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Article: Aerodynamic mechanism of blade end bending technique
| Title | Aerodynamic mechanism of blade end bending technique 葉片端彎技術機理探討 |
|---|---|
| Authors | |
| Issue Date | 1988 |
| Publisher | Zhongguo 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 Identifier | http://hdl.handle.net/10722/161618 |
| ISSN | 2020 SCImago Journal Rankings: 0.251 |
| DC Field | Value | Language |
|---|---|---|
| dc.contributor.author | Huang, L | - |
| dc.contributor.author | Wei, XL | - |
| dc.contributor.author | Peng , ZY | - |
| dc.date.accessioned | 2012-09-04T08:43:44Z | - |
| dc.date.available | 2012-09-04T08:43:44Z | - |
| dc.date.issued | 1988 | - |
| dc.identifier.citation | Journal 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.issn | 1000-8055 | - |
| dc.identifier.uri | http://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.abstract | 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. | - |
| dc.language | chi | - |
| dc.publisher | Zhongguo Hangkong Xuehui (中國航空學會) | - |
| dc.relation.ispartof | Journal of Aerospace Power | - |
| dc.relation.ispartof | 航空動力學報 (Hangkong Dongli Xuebao) | - |
| dc.title | Aerodynamic mechanism of blade end bending technique | en_US |
| dc.title | 葉片端彎技術機理探討 | - |
| dc.type | Article | en_US |
| dc.identifier.email | Huang, L: lixi@hku.hk | - |
| dc.identifier.volume | 3 | - |
| dc.identifier.issue | 3 | - |
| dc.identifier.spage | 219 | - |
| dc.identifier.epage | 222 | - |
| dc.publisher.place | China (中國) | - |
| dc.identifier.issnl | 1000-8055 | - |