Experimental Investigations of Surface Roughness Effects on Aerodynamic Performance of Axial Compressor Blades

Experimental Investigations of Surface Roughness Effects on Aerodynamic Performance of Axial Compressor Blades | Research Square window.SnipcartSettings = { analytics: { enabled: false } }; (function() { var accessVector = localStorage.getItem('access_vector') || ''; window.dataLayer = window.dataLayer || []; if (accessVector) { window.dataLayer.push({ user: { profile: { profileInfo: { snid: accessVector } } } }); } })(); (function(w,d,s,l,i){w[l]=w[l]||[];w[l].push({'gtm.start':new Date().getTime(),event:'gtm.js'});var f=d.getElementsByTagName(s)[0],j=d.createElement(s),dl=l!='dataLayer'?'&l='+l:'';j.async=true;j.src='https://www.googletagmanager.com/gtm.js?id='+i+dl;f.parentNode.insertBefore(j,f);})(window,document,'script','dataLayer','GTM-K279D39R'); Browse Preprints In Review Journals COVID-19 Preprints AJE Video Bytes Research Tools Research Promotion AJE Professional Editing AJE Rubriq About Preprint Platform In Review Editorial Policies Our Team Advisory Board Help Center Sign In Submit a Preprint Cite Share Download PDF Article Experimental Investigations of Surface Roughness Effects on Aerodynamic Performance of Axial Compressor Blades Reza Taghavi Zenouz, Seyyed Mohammad Mahdi Abiri, Mohammad Reza Khosravizadeh This is a preprint; it has not been peer reviewed by a journal. https://doi.org/ 10.21203/rs.3.rs-4427246/v1 This work is licensed under a CC BY 4.0 License Status: Posted Version 1 posted You are reading this latest preprint version Abstract Fluid dynamic of axial compressor blades under different surface roughness levels is experimentally investigated in this research work. An open circuit wind tunnel has been prepared for the test model of a linear cascade of axial compressor blades. Reynolds number ranged between 100000 and 300000 and free turbulence intensity was 2%. Four different roughness levels, ranged between \(10.96 \text{a}\text{n}\text{d} 68.54\mu m\) besides smooth surface case were examined. Hot wire anemometry has been undertaken to extract velocity profiles to distinguish boundary layer type in terms of laminar, transitional or turbulent regimes, and also to investigate occurring laminar separation bubble. Total pressure loss coefficient was also calculated for different Reynolds numbers and surface roughness levels. The results showed that the boundary layer remains in fully laminar regime for flows with Reynolds numbers less than about 150000 for smooth surface case. At the lowest test Reynolds number adding surface roughness caused the total pressure loss to decrease. Highest Reynolds number was accompanied by the lowest losses for the smooth surface. Increasing the surface roughness caused losses to increase at this Reynolds number. Furthermore, roughening the surface caused the bubble to shrink, and transition point to shift upstream accompanied by reduction in pressure loss. Physical sciences/Engineering Physical sciences/Engineering/Mechanical engineering Axial compressor blade Surface roughness Transition Laminar separation bubble Full Text Additional Declarations No competing interests reported. Cite Share Download PDF Status: Posted Version 1 posted You are reading this latest preprint version Research Square lets you share your work early, gain feedback from the community, and start making changes to your manuscript prior to peer review in a journal. As a division of Research Square Company, we’re committed to making research communication faster, fairer, and more useful. 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Also discoverable on Platform About Our Team In Review Editorial Policies Advisory Board Help Center Resources Author Services Accessibility API Access RSS feed Manage Cookie Preferences © Research Square 2026 | ISSN 2693-5015 (online) Privacy Policy Terms of Service Do Not Sell My Personal Information {"props":{"pageProps":{"initialData":{"identity":"rs-4427246","acceptedTermsAndConditions":true,"allowDirectSubmit":true,"archivedVersions":[],"articleType":"Article","associatedPublications":[],"authors":[{"id":309631888,"identity":"c11b101a-aa7f-4717-a791-910a5dd7b5fd","order_by":0,"name":"Reza Taghavi