Investigation on the effect of hole diameter and wall thickness on the overall cooling effectiveness of turbine vane leading edge-Reference-Cited by-同舟云学术

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Investigation on the effect of hole diameter and wall thickness on the overall cooling effectiveness of turbine vane leading edge

Published:2024-04 Issue: Volume:243 Page:122662
ISSN:1359-4311
Container-title:Applied Thermal Engineering
language:en
Short-container-title:Applied Thermal Engineering

Author:

Wang Rui,Ye Lin,Zhang Lingjun,Liu Cunliang,Cao Feifei,Hui Zhonghao

Funder

National Natural Science Foundation of China

National Major Science and Technology Projects of China

Joint Fund for Aerospace Advanced Manufacturing Technology Research

Publisher

Elsevier BV

Reference32 articles.

1. Gas Turbine Heat Transfer and Cooling Technology;Han,2012

2. C.L. Liu, H.R. Zhu, Z.W. Zhang et al., Experimental investigation on the leading edge film cooling of cylindrical and laid-back holes with different hole pitches, Int. J. Heat Mass Transfer 55(23-24), 6832-6845.

3. Investigations on the film cooling of counter-inclined film-hole row structures for turbine vane leading edge;Liu;Int. J. Turbo Jet Engines,2016

4. Experimental investigation on the adiabatic film effectiveness for counter-inclined simple and laid-back film-holes of leading edge;Ye;J. Therm. Sci.,2020

5. Experimental study on heat transfer of leading edge film-cooling with counter-inclined cylindrical and laid-back holes;Ye;ASME Trans.-J. Heat Transfer,2020

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