Conjugate Heat Transfer Investigation on Swirl-Film Cooling at the Leading Edge of a Gas Turbine Vane

Entropy

Wei Jiang¹  Jiayao Zou¹  Ziyue Mei¹  Danmei Xie¹  Haifen Du¹ 

[1] Key Laboratory of Hydraulic Machinery Transients (MOE), School of Power and Mechanical Engineering, Wuhan University, Wuhan 430072, China;

关键词: film cooling;    swirl cooling;    overall effectiveness;    heat transfer;    pressure loss;   

DOI  :  10.3390/e21101007

来源: DOAJ

【 摘 要 】

Numerical calculation of conjugate heat transfer was carried out to study the effect of combined film and swirl cooling at the leading edge of a gas turbine vane with a cooling chamber inside. Two cooling chambers (C₁ and C₂ cases) were specially designed to generate swirl in the chamber, which could enhance overall cooling effectiveness at the leading edge. A simple cooling chamber (C₀ case) was designed as a baseline. The effects of different cooling chambers were studied. Compared with the C₀ case, the cooling chamber in the C₁ case consists of a front cavity and a back cavity and two cavities are connected by a passage on the pressure side to improve the overall cooling effectiveness of the vane. The area-averaged overall cooling effectiveness of the leading edge ( $\overline{\overline{\varphi }}$ ) was improved by approximately 57%. Based on the C₁ case, the passage along the vane was divided into nine segments in the C₂ case to enhance the cooling effectiveness at the leading edge, and $\overline{\overline{\varphi }}$ was enhanced by 75% compared with that in the C₀ case. Additionally, the cooling efficiency on the pressure side was improved significantly by using swirl-cooling chambers. Pressure loss in the C₂ and C₁ cases was larger than that in the C₀ case.

【 授权许可】

Unknown