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Michael van de Noort and Peter T. Ireland
Double-Wall Effusion Cooling schemes present an opportunity for aeroengine designers to achieve high overall cooling effectiveness and convective cooling efficiency in High-Pressure Turbine blades with reduced coolant usage compared to conventional cooli...
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Kefu Wang, Yiqun Ao, Kai Zhao, Tao Zhou and Feng Li
Shaped cooling holes have received considerable attention in recent years due to their potential to improve heat transfer while minimizing pressure drop. In this study, the effects of lobe-shaped cooling holes on film cooling performance and turbulent fl...
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Ashutosh Kumar Singh, Sourabh Kumar and Kuldeep Singh
The recent advancement of cooling methodologies for critical components such as turbine blades, combustor liners, and afterburner liners has led to the development of a combination of impingement and film cooling. The present study proposes an efficient ...
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Giovanna Barigozzi, Hamed Abdeh, Samaneh Rouina and Nicoletta Franchina
Design of cooling systems for rotor platforms is critical due to the complex flow field and heat transfer phenomena related to the secondary flow structures originating at the blade leading edge. Horseshoe vortex and passage vortex are the fluid-dynamic ...
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Dongjie Yan, Hongmei Jiang, Jieling Li, Wenbo Xie, Zhaoguang Wang, Shaopeng Lu and Qiang Zhang
In high-pressure turbines, there is a large difference in temperature between the mainstream and the turbine blade surface. Most of the turbine blade tip heat transfer studies were conducted under the assumption that the Over-Tip-Leakage (OTL) flow field...
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Xiaojun Wu, Xin Du and Chunhua Wang
Film cooling effectiveness can be improved significantly by embedding a round hole in trenches or craters. In this study, film cooling performances of a transverse trench, W-shaped trench and elliptic trench were compared and analyzed in detail. The CFD ...
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Xuan-Truong Le, Duc-Anh Nguyen, Cong-Truong Dinh and Quang-Hai Nguyen
Film cooling is commonly utilized in turbine blades to decrease the temperature of the air stream from the combustion chamber that contacts directly with the blades. The shape of a cylindrical hole (CH) with the geometrical variations at inlet and outlet...
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Matthew Courtis, Alexander Murray, Ben Coulton, Peter Ireland and Ignacio Mayo
To meet the challenges of increased thermal loads and performance demands on aero-engine turbine blades, more advanced cooling techniques are required. This study used a modification of the well-known Goldstein equation to predict film effectiveness for ...
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Augustin Wambersie, Holt Wong, Peter Ireland and Ignacio Mayo
Panels were tested at different locations around the turbine blade, on both suction and pressure surfaces. Three different surface porosities were also tested. Results demonstrated that the approach can be very successful with high levels of film cooling...
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Chenwei Zhao, Zecan Tu and Junkui Mao
The film-cooling performance of a 2.5D braided ceramic matrix composite (CMC) plate with preformed holes was numerically studied. Four numerical models containing braided structures were established: one model with film-cooling holes preformed through fi...
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