Mechanisms of Lean on the Performance of Transonic Centrifugal Compressor Impellers
Transonic centrifugal compressors with high performance are required in modern gas turbine engines and turbochargers. Lean of the blades is one of the crucial features that have a significant influence on their performance. This paper numerically investigates mechanisms by which lean affects the per...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
He, Xiao [verfasserIn] |
|---|
| Format: |
Artikel |
|---|---|
| Sprache: |
Englisch |
| Erschienen: |
2016 |
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| Rechteinformationen: |
Nutzungsrecht: Copyright © 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Copies of this paper may be made for personal and internal use, on condition that the copier pay the per-copy fee to the Copyright Clearance Center (CCC). All requests for copying and permission to reprint should be submitted to CCC at ; employ the ISSN (print) or (online) to initiate your request. |
|---|
| Übergeordnetes Werk: |
Enthalten in: Journal of propulsion and power - New York, NY : AIAA, 1985, 32(2016), 5, Seite 1220-1229 |
|---|---|
| Übergeordnetes Werk: |
volume:32 ; year:2016 ; number:5 ; pages:1220-1229 |
| Links: |
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| DOI / URN: |
10.2514/1.B36008 |
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OLC1982696095 |
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| 520 | |a Transonic centrifugal compressors with high performance are required in modern gas turbine engines and turbochargers. Lean of the blades is one of the crucial features that have a significant influence on their performance. This paper numerically investigates mechanisms by which lean affects the performance of a transonic impeller with twin splitters. Lean is defined relative to the tangential direction, and the variation range of lean angle has been chosen from −5 to +5 deg. Results show that the variation of efficiency value is 4.5% and the optimal lean angle occurs near 0 deg. Lean influences the flowfields through the effects on the shock structure, the spanwise pressure gradient, the axial-to-radial flow separation, and the secondary flow structure. The induced second blade surface vortex with positive lean tends to migrate the low-momentum flow from hub to shroud, whereas the induced inward spanwise pressure gradient with negative lean enhances the axial-to-radial flow separation, both of which increase the tip leakage loss and lead to the efficiency drop of leaned designs. The optimal lean angle is deduced to be the result of a trade-off between the suppression of axial-to-radial flow separation and the suppression of secondary flow. | ||
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10.2514/1.B36008 doi PQ20161012 (DE-627)OLC1982696095 (DE-599)GBVOLC1982696095 (PRQ)a872-76719627f21a8c7cc7e0acd28bb45b043fbfe0d0af581b98c0d38c862a40f0c50 (KEY)0137686120160000032000501220mechanismsofleanontheperformanceoftransoniccentrif DE-627 ger DE-627 rakwb eng 380 DNB 55.50 bkl He, Xiao verfasserin aut Mechanisms of Lean on the Performance of Transonic Centrifugal Compressor Impellers 2016 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier Transonic centrifugal compressors with high performance are required in modern gas turbine engines and turbochargers. Lean of the blades is one of the crucial features that have a significant influence on their performance. This paper numerically investigates mechanisms by which lean affects the performance of a transonic impeller with twin splitters. Lean is defined relative to the tangential direction, and the variation range of lean angle has been chosen from −5 to +5 deg. Results show that the variation of efficiency value is 4.5% and the optimal lean angle occurs near 0 deg. Lean influences the flowfields through the effects on the shock structure, the spanwise pressure gradient, the axial-to-radial flow separation, and the secondary flow structure. The induced second blade surface vortex with positive lean tends to migrate the low-momentum flow from hub to shroud, whereas the induced inward spanwise pressure gradient with negative lean enhances the axial-to-radial flow separation, both of which increase the tip leakage loss and lead to the efficiency drop of leaned designs. The optimal lean angle is deduced to be the result of a trade-off between the suppression of axial-to-radial flow separation and the suppression of secondary flow. Nutzungsrecht: Copyright © 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Copies of this paper may be made for personal and internal use, on condition that the copier pay the per-copy fee to the Copyright Clearance Center (CCC). All requests for copying and permission to reprint should be submitted to CCC at ; employ the ISSN (print) or (online) to initiate your request. Zheng, Xinqian oth Enthalten in Journal of propulsion and power New York, NY : AIAA, 1985 32(2016), 5, Seite 1220-1229 (DE-627)129170992 (DE-600)51014-2 (DE-576)03847364X 0748-4658 nnns volume:32 year:2016 number:5 pages:1220-1229 http://dx.doi.org/10.2514/1.B36008 Volltext http://arc.aiaa.org/doi/full/10.2514/1.B36008 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_70 GBV_ILN_4046 GBV_ILN_4700 55.50 AVZ AR 32 2016 5 1220-1229 |
