The trailing edge of the high-pressure turbine blade presents significant challenges to cooling structure design. To achieve better cooling performance at turbine blade trailing edge, a novel ribbed cutback structure is proposed for trailing edge cooling, which has rib structures on the cutback surface for heat transfer enhancement. In this study, numerical simulations have been performed on the effects of V-shaped rib angle on the film cooling characteristics and flow physics. Three V-shaped rib angles of 30°, 45° and 60° are studied. The distributions of adiabatic cooling effectiveness and heat transfer coefficient are obtained under blowing ratios with the value of 0.5, 1.0 and 1.5 respectively. Due to the relatively small rib height, the effect of V-shaped ribs on the film cooling effectiveness is not notable. The disadvantage of V-shaped ribs mainly exhibits at the downstream area of cutback surface. With the increase of V-shaped rib angle, the film cooling effectiveness becomes lower, but the values are still above 0.9. The V-shaped ribs obviously enhance the heat transfer on trailing edge cutback surface. The area-averaged heat transfer coefficient of the V-rib case is higher than that of the smooth case by 26.3–41.2%. The 45° V-rib case has higher heat transfer intensity than the other two V-shaped rib cases under all the three blowing ratios. However, the heat transfer coefficient distribution of the 60° V-rib case is more uniform. The heat transfer intensity of the 30° V-rib case is higher in the downstream region than the other two cases, but lower in the upstream region in which the difference becomes smaller with the increase of blowing ratio. The 45° V-rib case and the 60° V-rib case both reach the maximum value of area-averaged heat transfer intensity under blowing ratio is 1.0. Under higher blowing ratio, the 30° V-rib case and the 45° V-rib case outperform 2.1% and 6.7% higher value relative to the 60° V-rib case respectively due to the smaller velocity gradient in the 60° V-rib case in the downstream.
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ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition
June 11–15, 2018
Oslo, Norway
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5108-1
PROCEEDINGS PAPER
Numerical Study on the Effects of V-Shaped Rib Angle on Film Cooling Performance for Turbine Blade Trailing Edge
Lin Ye,
Lin Ye
Northwestern Polytechnical University, Xi’an, China
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Cun-liang Liu,
Cun-liang Liu
Northwestern Polytechnical University, Xi’an, China
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Hai-yong Liu,
Hai-yong Liu
Northwestern Polytechnical University, Xi’an, China
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Qi-jiao He,
Qi-jiao He
Northwestern Polytechnical University, Xi’an, China
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Gang Xie
Gang Xie
Northwestern Polytechnical University, Xi’an, China
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Lin Ye
Northwestern Polytechnical University, Xi’an, China
Cun-liang Liu
Northwestern Polytechnical University, Xi’an, China
Hai-yong Liu
Northwestern Polytechnical University, Xi’an, China
Qi-jiao He
Northwestern Polytechnical University, Xi’an, China
Gang Xie
Northwestern Polytechnical University, Xi’an, China
Paper No:
GT2018-75114, V05AT12A002; 13 pages
Published Online:
August 30, 2018
Citation
Ye, L, Liu, C, Liu, H, He, Q, & Xie, G. "Numerical Study on the Effects of V-Shaped Rib Angle on Film Cooling Performance for Turbine Blade Trailing Edge." Proceedings of the ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. Volume 5A: Heat Transfer. Oslo, Norway. June 11–15, 2018. V05AT12A002. ASME. https://doi.org/10.1115/GT2018-75114
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