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Numerical investigation of effect of inlet swirl and total-pressure distortion on performance and stability of an axial transonic compressor
This paper represents numerical simulation of flow inside an axial transonic compressor subject to inlet flow distortion, to evaluate its effect on compressor performance and stability. Two types of inlet distortion, namely inlet swirl and total pressure distortion are investigated. To study the eff...
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Published in: | Journal of thermal science 2016-12, Vol.25 (6), p.501-510 |
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creator | Naseri, A. Boroomand, M. Sammak, S. |
description | This paper represents numerical simulation of flow inside an axial transonic compressor subject to inlet flow distortion, to evaluate its effect on compressor performance and stability. Two types of inlet distortion, namely inlet swirl and total pressure distortion are investigated. To study the effect of combined distortion patterns, different combinations of inlet swirl and total pressure distortion are also studied. Results for cases with total pressure distortion indicate that hub radial distortion improves stability range of the compressor while tip radial distortion deteriorates it. An explanation for this observation is presented based on redistribution of flow parameters caused by distortion and the way it interacts with stall inception mechanisms in a transonic axial compressor. Results also show that while co-swirl patterns slightly improve stability range of the compressor, counter-swirl patterns diminish it. Study of combined distortion cases reveals that superimposition of effects of each individual pattern could predict the effect of a combined pattern on compressor’s performance within an accuracy of 1%. However, it is unable to predict the associated effect on compressor’s stability. |
doi_str_mv | 10.1007/s11630-016-0891-6 |
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Two types of inlet distortion, namely inlet swirl and total pressure distortion are investigated. To study the effect of combined distortion patterns, different combinations of inlet swirl and total pressure distortion are also studied. Results for cases with total pressure distortion indicate that hub radial distortion improves stability range of the compressor while tip radial distortion deteriorates it. An explanation for this observation is presented based on redistribution of flow parameters caused by distortion and the way it interacts with stall inception mechanisms in a transonic axial compressor. Results also show that while co-swirl patterns slightly improve stability range of the compressor, counter-swirl patterns diminish it. Study of combined distortion cases reveals that superimposition of effects of each individual pattern could predict the effect of a combined pattern on compressor’s performance within an accuracy of 1%. However, it is unable to predict the associated effect on compressor’s stability.</description><identifier>ISSN: 1003-2169</identifier><identifier>EISSN: 1993-033X</identifier><identifier>DOI: 10.1007/s11630-016-0891-6</identifier><language>eng</language><publisher>Heidelberg: Science Press</publisher><subject>Classical and Continuum Physics ; Engineering Fluid Dynamics ; Engineering Thermodynamics ; Flow distortion ; Heat and Mass Transfer ; Inlet flow ; Performance evaluation ; Physics ; Physics and Astronomy ; Pressure effects ; Stability ; Transonic compressors ; Transonic flow ; Turbocompressors</subject><ispartof>Journal of thermal science, 2016-12, Vol.25 (6), p.501-510</ispartof><rights>Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag Berlin Heidelberg 2016</rights><rights>Copyright Springer Science & Business Media 2016</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c316t-7503676ac292b0901c6d5656b1635cea599127306bdbdc6df208d15759f9beb13</citedby><cites>FETCH-LOGICAL-c316t-7503676ac292b0901c6d5656b1635cea599127306bdbdc6df208d15759f9beb13</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,27923,27924</link.rule.ids></links><search><creatorcontrib>Naseri, A.</creatorcontrib><creatorcontrib>Boroomand, M.</creatorcontrib><creatorcontrib>Sammak, S.</creatorcontrib><title>Numerical investigation of effect of inlet swirl and total-pressure distortion on performance and stability of an axial transonic compressor</title><title>Journal of thermal science</title><addtitle>J. Therm. Sci</addtitle><description>This paper represents numerical simulation of flow inside an axial transonic compressor subject to inlet flow distortion, to evaluate its effect on compressor performance and stability. Two types of inlet distortion, namely inlet swirl and total pressure distortion are investigated. To study the effect of combined distortion patterns, different combinations of inlet swirl and total pressure distortion are also studied. Results for cases with total pressure distortion indicate that hub radial distortion improves stability range of the compressor while tip radial distortion deteriorates it. An explanation for this observation is presented based on redistribution of flow parameters caused by distortion and the way it interacts with stall inception mechanisms in a transonic axial compressor. Results also show that while co-swirl patterns slightly improve stability range of the compressor, counter-swirl patterns diminish it. Study of combined distortion cases reveals that superimposition of effects of each individual pattern could predict the effect of a combined pattern on compressor’s performance within an accuracy of 1%. However, it is unable to predict the associated effect on compressor’s stability.