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10.2514/1.B36008 doi PQ20161012 (DE-627)OLC1982696095 (DE-599)GBVOLC1982696095 (PRQ)a872-76719627f21a8c7cc7e0acd28bb45b043fbfe0d0af581b98c0d38c862a40f0c50 (KEY)0137686120160000032000501220mechanismsofleanontheperformanceoftransoniccentrif DE-627 ger DE-627 rakwb eng 380 DNB 55.50 bkl He, Xiao verfasserin aut Mechanisms of Lean on the Performance of Transonic Centrifugal Compressor Impellers 2016 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier Transonic centrifugal compressors with high performance are required in modern gas turbine engines and turbochargers. Lean of the blades is one of the crucial features that have a significant influence on their performance. This paper numerically investigates mechanisms by which lean affects the performance of a transonic impeller with twin splitters. Lean is defined relative to the tangential direction, and the variation range of lean angle has been chosen from −5 to +5 deg. Results show that the variation of efficiency value is 4.5% and the optimal lean angle occurs near 0 deg. Lean influences the flowfields through the effects on the shock structure, the spanwise pressure gradient, the axial-to-radial flow separation, and the secondary flow structure. The induced second blade surface vortex with positive lean tends to migrate the low-momentum flow from hub to shroud, whereas the induced inward spanwise pressure gradient with negative lean enhances the axial-to-radial flow separation, both of which increase the tip leakage loss and lead to the efficiency drop of leaned designs. The optimal lean angle is deduced to be the result of a trade-off between the suppression of axial-to-radial flow separation and the suppression of secondary flow. Nutzungsrecht: Copyright © 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Copies of this paper may be made for personal and internal use, on condition that the copier pay the per-copy fee to the Copyright Clearance Center (CCC). All requests for copying and permission to reprint should be submitted to CCC at ; employ the ISSN (print) or (online) to initiate your request. Zheng, Xinqian oth Enthalten in Journal of propulsion and power New York, NY : AIAA, 1985 32(2016), 5, Seite 1220-1229 (DE-627)129170992 (DE-600)51014-2 (DE-576)03847364X 0748-4658 nnns volume:32 year:2016 number:5 pages:1220-1229 http://dx.doi.org/10.2514/1.B36008 Volltext http://arc.aiaa.org/doi/full/10.2514/1.B36008 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_70 GBV_ILN_4046 GBV_ILN_4700 55.50 AVZ AR 32 2016 5 1220-1229 |
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10.2514/1.B36008 doi PQ20161012 (DE-627)OLC1982696095 (DE-599)GBVOLC1982696095 (PRQ)a872-76719627f21a8c7cc7e0acd28bb45b043fbfe0d0af581b98c0d38c862a40f0c50 (KEY)0137686120160000032000501220mechanismsofleanontheperformanceoftransoniccentrif DE-627 ger DE-627 rakwb eng 380 DNB 55.50 bkl He, Xiao verfasserin aut Mechanisms of Lean on the Performance of Transonic Centrifugal Compressor Impellers 2016 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier Transonic centrifugal compressors with high performance are required in modern gas turbine engines and turbochargers. Lean of the blades is one of the crucial features that have a significant influence on their performance. This paper numerically investigates mechanisms by which lean affects the performance of a transonic impeller with twin splitters. Lean is defined relative to the tangential direction, and the variation range of lean angle has been chosen from −5 to +5 deg. Results show that the variation of efficiency value is 4.5% and the optimal lean angle occurs near 0 deg. Lean influences the flowfields through the effects on the shock structure, the spanwise pressure gradient, the axial-to-radial flow separation, and the secondary flow structure. The induced second blade surface vortex with positive lean tends to migrate the low-momentum flow from hub to shroud, whereas the induced inward spanwise pressure gradient with negative lean enhances the axial-to-radial flow separation, both of which increase the tip leakage loss and lead to the efficiency drop of leaned designs. The optimal lean angle is deduced to be the result of a trade-off between the suppression of axial-to-radial flow separation and the suppression of secondary flow. Nutzungsrecht: Copyright © 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Copies of this paper may be made for personal and internal use, on condition that the copier pay the per-copy fee to the Copyright Clearance Center (CCC). All requests for copying and permission to reprint should be submitted to CCC at ; employ the ISSN (print) or (online) to initiate your request. Zheng, Xinqian oth Enthalten in Journal of propulsion and power New York, NY : AIAA, 1985 32(2016), 5, Seite 1220-1229 (DE-627)129170992 (DE-600)51014-2 (DE-576)03847364X 0748-4658 nnns volume:32 year:2016 number:5 pages:1220-1229 http://dx.doi.org/10.2514/1.B36008 Volltext http://arc.aiaa.org/doi/full/10.2514/1.B36008 GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_70 GBV_ILN_4046 GBV_ILN_4700 55.50 AVZ AR 32 2016 5 1220-1229 |
