Study of film cooling on a turbine guide vane pressure side with a serrated trench-Reference-Cited by-同舟云学术

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Study of film cooling on a turbine guide vane pressure side with a serrated trench

Published:2024-01-02 Issue: Volume: Page:1-20
ISSN:1040-7782
Container-title:Numerical Heat Transfer, Part A: Applications
language:en
Short-container-title:Numerical Heat Transfer, Part A: Applications

Author:

Huang Kenan¹,Zhang Jingzhou²,Li Guoneng¹,Zhu Yiyuan¹,Zhou Junshu³,Yan Jun³

Affiliation:

1. Department of Energy and Environment System Engineering, Zhejiang University of Science and Technology, Hangzhou, P.R. China

2. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, P.R. China

3. Ningbo Baogong Electrical Appliance Co., Ltd., Cixi, P.R. China

Funder

Zhejiang University of Science and Technology

Key R&D Programme of Cixi City

Publisher

Informa UK Limited

Link

https://www.tandfonline.com/doi/pdf/10.1080/10407782.2023.2299296

Reference37 articles.

1. Effects of supersonic film cooling on shock wave/boundary layer interaction in a scramjet combustor

2. Film cooling performance of multi-row casing injection in a turbine-rotor cascade under blade passing

3. Numerical investigation of sweeping jet film cooling on a flat plate

4. Application of double-wall cooling structure in the integrated strut flame stabilizer

5. D. K. Walters and J. H. Leylek, “A detailed analysis of film–cooling physics: part I – streamwise injection with cylindrical holes,” presented at the ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition, Orlando, FL, USA, Jun. 2–5, 1997.

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