Unsteady Heat Transfer and Pressure Measurements on the Airfoils of a Rotating Transonic Turbine With Multiple Cooling Configurations.
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| Title: | Unsteady Heat Transfer and Pressure Measurements on the Airfoils of a Rotating Transonic Turbine With Multiple Cooling Configurations. |
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| Authors: | Nickol, Jeremy B.1, Mathison, Randall M.1 Mathison.4@osu.edu, Dunn, Michael G.1 dunn.129@osu.edu, Liu, Jong S.2, Malak, Malak F.2 |
| Source: | Journal of Engineering for Gas Turbines & Power. Sep2017, Vol. 139 Issue 9, p1-10. 10p. |
| Abstract: | Measurements are presented for a high-pressure transonic turbine stage operating at design-corrected conditions with forward and aft purge flow and blade film cooling in a short-duration blowdown facility. Four different film-cooling configurations are investigated: simple cylindrical-shaped holes, diffusing fan-shaped holes, an advanced-shaped hole, and uncooled blades. A rainbow turbine approach is used so each of the four blade types comprises a wedge of the overall bladed disk and is investigated simultaneously at identical speed and vane exit conditions. Double-sided Kapton heat-flux gauges are installed at midspan on all three film-cooled blade types, and single-sided Pyrex heat-flux gauges are installed on the uncooled blades. Kulite pressure transducers are installed at midspan on cooled blades with round and fan-shaped cooling holes. Experimental results are presented both as time-averaged values and as time-accurate ensemble-averages. In addition, the results of a steady Reynolds-averaged Navier-Stokes computational fluid dynamics (RANS CFD) computation are compared to the time-averaged data. The computational and experimental results show that the cooled blades reduce heat transfer into the blade significantly from the uncooled case, but the overall differences in heat transfer among the three cooling configurations are small. This challenges previous conclusions for simplified geometries that show shaped cooling holes outperforming cylindrical holes by a great margin. It suggests that the more complicated flow physics associated with an airfoil operating in an engine-representative environment reduces the effectiveness of the shaped cooling holes. Time-accurate comparisons provide some insight into the complicated interactions that are driving these flows and make it difficult to characterize cooling benefits. [ABSTRACT FROM AUTHOR] |
| Copyright of Journal of Engineering for Gas Turbines & Power is the property of American Society of Mechanical Engineers 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 |
| FullText | Text: Availability: 0 |
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| Header | DbId: egs DbLabel: Engineering Source An: 123123477 AccessLevel: 6 PubType: Academic Journal PubTypeId: academicJournal PreciseRelevancyScore: 0 |
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| Items | – Name: Title Label: Title Group: Ti Data: Unsteady Heat Transfer and Pressure Measurements on the Airfoils of a Rotating Transonic Turbine With Multiple Cooling Configurations. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Nickol%2C+Jeremy+B%2E%22">Nickol, Jeremy B.</searchLink><relatesTo>1</relatesTo><br /><searchLink fieldCode="AR" term="%22Mathison%2C+Randall+M%2E%22">Mathison, Randall M.</searchLink><relatesTo>1</relatesTo><i> Mathison.4@osu.edu</i><br /><searchLink fieldCode="AR" term="%22Dunn%2C+Michael+G%2E%22">Dunn, Michael G.</searchLink><relatesTo>1</relatesTo><i> dunn.129@osu.edu</i><br /><searchLink fieldCode="AR" term="%22Liu%2C+Jong+S%2E%22">Liu, Jong S.</searchLink><relatesTo>2</relatesTo><br /><searchLink fieldCode="AR" term="%22Malak%2C+Malak+F%2E%22">Malak, Malak F.</searchLink><relatesTo>2</relatesTo> – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22Journal+of+Engineering+for+Gas+Turbines+%26+Power%22">Journal of Engineering for Gas Turbines & Power</searchLink>. Sep2017, Vol. 139 Issue 9, p1-10. 10p. – Name: Abstract Label: Abstract Group: Ab Data: Measurements are presented for a high-pressure transonic turbine stage operating at design-corrected conditions with forward and aft purge flow and blade film cooling in a short-duration blowdown facility. Four different film-cooling configurations are investigated: simple cylindrical-shaped holes, diffusing fan-shaped holes, an advanced-shaped hole, and uncooled blades. A rainbow turbine approach is used so each of the four blade types comprises a wedge of the overall bladed disk and is investigated simultaneously at identical speed and vane exit conditions. Double-sided Kapton heat-flux gauges are installed at midspan on all three film-cooled blade types, and single-sided Pyrex heat-flux gauges are installed on the uncooled blades. Kulite pressure transducers are installed at midspan on cooled blades with round and fan-shaped cooling holes. Experimental results are presented both as time-averaged values and as time-accurate ensemble-averages. In addition, the results of a steady Reynolds-averaged Navier-Stokes computational fluid dynamics (RANS CFD) computation are compared to the time-averaged data. The computational and experimental results show that the cooled blades reduce heat transfer into the blade significantly from the uncooled case, but the overall differences in heat transfer among the three cooling configurations are small. This challenges previous conclusions for simplified geometries that show shaped cooling holes outperforming cylindrical holes by a great margin. It suggests that the more complicated flow physics associated with an airfoil operating in an engine-representative environment reduces the effectiveness of the shaped cooling holes. Time-accurate comparisons provide some insight into the complicated interactions that are driving these flows and make it difficult to characterize cooling benefits. [ABSTRACT FROM AUTHOR] – Name: AbstractSuppliedCopyright Label: Group: Ab Data: <i>Copyright of Journal of Engineering for Gas Turbines & Power is the property of American Society of Mechanical Engineers 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: 10.1115/1.4036059 Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 10 StartPage: 1 Titles: – TitleFull: Unsteady Heat Transfer and Pressure Measurements on the Airfoils of a Rotating Transonic Turbine With Multiple Cooling Configurations. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Nickol, Jeremy B. – PersonEntity: Name: NameFull: Mathison, Randall M. – PersonEntity: Name: NameFull: Dunn, Michael G. – PersonEntity: Name: NameFull: Liu, Jong S. – PersonEntity: Name: NameFull: Malak, Malak F. IsPartOfRelationships: – BibEntity: Dates: – D: 01 M: 09 Text: Sep2017 Type: published Y: 2017 Identifiers: – Type: issn-print Value: 07424795 Numbering: – Type: volume Value: 139 – Type: issue Value: 9 Titles: – TitleFull: Journal of Engineering for Gas Turbines & Power Type: main |
| ResultId | 1 |