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Mechanisms of Lean on the Performance of Transonic Centrifugal Compressor Impellers |
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Mechanisms of Lean on the Performance of Transonic Centrifugal Compressor Impellers |
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He, Xiao |
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Journal of propulsion and power |
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He, Xiao |
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10.2514/1.B36008 |
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380 |
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mechanisms of lean on the performance of transonic centrifugal compressor impellers |
| title_auth |
Mechanisms of Lean on the Performance of Transonic Centrifugal Compressor Impellers |
| abstract |
Transonic centrifugal compressors with high performance are required in modern gas turbine engines and turbochargers. Lean of the blades is one of the crucial features that have a significant influence on their performance. This paper numerically investigates mechanisms by which lean affects the performance of a transonic impeller with twin splitters. Lean is defined relative to the tangential direction, and the variation range of lean angle has been chosen from −5 to +5 deg. Results show that the variation of efficiency value is 4.5% and the optimal lean angle occurs near 0 deg. Lean influences the flowfields through the effects on the shock structure, the spanwise pressure gradient, the axial-to-radial flow separation, and the secondary flow structure. The induced second blade surface vortex with positive lean tends to migrate the low-momentum flow from hub to shroud, whereas the induced inward spanwise pressure gradient with negative lean enhances the axial-to-radial flow separation, both of which increase the tip leakage loss and lead to the efficiency drop of leaned designs. The optimal lean angle is deduced to be the result of a trade-off between the suppression of axial-to-radial flow separation and the suppression of secondary flow. |
| abstractGer |
Transonic centrifugal compressors with high performance are required in modern gas turbine engines and turbochargers. Lean of the blades is one of the crucial features that have a significant influence on their performance. This paper numerically investigates mechanisms by which lean affects the performance of a transonic impeller with twin splitters. Lean is defined relative to the tangential direction, and the variation range of lean angle has been chosen from −5 to +5 deg. Results show that the variation of efficiency value is 4.5% and the optimal lean angle occurs near 0 deg. Lean influences the flowfields through the effects on the shock structure, the spanwise pressure gradient, the axial-to-radial flow separation, and the secondary flow structure. The induced second blade surface vortex with positive lean tends to migrate the low-momentum flow from hub to shroud, whereas the induced inward spanwise pressure gradient with negative lean enhances the axial-to-radial flow separation, both of which increase the tip leakage loss and lead to the efficiency drop of leaned designs. The optimal lean angle is deduced to be the result of a trade-off between the suppression of axial-to-radial flow separation and the suppression of secondary flow. |
| abstract_unstemmed |
Transonic centrifugal compressors with high performance are required in modern gas turbine engines and turbochargers. Lean of the blades is one of the crucial features that have a significant influence on their performance. This paper numerically investigates mechanisms by which lean affects the performance of a transonic impeller with twin splitters. Lean is defined relative to the tangential direction, and the variation range of lean angle has been chosen from −5 to +5 deg. Results show that the variation of efficiency value is 4.5% and the optimal lean angle occurs near 0 deg. Lean influences the flowfields through the effects on the shock structure, the spanwise pressure gradient, the axial-to-radial flow separation, and the secondary flow structure. The induced second blade surface vortex with positive lean tends to migrate the low-momentum flow from hub to shroud, whereas the induced inward spanwise pressure gradient with negative lean enhances the axial-to-radial flow separation, both of which increase the tip leakage loss and lead to the efficiency drop of leaned designs. The optimal lean angle is deduced to be the result of a trade-off between the suppression of axial-to-radial flow separation and the suppression of secondary flow. |
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| title_short |
Mechanisms of Lean on the Performance of Transonic Centrifugal Compressor Impellers |
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http://dx.doi.org/10.2514/1.B36008 http://arc.aiaa.org/doi/full/10.2514/1.B36008 |
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Zheng, Xinqian |
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2024-07-03T18:17:30.627Z |
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