</description><subject>Classical and Continuum Physics</subject><subject>Engineering Fluid Dynamics</subject><subject>Engineering Thermodynamics</subject><subject>Flow distortion</subject><subject>Heat and Mass Transfer</subject><subject>Inlet flow</subject><subject>Performance evaluation</subject><subject>Physics</subject><subject>Physics and Astronomy</subject><subject>Pressure effects</subject><subject>Stability</subject><subject>Transonic compressors</subject><subject>Transonic flow</subject><subject>Turbocompressors</subject><issn>1003-2169</issn><issn>1993-033X</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2016</creationdate><recordtype>article</recordtype><recordid>eNp1kE1LxDAQhosouK7-AG8Bz9FJs02boyx-waIXBW8hTdMlS5vUJPXjP_ijTbcevHiagXnfd2aeLDsncEkAyqtACKOAgTAMFSeYHWQLwjnFQOnrYeoBKM4J48fZSQg7AFYyulpk349jr71RskPGvusQzVZG4yxyLdJtq1WcOmM7HVH4ML5D0jYouig7PHgdwug1akyIzs82iwbtW-d7aZXei0OUtelM_JqSpEXy06Rt0UsbnDUKKdfvk5w_zY5a2QV99luX2cvtzfP6Hm-e7h7W1xusKGERlwXQdL5UOc9r4EAUawpWsDohKJSWBeckLymwuqmbNGtzqBpSlAVvea1rQpfZxZw7ePc2pqfFzo3eppWCVBVUq3xFeVKRWaW8C8HrVgze9NJ_CQJigi5m6CJBFxN0wZInnz0hae1W-z_J_5p-AEMPh4E</recordid><startdate>20161201</startdate><enddate>20161201</enddate><creator>Naseri, A.</creator><creator>Boroomand, M.</creator><creator>Sammak, S.</creator><general>Science Press</general><general>Springer Nature B.V</general><scope>AAYXX</scope><scope>CITATION</scope></search><sort><creationdate>20161201</creationdate><title>Numerical investigation of effect of inlet swirl and total-pressure distortion on performance and stability of an axial transonic compressor</title><author>Naseri, A. ; Boroomand, M. ; Sammak, S.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c316t-7503676ac292b0901c6d5656b1635cea599127306bdbdc6df208d15759f9beb13</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2016</creationdate><topic>Classical and Continuum Physics</topic><topic>Engineering Fluid Dynamics</topic><topic>Engineering Thermodynamics</topic><topic>Flow distortion</topic><topic>Heat and Mass Transfer</topic><topic>Inlet flow</topic><topic>Performance evaluation</topic><topic>Physics</topic><topic>Physics and Astronomy</topic><topic>Pressure effects</topic><topic>Stability</topic><topic>Transonic compressors</topic><topic>Transonic flow</topic><topic>Turbocompressors</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Naseri, A.</creatorcontrib><creatorcontrib>Boroomand, M.</creatorcontrib><creatorcontrib>Sammak, S.</creatorcontrib><collection>CrossRef</collection><jtitle>Journal of thermal science</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Naseri, A.</au><au>Boroomand, M.</au><au>Sammak, S.</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Numerical investigation of effect of inlet swirl and total-pressure distortion on performance and stability of an axial transonic compressor</atitle><jtitle>Journal of thermal science</jtitle><stitle>J. Therm. Sci</stitle><date>2016-12-01</date><risdate>2016</risdate><volume>25</volume><issue>6</issue><spage>501</spage><epage>510</epage><pages>501-510</pages><issn>1003-2169</issn><eissn>1993-033X</eissn><abstract>This paper represents numerical simulation of flow inside an axial transonic compressor subject to inlet flow distortion, to evaluate its effect on compressor performance and stability. Two types of inlet distortion, namely inlet swirl and total pressure distortion are investigated. To study the effect of combined distortion patterns, different combinations of inlet swirl and total pressure distortion are also studied. Results for cases with total pressure distortion indicate that hub radial distortion improves stability range of the compressor while tip radial distortion deteriorates it. An explanation for this observation is presented based on redistribution of flow parameters caused by distortion and the way it interacts with stall inception mechanisms in a transonic axial compressor. Results also show that while co-swirl patterns slightly improve stability range of the compressor, counter-swirl patterns diminish it. Study of combined distortion cases reveals that superimposition of effects of each individual pattern could predict the effect of a combined pattern on compressor’s performance within an accuracy of 1%. However, it is unable to predict the associated effect on compressor’s stability.</abstract><cop>Heidelberg</cop><pub>Science Press</pub><doi>10.1007/s11630-016-0891-6</doi><tpages>10</tpages></addata></record> |
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subjects | Classical and Continuum Physics Engineering Fluid Dynamics Engineering Thermodynamics Flow distortion Heat and Mass Transfer Inlet flow Performance evaluation Physics Physics and Astronomy Pressure effects Stability Transonic compressors Transonic flow Turbocompressors |
title | Numerical investigation of effect of inlet swirl and total-pressure distortion on performance and stability of an axial transonic compressor |
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