Influences of the Flow Cut and Axial Lift of the Impeller on the Aerodynamic Performance of a Transonic Centrifugal Compressor
DC Field | Value | Language |
---|---|---|
dc.contributor.author | Park, Kun Sung | - |
dc.contributor.author | Jung, In Hyuk | - |
dc.contributor.author | You, Sung Jin | - |
dc.contributor.author | Lee, Seung Yeob | - |
dc.contributor.author | Zamiri, Ali | - |
dc.contributor.author | Chung, Jin Taek | - |
dc.date.accessioned | 2021-08-31T22:54:46Z | - |
dc.date.available | 2021-08-31T22:54:46Z | - |
dc.date.created | 2021-06-18 | - |
dc.date.issued | 2019-12 | - |
dc.identifier.issn | 1996-1073 | - |
dc.identifier.uri | https://scholar.korea.ac.kr/handle/2021.sw.korea/61493 | - |
dc.description.abstract | In this study, the influences of the flow cut and axial lift of the impeller on the aerodynamic performance of a transonic centrifugal compressor were analyzed. The flow cut is a method to reduce the flow rate by decreasing the impeller passage height. The axial lift is a method of increasing the impeller passage height in the axial direction, which increases the impeller exit width (B2) and increases the total pressure. A NASA CC3 transonic centrifugal compressor with a backswept angle was used as a base compressor. After applying the flow cut, the total pressure at the target flow rate was lower than the total pressure at the design point due to the increase in the relative velocity at the impeller exit. After applying the axial lift, the total pressure at the design flow rate was increased, which was caused by the reduction in the relative velocity as the passage area at the impeller exit was increased. By applying the flow cut and axial lift methods, it was shown that the variation in relative velocity at the impeller exit has a significant effect on the variation in total pressure. In addition, it was found that the relative velocity at the impeller exit of the target flow rate is maintained similar to the base impeller when the flow cut and the axial lift are combined. Therefore, by combining the flow cut and the axial lift, three transonic centrifugal impellers with flow fractions of 0.7, 0.8, and 0.9 compared to the design flow rate were newly designed. | - |
dc.language | English | - |
dc.language.iso | en | - |
dc.publisher | MDPI | - |
dc.title | Influences of the Flow Cut and Axial Lift of the Impeller on the Aerodynamic Performance of a Transonic Centrifugal Compressor | - |
dc.type | Article | - |
dc.contributor.affiliatedAuthor | Chung, Jin Taek | - |
dc.identifier.doi | 10.3390/en12234503 | - |
dc.identifier.scopusid | 2-s2.0-85076193227 | - |
dc.identifier.wosid | 000514090100101 | - |
dc.identifier.bibliographicCitation | ENERGIES, v.12, no.23 | - |
dc.relation.isPartOf | ENERGIES | - |
dc.citation.title | ENERGIES | - |
dc.citation.volume | 12 | - |
dc.citation.number | 23 | - |
dc.type.rims | ART | - |
dc.type.docType | Article | - |
dc.description.journalClass | 1 | - |
dc.description.journalRegisteredClass | scie | - |
dc.description.journalRegisteredClass | scopus | - |
dc.relation.journalResearchArea | Energy & Fuels | - |
dc.relation.journalWebOfScienceCategory | Energy & Fuels | - |
dc.subject.keywordAuthor | transonic centrifugal compressor | - |
dc.subject.keywordAuthor | backswept angle | - |
dc.subject.keywordAuthor | flow cut | - |
dc.subject.keywordAuthor | axial lift | - |
dc.subject.keywordAuthor | relative velocity | - |
dc.subject.keywordAuthor | aerodynamic design | - |
dc.subject.keywordAuthor | impeller | - |
Items in ScholarWorks are protected by copyright, with all rights reserved, unless otherwise indicated.
(02841) 서울특별시 성북구 안암로 14502-3290-1114
COPYRIGHT © 2021 Korea University. All Rights Reserved.
Certain data included herein are derived from the © Web of Science of Clarivate Analytics. All rights reserved.
You may not copy or re-distribute this material in whole or in part without the prior written consent of Clarivate Analytics.