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Sanjay Nambiar, Anan Ashrabi Ananno, Herman Titus, Anton Wiberg and Mehdi Tarkian
In the quest to enhance the efficiency of gas turbines, there is a growing demand for innovative solutions to optimize high-pressure turbine blade cooling. However, the traditional methods for achieving this optimization are known for their complexity an...
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Kirttayoth Yeranee, Yu Rao, Chao Xu, Yueliang Zhang and Xiyuan Su
Additive manufacturing allows the fabrication of relatively complex cooling structures, such as triply periodic minimal surface (TPMS), which offers high heat transfer per unit volume. This study shows the turbulent flow heat transfer and thermal stress ...
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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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Hamed Abdeh, Giovanna Barigozzi and Nicoletta Franchina
Off-design condition of a rotor blade cascade with and without platform cooling was experimentally investigated. The ability of the gas turbine to operate down to 50% to 20% of its nominal intake air flow rate has an important consequence in the change i...
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Zhe Zhang, Zeyu Wu, Xiang Luo and Weitong Liu
The traditional blade cooling method can no longer meet the requirements of high cooling efficiency in modern engines. In order to solve this cooling problem, this paper proposes cooling turbine guide blades based on liquid metal. The feasibility was pre...
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Yue-Fang Hsiao and Yui-Chuin Shiah
The modeling of the turbine blades in aero-parts presents difficulties in conventional domain solution techniques, especially when internal cooling air passages and a thermal barrier coating (TBC) are applied. This paper presents a very efficient 3D mode...
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Bin Qu, Zilong Chen, Dengke He, Fei Zeng, Youfu Song, Yuqing Ouyang and Lei Luo
Today, impingement cooling structures with dimples can effectively ease the burden of turbine blades. This paper investigates the effect of dimple diameter and depth on the heat transfer of the target surface on a laminar-cooled turbine blade with a cros...
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Artur Kulaszka, Józef Blachnio and Henryk Borowczyk
The reliability and operational safety of an aircraft engine gas turbine are extremely important in terms of its operation. In the course of operation, these turbines undergo complex thermal, mechanical, aerodynamic, and chemical exhaust gas loads. Due t...
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Lei Xi, Jianmin Gao, Liang Xu, Zhen Zhao, Zhengheng Yang and Yunlong Li
In this study, different layout schemes for an X-shaped truss array channel are designed to explore the application of an X-shaped truss array structure in the mid-chord region of turbine blades. The flow and heat transfer performance of X-shaped truss a...
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Lei Xi, Jianmin Gao, Liang Xu, Zhen Zhao, Qicheng Ruan and Yunlong Li
In this study, numerical simulations were carried out to investigate the flow and heat transfer characteristics of jet array impingement cooling in the quasi-leading-edge channel of gas turbine blades. The influence laws of Reynolds number (Re, 10,000 to...
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