end bending techniqueen_US
dc.title葉片端彎技術機理探討-
dc.typeArticleen_US
dc.identifier.emailHuang, L: lixi@hku.hk-
dc.identifier.volume3-
dc.identifier.issue3-
dc.identifier.spage219-
dc.identifier.epage222-
dc.publisher.placeChina (中國)-

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