Zenouz","email":"data:image/png;base64,iVBORw0KGgoAAAANSUhEUgAAAZAAAAAyAQMAAABI0h/eAAAABlBMVEX///8AAABVwtN+AAAACXBIWXMAAA7EAAAOxAGVKw4bAAAAz0lEQVRIiWNgGAWjYHACNiCWkGND5uIFPFAtxkCSsYEULQyJDTAtBIE9+/FrD362WaT3SaQ/f8BQY8fAJ32AgC08OeWGvW0SuW0SOYYNDMeSGdj4Egg5LCdNgucMWAvQYWwHGNh4CDiMh/9NmuSfMxLpbBLpDxsY/hGjRSL9mDRPhUQCm0SCYQNjGzFabrxhk5apkDBs43ljOCOxL5mHoBb2/vRnkm8M6uTl29MffPjwzU5OvoeAFqA9Bgh2AjiiCAL2B0QoGgWjYBSMghENAM4PNNfeA49wAAAAAElFTkSuQmCC","orcid":"","institution":"Iran University of Science and Technology","correspondingAuthor":true,"prefix":"","firstName":"Reza","middleName":"Taghavi","lastName":"Zenouz","suffix":""},{"id":309631889,"identity":"019f06f5-eeaf-4e64-b287-64fc6f609240","order_by":1,"name":"Seyyed Mohammad Mahdi Abiri","email":"","orcid":"","institution":"Iran University of Science and Technology","correspondingAuthor":false,"prefix":"","firstName":"Seyyed","middleName":"Mohammad Mahdi","lastName":"Abiri","suffix":""},{"id":309631890,"identity":"a98ee1b5-9c43-40d0-8e68-64d6919fce4b","order_by":2,"name":"Mohammad Reza Khosravizadeh","email":"","orcid":"","institution":"Iran University of Science and Technology","correspondingAuthor":false,"prefix":"","firstName":"Mohammad","middleName":"Reza","lastName":"Khosravizadeh","suffix":""}],"badges":[],"createdAt":"2024-05-15 20:53:22","currentVersionCode":1,"declarations":"","doi":"10.21203/rs.3.rs-4427246/v1","doiUrl":"https://doi.org/10.21203/rs.3.rs-4427246/v1","draftVersion":[],"editorialEvents":[],"editorialNote":"","failedWorkflow":false,"files":[{"id":74550418,"identity":"6d96891f-4624-4387-9de6-56b0982b7fab","added_by":"auto","created_at":"2025-01-23 10:47:19","extension":"pdf","order_by":1,"title":"","display":"","copyAsset":false,"role":"manuscript-pdf","size":422257,"visible":true,"origin":"","legend":"","description":"","filename":"ExpRoughnessFR3.pdf","url":"https://assets-eu.researchsquare.com/files/rs-4427246/v1_covered_d29bccb3-5106-4794-aa99-4b8b5302d2a6.pdf"}],"financialInterests":"No competing interests reported.","formattedTitle":"Experimental Investigations of Surface Roughness Effects on Aerodynamic Performance of Axial Compressor Blades","fulltext":[],"fulltextSource":"","fullText":"","funders":[],"hasAdminPriorityOnWorkflow":false,"hasManuscriptDocX":false,"hasOptedInToPreprint":true,"hasPassedJournalQc":"","hasAnyPriority":false,"hideJournal":true,"highlight":"","institution":"","isAcceptedByJournal":false,"isAuthorSuppliedPdf":true,"isDeskRejected":"","isHiddenFromSearch":false,"isInQc":false,"isInWorkflow":false,"isPdf":true,"isPdfUpToDate":true,"isWithdrawnOrRetracted":false,"journal":{"display":true,"email":"[email protected]","identity":"researchsquare","isNatureJournal":false,"hasQc":true,"allowDirectSubmit":true,"externalIdentity":"","sideBox":"","snPcode":"","submissionUrl":"/submission","title":"Research Square","twitterHandle":"researchsquare","acdcEnabled":true,"dfaEnabled":false,"editorialSystem":"","reportingPortfolio":"","inReviewEnabled":false,"inReviewRevisionsEnabled":true},"keywords":"Axial compressor blade, Surface roughness, Transition, Laminar separation bubble","lastPublishedDoi":"10.21203/rs.3.rs-4427246/v1","lastPublishedDoiUrl":"https://doi.org/10.21203/rs.3.rs-4427246/v1","license":{"name":"CC BY 4.0","url":"https://creativecommons.org/licenses/by/4.0/"},"manuscriptAbstract":"\u003cp\u003eFluid dynamic of axial compressor blades under different surface roughness levels is experimentally investigated in this research work. An open circuit wind tunnel has been prepared for the test model of a linear cascade of axial compressor blades. Reynolds number ranged between 100000 and 300000 and free turbulence intensity was 2%. Four different roughness levels, ranged between\u003cspan class=\"InlineEquation\"\u003e\u003cspan class=\"mathinline\"\u003e\\(10.96 \\text{a}\\text{n}\\text{d} 68.54\\mu m\\)\u003c/span\u003e\u003c/span\u003e besides smooth surface case were examined. Hot wire anemometry has been undertaken to extract velocity profiles to distinguish boundary layer type in terms of laminar, transitional or turbulent regimes, and also to investigate occurring laminar separation bubble. Total pressure loss coefficient was also calculated for different Reynolds numbers and surface roughness levels. The results showed that the boundary layer remains in fully laminar regime for flows with Reynolds numbers less than about 150000 for smooth surface case. 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