Effect of Cutbacks on Tip Leakage Flow and Film-Cooling Effectiveness of a Turbine Blade Tip under Relative Moving Condition-Reference-Cited by-同舟云学术

Effect of Cutbacks on Tip Leakage Flow and Film-Cooling Effectiveness of a Turbine Blade Tip under Relative Moving Condition

Published:2021 Issue:6 Volume:64 Page:293-303
ISSN:0549-3811
Container-title:TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
language:en
Short-container-title:Trans. Japan Soc. Aero. S Sci.

Author:

CHENG Fengna¹,ZHANG Jingzhou²,ZHANG Jingyang³,ZHANG Yuyan¹

Affiliation:

1. College of Mechanical and Electronic Engineering, Nanjing Forestry University

2. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

3. College of Astronautics, Nanjing University of Aeronautics and Astronautics

Publisher

Japan Society for Aeronautical and Space Sciences

Subject

Space and Planetary Science,Aerospace Engineering

Link

https://www.jstage.jst.go.jp/article/tjsass/64/6/64_T-19-90/_pdf

Reference29 articles.

1. 1) Azad, G. S., et al.: Heat Transfer and Flow on the Squealer Tip of a Gas Turbine Blade, J. Turbomachinery, 122 (2000), pp. 725–732.

2. 2) Azad, G. S., Han, J. C., Bunker, R. S., and Lee, C. P.: Effect of Squealer Geometry Arrangement on a Gas Turbine Blade Tip Heat Transfer, J. Heat Transfer, 124 (2002), pp. 452–459.

3. 3) Kwak, J. S. and Han, J. C.: Heat Transfer Coefficients on the Squealer Tip and Near Squealer Tip Regions of a Gas Turbine Blade, J. Heat Transfer, 125 (2003), pp. 669–677.

4. 4) Kwak, J. S., et al.: Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade with Single or Double Squealer, J. Turbomachinery, 125 (2003), pp. 778–787.

5. 5) Nasir, H., et al.: Effect of Tip Gap and Squealer Geometry on Detailed Heat Transfer Measurements over a High Pressure Turbine Rotor Blade Tip, J. Turbomachinery, 126 (2004), pp. 221–228.