Film cooling of showerhead holes from the twisted leading edge of a gas turbine blade: Complex mainstream characteristics and reasonable angle arrangement-Reference-Cited by-同舟云学术

Film cooling of showerhead holes from the twisted leading edge of a gas turbine blade: Complex mainstream characteristics and reasonable angle arrangement

Published:2021-12 Issue: Volume:119 Page:107208
ISSN:1270-9638
Container-title:Aerospace Science and Technology
language:en
Short-container-title:Aerospace Science and Technology

Author:

Zhao Y.C.,Gao H.S.,Wen Z.X.,Yang Y.Q.,Cheng H.,Li Q.,Yue Z.F.

Funder

Natural Science Foundation of Shaanxi Province

National Major Science and Technology Projects of China

National Natural Science Foundation of China

Publisher

Elsevier BV

Subject

Aerospace Engineering

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4. Precise infrared thermometry with considering background radiation for gas turbine air cooling application;Shin;Int. J. Therm. Sci.,2020

5. Effect of turbine inlet temperature on rotor blade tip leakage flow and heat transfer;Kim;Int. J. Numer. Methods Heat Fluid Flow,2009

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