Investigation of Leading Edge Film Cooling Jets in a Cross Flow
The thermal effect of the turbine blade film cooling and the penetration area of jets issuing at an angle into cross mainstream flow have been investigated numerically and experimentally. Experimental and numerical simulations have been introduced to simulate a discrete circle hole film cooling flo...
| Main Authors: | , , |
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| Format: | Article |
| Language: | Arabic |
| Published: |
Mustansiriyah University/College of Engineering
2011-06-01
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| Series: | Journal of Engineering and Sustainable Development |
| Subjects: | |
| Online Access: | https://jeasd.uomustansiriyah.edu.iq/index.php/jeasd/article/view/1390 |
| _version_ | 1811232954179911680 |
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| author | A H. Yousif K . J. M. Al-Khishali Muna S Kassim |
| author_facet | A H. Yousif K . J. M. Al-Khishali Muna S Kassim |
| author_sort | A H. Yousif |
| collection | DOAJ |
| description |
The thermal effect of the turbine blade film cooling and the penetration area of jets issuing at an angle into cross mainstream flow have been investigated numerically and experimentally. Experimental and numerical simulations have been introduced to simulate a discrete circle hole film cooling flow over a symmetrical airfoil representing turbine guide vanes surface. Several cases have been studied in the experimental work by using three-velocity ratio (0.5, 0.9, 1.3), and three different jet issuing angles, longitudinal injection angle (37.50 and 900) both with lateral injection angle (stagger angle = 00 and 450). Airfoil angle of attack has been changed during the experimental program throughout (00, 50, 100, and 150). Experimental investigations gave qualitative information about the penetration area and flow structure of the mixing flow at all cases and the results were used to verify the computation method and to select the best velocity ratios for the flow penetration, flow structure, and the thermal effect of cool jets.
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| first_indexed | 2024-04-12T11:11:56Z |
| format | Article |
| id | doaj.art-179807d8bf2a4d488dddd385fc0257fc |
| institution | Directory Open Access Journal |
| issn | 2520-0917 2520-0925 |
| language | Arabic |
| last_indexed | 2024-04-12T11:11:56Z |
| publishDate | 2011-06-01 |
| publisher | Mustansiriyah University/College of Engineering |
| record_format | Article |
| series | Journal of Engineering and Sustainable Development |
| spelling | doaj.art-179807d8bf2a4d488dddd385fc0257fc2022-12-22T03:35:35ZaraMustansiriyah University/College of EngineeringJournal of Engineering and Sustainable Development2520-09172520-09252011-06-01152Investigation of Leading Edge Film Cooling Jets in a Cross FlowA H. Yousif0K . J. M. Al-Khishali1Muna S Kassim2University of Technology, Baghdad, IraqUniversity of Technology, Baghdad, IraqMechanical Engineering Department, Al-Mustansiriyah University , Baghdad, Iraq The thermal effect of the turbine blade film cooling and the penetration area of jets issuing at an angle into cross mainstream flow have been investigated numerically and experimentally. Experimental and numerical simulations have been introduced to simulate a discrete circle hole film cooling flow over a symmetrical airfoil representing turbine guide vanes surface. Several cases have been studied in the experimental work by using three-velocity ratio (0.5, 0.9, 1.3), and three different jet issuing angles, longitudinal injection angle (37.50 and 900) both with lateral injection angle (stagger angle = 00 and 450). Airfoil angle of attack has been changed during the experimental program throughout (00, 50, 100, and 150). Experimental investigations gave qualitative information about the penetration area and flow structure of the mixing flow at all cases and the results were used to verify the computation method and to select the best velocity ratios for the flow penetration, flow structure, and the thermal effect of cool jets. https://jeasd.uomustansiriyah.edu.iq/index.php/jeasd/article/view/1390turbine bladefilm coolingpenetration areajet anglemixing flow |
| spellingShingle | A H. Yousif K . J. M. Al-Khishali Muna S Kassim Investigation of Leading Edge Film Cooling Jets in a Cross Flow Journal of Engineering and Sustainable Development turbine blade film cooling penetration area jet angle mixing flow |
| title | Investigation of Leading Edge Film Cooling Jets in a Cross Flow |
| title_full | Investigation of Leading Edge Film Cooling Jets in a Cross Flow |
| title_fullStr | Investigation of Leading Edge Film Cooling Jets in a Cross Flow |
| title_full_unstemmed | Investigation of Leading Edge Film Cooling Jets in a Cross Flow |
| title_short | Investigation of Leading Edge Film Cooling Jets in a Cross Flow |
| title_sort | investigation of leading edge film cooling jets in a cross flow |
| topic | turbine blade film cooling penetration area jet angle mixing flow |
| url | https://jeasd.uomustansiriyah.edu.iq/index.php/jeasd/article/view/1390 |
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