Numerical study on the effect of blade tip clearance change on stall margin of the transonic axial flow compressor rotor
The change of the blade tip clearance size has an important impact on the performance of the compressor. Considering that the performance curve of the compressor is often limited by surge and stall boundaries, this paper used the numerical simulation method to investigate the influence mechanism of...
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| Veröffentlicht in: | Proceedings of the Institution of Mechanical Engineers. Part A, Journal of power and energy Journal of power and energy, 2022-03, Vol.236 (2), p.194-207 |
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| container_title | Proceedings of the Institution of Mechanical Engineers. Part A, Journal of power and energy |
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| creator | Yan, Song Chu, Wuli Li, Yu Dai, YuChen |
| description | The change of the blade tip clearance size has an important impact on the performance of the compressor. Considering that the performance curve of the compressor is often limited by surge and stall boundaries, this paper used the numerical simulation method to investigate the influence mechanism of the blade tip clearance size change on the stall margin of transonic axial flow compressor rotor. By mathematically decomposing the calculation formula of the stall margin of rotor, the approximate calculation formula of the change of rotor’s stall margin was obtained. Then, the detailed quantitative analysis of the factors that affect the rotor’s stall margin was carried out, the influence weights of various factors on the rotor’s stall margin was also obtained. Finally, the physical mechanism of the change of the rotor’s performance parameters was obtained by the analysis of rotor tip flow field after the blade tip clearance size change. |
| doi_str_mv | 10.1177/09576509211036807 |
| format | Article |
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Considering that the performance curve of the compressor is often limited by surge and stall boundaries, this paper used the numerical simulation method to investigate the influence mechanism of the blade tip clearance size change on the stall margin of transonic axial flow compressor rotor. By mathematically decomposing the calculation formula of the stall margin of rotor, the approximate calculation formula of the change of rotor’s stall margin was obtained. Then, the detailed quantitative analysis of the factors that affect the rotor’s stall margin was carried out, the influence weights of various factors on the rotor’s stall margin was also obtained. Finally, the physical mechanism of the change of the rotor’s performance parameters was obtained by the analysis of rotor tip flow field after the blade tip clearance size change.</description><identifier>ISSN: 0957-6509</identifier><identifier>EISSN: 2041-2967</identifier><identifier>DOI: 10.1177/09576509211036807</identifier><language>eng</language><publisher>London, England: SAGE Publications</publisher><subject>Blade tips ; Compressor rotors ; Tip clearance ; Transonic flow ; Turbocompressors</subject><ispartof>Proceedings of the Institution of Mechanical Engineers. 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Part A, Journal of power and energy</title><description>The change of the blade tip clearance size has an important impact on the performance of the compressor. Considering that the performance curve of the compressor is often limited by surge and stall boundaries, this paper used the numerical simulation method to investigate the influence mechanism of the blade tip clearance size change on the stall margin of transonic axial flow compressor rotor. By mathematically decomposing the calculation formula of the stall margin of rotor, the approximate calculation formula of the change of rotor’s stall margin was obtained. Then, the detailed quantitative analysis of the factors that affect the rotor’s stall margin was carried out, the influence weights of various factors on the rotor’s stall margin was also obtained. Finally, the physical mechanism of the change of the rotor’s performance parameters was obtained by the analysis of rotor tip flow field after the blade tip clearance size change.</description><subject>Blade tips</subject><subject>Compressor rotors</subject><subject>Tip clearance</subject><subject>Transonic flow</subject><subject>Turbocompressors</subject><issn>0957-6509</issn><issn>2041-2967</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2022</creationdate><recordtype>article</recordtype><recordid>eNp1kM1OwzAQhC0EEqXwANwscU7xT2I7R1QBRargAufIcdZtqjQOtiPat8dRkTgg9rKH_WZWMwjdUrKgVMp7UhZSFKRklBIuFJFnaMZITjNWCnmOZtM9m4BLdBXCjqQpJJuhw-u4B98a3eEQx-aIXY_jFjBYCyZiZ3Hd6QZwbAdsOtBe9waw2ep-AxMbou46vNd-0_YTPWljgoLrW4P1oU3GtnNf2Lj94CEE57F30flrdGF1F-DmZ8_Rx9Pj-3KVrd-eX5YP68wwkceMKWtrDpxDXhdKFU2TcjIgTa0kJcoIygsLQIQBRWtbG9CESwqW6UY0OfA5ujv5Dt59jhBitXOj79PLignOJKelIomiJ8p4F4IHWw2-TamOFSXVVHD1p-CkWZw0QW_g1_V_wTfldny9</recordid><startdate>202203</startdate><enddate>202203</enddate><creator>Yan, Song</creator><creator>Chu, Wuli</creator><creator>Li, Yu</creator><creator>Dai, YuChen</creator><general>SAGE Publications</general><general>SAGE PUBLICATIONS, INC</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7SP</scope><scope>7TB</scope><scope>8FD</scope><scope>F28</scope><scope>FR3</scope><scope>KR7</scope><scope>L7M</scope><orcidid>https://orcid.org/0000-0002-4209-3159</orcidid></search><sort><creationdate>202203</creationdate><title>Numerical study on the effect of blade tip clearance change on stall margin of the transonic axial flow compressor rotor</title><author>Yan, Song ; Chu, Wuli ; Li, Yu ; Dai, YuChen</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c264t-28ffb3e33e4b5885dd5762e0db87108c6135fee06ce81bfbcea0371ef2ad6d4e3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2022</creationdate><topic>Blade tips</topic><topic>Compressor rotors</topic><topic>Tip clearance</topic><topic>Transonic flow</topic><topic>Turbocompressors</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Yan, Song</creatorcontrib><creatorcontrib>Chu, Wuli</creatorcontrib><creatorcontrib>Li, Yu</creatorcontrib><creatorcontrib>Dai, YuChen</creatorcontrib><collection>CrossRef</collection><collection>Electronics & Communications Abstracts</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>ANTE: Abstracts in New Technology & Engineering</collection><collection>Engineering Research Database</collection><collection>Civil Engineering Abstracts</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Proceedings of the Institution of Mechanical Engineers. 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Considering that the performance curve of the compressor is often limited by surge and stall boundaries, this paper used the numerical simulation method to investigate the influence mechanism of the blade tip clearance size change on the stall margin of transonic axial flow compressor rotor. By mathematically decomposing the calculation formula of the stall margin of rotor, the approximate calculation formula of the change of rotor’s stall margin was obtained. Then, the detailed quantitative analysis of the factors that affect the rotor’s stall margin was carried out, the influence weights of various factors on the rotor’s stall margin was also obtained. 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| ispartof | Proceedings of the Institution of Mechanical Engineers. Part A, Journal of power and energy, 2022-03, Vol.236 (2), p.194-207 |
| issn | 0957-6509 2041-2967 |
| language | eng |
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| source | SAGE Complete |
| subjects | Blade tips Compressor rotors Tip clearance Transonic flow Turbocompressors |
| title | Numerical study on the effect of blade tip clearance change on stall margin of the transonic axial flow compressor rotor |
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