Numerical simulation of cooling effectiveness with injection of double-outlet hole

LI Guang-chao; ZHANG Wei; XIANG Song; WANG Cheng-jun; PENG Da-wei

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Numerical simulation of cooling effectiveness with injection of double-outlet hole

更新时间：2026-07-07

- Numerical simulation of cooling effectiveness with injection of double-outlet hole
- Vol. 25, Issue 6, (2010)
- 作者机构：
  
  沈阳航空工业学院动力与能源工程学院,沈阳,110136
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2010
- 稿件说明：
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LI Guang-chao, ZHANG Wei, XIANG Song, et al. Numerical simulation of cooling effectiveness with injection of double-outlet hole[J]. 2010, 25(6).
DOI：

LI Guang-chao, ZHANG Wei, XIANG Song, et al. Numerical simulation of cooling effectiveness with injection of double-outlet hole[J]. 2010, 25(6). DOI：

摘要

为了优化气膜冷却结构

通过数值模拟研究了一种新型气膜孔(由两个圆柱孔组成的双出口孔)的气膜冷却特性.利用Fluent软件对Navier-Stokes方程进行求解

湍流模型采用两方程Realizablek-ε模型和增强壁面函数处理.圆柱孔射流的冷却效率计算结果和实验数据吻合较好.双出口孔射流冷却效率计算结果表明

双出口孔射流有效地增加了冷气的径向覆盖范围

在吹风比为0.5时

次孔射流起到了减弱主孔出口对旋涡的作用;在吹风比为1.0和2.0时

次孔射流使主孔出口处的对旋涡消失.最高冷却效率对应的吹风比为1.0.双出口孔射流在提高冷却效率的同时

其加工难度较扩张形孔明显降低.

Abstract

In order to optimize the structure of the film cooling

the film cooling performance of a novel hole with double-outlet was investigated by numerical simulation.The Navier-Stokes equation was solved by Fluent.The realizable k-ε model and enhanced function were used.The numerical effectiveness of the cylindrical hole agrees well with the experimental data.The result of the double-outlet hole injection shows that the lateral spreading of the film is improved as compared to the injection of the cylindrical hole.At the blowing ratio of 0.5

the vortices at the trunk hole outlet are reduced by the injection of the branch hole.At the blowing ratio of 1.0 and 2.0

the vortices at the trunk hole outlet are eliminated by the injection of the branch hole.The optimal blowing ratio is found at blowing ratio of 1.0.The double-outlet hole improves the cooling effectiveness significantly while requiring for easily machinable round hole as compared to expanded hole.

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Related Author

LI Guang-chao

ZHANG Wei

WANG Cheng-jun

PENG Da-wei

WANG Jian-ming

XU Zhi-hui

LI Guang-chao

LING Xu

Related Institution

Liaoning Key Laboratory of Digital Technology Simulation and Test Technique, School of Aero Dynamics and Energy Engineering, Shenyang Aerospace University

Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University

National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics

Aircraft Design and Research Institute,Hongdu Aviation Industry Group

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