HIGH SPEED SCHLIEREN EXPERIMENTAL STUDY OF HIGH PRESSURE TURBINE CASCADE UNDER SUBSONIC AND TRANSONIC CONDITIONS.
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| Title: | HIGH SPEED SCHLIEREN EXPERIMENTAL STUDY OF HIGH PRESSURE TURBINE CASCADE UNDER SUBSONIC AND TRANSONIC CONDITIONS. |
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| Authors: | WU, Xingshuang1, YANG, Rongfei1 yrf@nuaa.edu.cn, CHEN, Qiang2, GE, Ning1, ZHANG, Zhibo2 |
| Source: | Thermal Science. 2026, Vol. 30 Issue 3B, p2089-2099. 11p. |
| Subjects: | Transonic flow, Wakes (Fluid dynamics), Turbine blades, Subsonic flow, Turbines, Proper orthogonal decomposition, Flow visualization, Fluid flow |
| Abstract: | Experiments were conducted on a planner cascade test rig for the typical high pressure turbine blade profile VK ILS89 under conditions at a 0° inlet flow angle and exit Mach numbers of 0.55, 0.85, and 1.1. A high speed schlieren system was used to capture time-varying grayscale images of the region near the trailing edge of the blade. The variations in grayscale within these images are primarily caused by changes in the density gradient of the flow field and are correlated with the unsteady characteristics of the flow structure. Firstly, the mean grayscale value and roof mean square value of the time-series images were analyzed, with these values being correlated with the wake width and wake pulsation amplitude, respectively. As the exit Mach number of the blade cascade increases, both the wake width and wake pulsation amplitude increase, and a trend that is more pronounced at supersonic exit Mach numbers. In addition, the position of the wake centerline of the blade remains unchanged under subsonic conditions at the cascade outlet, but shifts towards the suction surface of the blade under transonic conditions. Further, the modal analysis results of proper orthogonal decomposition also reveal that the unsteadiness of the flow within the cascade is dominated by the wake under subsonic outflow conditions and by the wake-shock wave interaction under transonic outflow conditions. [ABSTRACT FROM AUTHOR] |
| Copyright of Thermal Science is the property of Society of Thermal Engineers of Serbia and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Database: | Engineering Source |
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| Items | – Name: Title Label: Title Group: Ti Data: HIGH SPEED SCHLIEREN EXPERIMENTAL STUDY OF HIGH PRESSURE TURBINE CASCADE UNDER SUBSONIC AND TRANSONIC CONDITIONS. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22WU%2C+Xingshuang%22">WU, Xingshuang</searchLink><relatesTo>1</relatesTo><br /><searchLink fieldCode="AR" term="%22YANG%2C+Rongfei%22">YANG, Rongfei</searchLink><relatesTo>1</relatesTo><i> yrf@nuaa.edu.cn</i><br /><searchLink fieldCode="AR" term="%22CHEN%2C+Qiang%22">CHEN, Qiang</searchLink><relatesTo>2</relatesTo><br /><searchLink fieldCode="AR" term="%22GE%2C+Ning%22">GE, Ning</searchLink><relatesTo>1</relatesTo><br /><searchLink fieldCode="AR" term="%22ZHANG%2C+Zhibo%22">ZHANG, Zhibo</searchLink><relatesTo>2</relatesTo> – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22Thermal+Science%22">Thermal Science</searchLink>. 2026, Vol. 30 Issue 3B, p2089-2099. 11p. – Name: Subject Label: Subjects Group: Su Data: <searchLink fieldCode="DE" term="%22Transonic+flow%22">Transonic flow</searchLink><br /><searchLink fieldCode="DE" term="%22Wakes+%28Fluid+dynamics%29%22">Wakes (Fluid dynamics)</searchLink><br /><searchLink fieldCode="DE" term="%22Turbine+blades%22">Turbine blades</searchLink><br /><searchLink fieldCode="DE" term="%22Subsonic+flow%22">Subsonic flow</searchLink><br /><searchLink fieldCode="DE" term="%22Turbines%22">Turbines</searchLink><br /><searchLink fieldCode="DE" term="%22Proper+orthogonal+decomposition%22">Proper orthogonal decomposition</searchLink><br /><searchLink fieldCode="DE" term="%22Flow+visualization%22">Flow visualization</searchLink><br /><searchLink fieldCode="DE" term="%22Fluid+flow%22">Fluid flow</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: Experiments were conducted on a planner cascade test rig for the typical high pressure turbine blade profile VK ILS89 under conditions at a 0° inlet flow angle and exit Mach numbers of 0.55, 0.85, and 1.1. A high speed schlieren system was used to capture time-varying grayscale images of the region near the trailing edge of the blade. The variations in grayscale within these images are primarily caused by changes in the density gradient of the flow field and are correlated with the unsteady characteristics of the flow structure. Firstly, the mean grayscale value and roof mean square value of the time-series images were analyzed, with these values being correlated with the wake width and wake pulsation amplitude, respectively. As the exit Mach number of the blade cascade increases, both the wake width and wake pulsation amplitude increase, and a trend that is more pronounced at supersonic exit Mach numbers. In addition, the position of the wake centerline of the blade remains unchanged under subsonic conditions at the cascade outlet, but shifts towards the suction surface of the blade under transonic conditions. Further, the modal analysis results of proper orthogonal decomposition also reveal that the unsteadiness of the flow within the cascade is dominated by the wake under subsonic outflow conditions and by the wake-shock wave interaction under transonic outflow conditions. [ABSTRACT FROM AUTHOR] – Name: AbstractSuppliedCopyright Label: Group: Ab Data: <i>Copyright of Thermal Science is the property of Society of Thermal Engineers of Serbia and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.) |
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| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.2298/TSCI250816234W Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 11 StartPage: 2089 Subjects: – SubjectFull: Transonic flow Type: general – SubjectFull: Wakes (Fluid dynamics) Type: general – SubjectFull: Turbine blades Type: general – SubjectFull: Subsonic flow Type: general – SubjectFull: Turbines Type: general – SubjectFull: Proper orthogonal decomposition Type: general – SubjectFull: Flow visualization Type: general – SubjectFull: Fluid flow Type: general Titles: – TitleFull: HIGH SPEED SCHLIEREN EXPERIMENTAL STUDY OF HIGH PRESSURE TURBINE CASCADE UNDER SUBSONIC AND TRANSONIC CONDITIONS. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: WU, Xingshuang – PersonEntity: Name: NameFull: YANG, Rongfei – PersonEntity: Name: NameFull: CHEN, Qiang – PersonEntity: Name: NameFull: GE, Ning – PersonEntity: Name: NameFull: ZHANG, Zhibo IsPartOfRelationships: – BibEntity: Dates: – D: 15 M: 03 Text: 2026 Type: published Y: 2026 Identifiers: – Type: issn-print Value: 03549836 Numbering: – Type: volume Value: 30 – Type: issue Value: 3B Titles: – TitleFull: Thermal Science Type: main |
| ResultId | 1 |
