Vortical structures and heat transfer augmentation of a cooling channel in a gas turbine blade with various arrangements of tip bleed holes-Reference-Cited by-同舟云学术

Vortical structures and heat transfer augmentation of a cooling channel in a gas turbine blade with various arrangements of tip bleed holes

Published:2020-09-10 Issue:1 Volume:79 Page:40-67
ISSN:1040-7782
Container-title:Numerical Heat Transfer, Part A: Applications
language:en
Short-container-title:Numerical Heat Transfer, Part A: Applications

Author:

Zhao Zhiqi¹²,Luo Lei¹,Qiu Dandan¹²,Wang Songtao¹,Wang Zhongqi¹,Sundén Bengt²

Affiliation:

1. School of Energy Science and Engineering, Harbin Institute of Technology, Heilongjiang, P.R. China;

2. Department of Energy Sciences, Lund University, Skåne, Sweden

Funder

Harbin Institute of Technology

National Natural Science Foundation of China

China Postdoctoral Science Foundation

Publisher

Informa UK Limited

Subject

Condensed Matter Physics,Numerical Analysis

Link

https://www.tandfonline.com/doi/pdf/10.1080/10407782.2020.1814591

Reference36 articles.

1. Mitsubishi. “Mitsubishi’s R1 turbine blade for the W501FD2 on track to run 72,000 hours” [Online]. Available: http://www.ccj-online.com/mitsubishis-r1-turbine-blade-for-the-w501fd2-on-track-to-run-72,000-hours/. Accessed: Jun. 16, 2020.

2. An Experimental Investigation of Adiabatic Film Cooling Effectiveness and Heat Transfer Coefficient on a Transonic Squealer Tip

3. A tip region film cooling study of the fan-shaped hole using PSP

4. Investigations of film-cooling effectiveness on the squealer tip with various film-hole configurations in a linear cascade

5. Experimental Investigation of Rotor Tip Film Cooling at an Axial Turbine with Swirling Inflow Using Pressure Sensitive Paint

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