Influence of coolant inlet angle on endwall leakage flow film cooling performance

被引：0
|
作者：
Tang, Runze [1 ]
Li, Haiwang [1 ,2 ,3 ]
Zhou, Zhiyu [1 ]
Xie, Gang [2 ,4 ]
机构：
[1] Research Institute of Aero-Engine, Beihang University, Beijing,100191, China
[2] National Key Laboratory of Science and Technology on Aero-Engnie Aero-thermodynamics, Beihang University, Beijing,100191, China
[3] Tianmushan Laboratory, Zhejiang Provincial Laboratory for Aviation, Hangzhou,311121, China
[4] Flying College, Beihang University, Beijing,100191, China
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 08期
关键词：
Film cooling - Gas turbines - Reynolds equation - Shear flow - Shear stress - Turbine components - Turbomachine blades;
D O I：
10.13224/j.cnki.jasp.20230762
中图分类号：
学科分类号：
摘要：
By using an integrated model with disc cavity and turbine blade，the endwall film cooling effectiveness was investigated numerically by using the shear stress transfer (SST) model to solve the Reynolds-averaged Naiver-Stokes (RANS) equation. The rotational Reynolds number at the outlet of the disc cavity was 1.5×105. Carbon dioxide was chosen as the coolant to maintain the coolant-to-mainstream density ratio. The diffusion process of coolant was characterized by solving the turbulent transport equation. The effect of coolant inlet angle (−45°，0°，+45°) on the endwall film cooling effectiveness was investigated. It was found that the inlet angle of coolant had a significant impact on the endwall film cooling effectiveness， and the −45° inlet angle can significantly improve the endwall film cooling effectiveness at various coolant-to-mainstream mass flow rates. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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