Numerical Investigation on Aerodynamic Performances of the Single-Stage Transonic Turbine With Various Coolant Ejection Positions and Coolant Mass Flow Rates
The effects of film cooling holes on the suction surface and the coolant mass flow were studied in this research, which focused on load distribution and flow characteristics such as shock migration. A high and low degree of reaction scheme (degree of reaction = 0.3, 0.53) is selected to numerically...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Frontiers Media S.A.
2022-08-01
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| Series: | Frontiers in Energy Research |
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| Online Access: | https://www.frontiersin.org/articles/10.3389/fenrg.2022.948134/full |
| _version_ | 1811315649365934080 |
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| author | Jinming Zhang Xun Zhou Wei Du Senpei Xu |
| author_facet | Jinming Zhang Xun Zhou Wei Du Senpei Xu |
| author_sort | Jinming Zhang |
| collection | DOAJ |
| description | The effects of film cooling holes on the suction surface and the coolant mass flow were studied in this research, which focused on load distribution and flow characteristics such as shock migration. A high and low degree of reaction scheme (degree of reaction = 0.3, 0.53) is selected to numerically investigate the aerodynamic performance with consideration of air film cooling. The results show that the above factors have different influences on the intensity and the trailing edge shock direction. The reflected shock weakens and then recovers when the coolant ejection position approaches and departs from the reflection point. Altering the coolant ejection position or coolant mass flow rate mainly affects the load at the front and middle of the blade and has some effects on the pressure rise at the trailing edge as well. There is an optimal position (x/Cax = 0.6) and optimal coolant volume (10% mainstream mass flow rate) for flattening the pressure rise and weakening shocks, thereby reducing losses. |
| first_indexed | 2024-04-13T11:34:26Z |
| format | Article |
| id | doaj.art-cf810b1ca36f451fa8a0857d0e328b2e |
| institution | Directory Open Access Journal |
| issn | 2296-598X |
| language | English |
| last_indexed | 2024-04-13T11:34:26Z |
| publishDate | 2022-08-01 |
| publisher | Frontiers Media S.A. |
| record_format | Article |
| series | Frontiers in Energy Research |
| spelling | doaj.art-cf810b1ca36f451fa8a0857d0e328b2e2022-12-22T02:48:28ZengFrontiers Media S.A.Frontiers in Energy Research2296-598X2022-08-011010.3389/fenrg.2022.948134948134Numerical Investigation on Aerodynamic Performances of the Single-Stage Transonic Turbine With Various Coolant Ejection Positions and Coolant Mass Flow RatesJinming ZhangXun ZhouWei DuSenpei XuThe effects of film cooling holes on the suction surface and the coolant mass flow were studied in this research, which focused on load distribution and flow characteristics such as shock migration. A high and low degree of reaction scheme (degree of reaction = 0.3, 0.53) is selected to numerically investigate the aerodynamic performance with consideration of air film cooling. The results show that the above factors have different influences on the intensity and the trailing edge shock direction. The reflected shock weakens and then recovers when the coolant ejection position approaches and departs from the reflection point. Altering the coolant ejection position or coolant mass flow rate mainly affects the load at the front and middle of the blade and has some effects on the pressure rise at the trailing edge as well. There is an optimal position (x/Cax = 0.6) and optimal coolant volume (10% mainstream mass flow rate) for flattening the pressure rise and weakening shocks, thereby reducing losses.https://www.frontiersin.org/articles/10.3389/fenrg.2022.948134/fulltransonic turbinecoolant mass flow ratecoolant ejection positiontrailing edge shockaerodynamic performance |
| spellingShingle | Jinming Zhang Xun Zhou Wei Du Senpei Xu Numerical Investigation on Aerodynamic Performances of the Single-Stage Transonic Turbine With Various Coolant Ejection Positions and Coolant Mass Flow Rates Frontiers in Energy Research transonic turbine coolant mass flow rate coolant ejection position trailing edge shock aerodynamic performance |
| title | Numerical Investigation on Aerodynamic Performances of the Single-Stage Transonic Turbine With Various Coolant Ejection Positions and Coolant Mass Flow Rates |
| title_full | Numerical Investigation on Aerodynamic Performances of the Single-Stage Transonic Turbine With Various Coolant Ejection Positions and Coolant Mass Flow Rates |
| title_fullStr | Numerical Investigation on Aerodynamic Performances of the Single-Stage Transonic Turbine With Various Coolant Ejection Positions and Coolant Mass Flow Rates |
| title_full_unstemmed | Numerical Investigation on Aerodynamic Performances of the Single-Stage Transonic Turbine With Various Coolant Ejection Positions and Coolant Mass Flow Rates |
| title_short | Numerical Investigation on Aerodynamic Performances of the Single-Stage Transonic Turbine With Various Coolant Ejection Positions and Coolant Mass Flow Rates |
| title_sort | numerical investigation on aerodynamic performances of the single stage transonic turbine with various coolant ejection positions and coolant mass flow rates |
| topic | transonic turbine coolant mass flow rate coolant ejection position trailing edge shock aerodynamic performance |
| url | https://www.frontiersin.org/articles/10.3389/fenrg.2022.948134/full |
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