Direct numerical simulation of the 7-7-7 film cooling at a range of compound angles-Reference-Cited by-同舟云学术

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Direct numerical simulation of the 7-7-7 film cooling at a range of compound angles

Published:2024-10 Issue: Volume:231 Page:125816
ISSN:0017-9310
Container-title:International Journal of Heat and Mass Transfer
language:en
Short-container-title:International Journal of Heat and Mass Transfer

Author:

Bin Yuanwei,Yang Xiang I.A.^ORCID

Funder

National Natural Science Foundation of China

Publisher

Elsevier BV

Reference80 articles.

1. A review of shaped hole turbine film-cooling technology;Bunker;J. Heat Transfer,2005

2. A converging slot-hole film-cooling geometry—Part 2: transonic nozzle guide vane heat transfer and loss;Sargison;J. Turbomach.,2002

3. Film cooling and aerodynamic performances of a turbine nozzle guide vane with trenched cooling holes;He;Appl. Therm. Eng.,2019

4. Recent development in turbine blade film cooling;Han;Int. J. Rotating Mach.,2001

5. Film cooling on a gas turbine blade pressure side or suction side with axial shaped holes;Gao;Int. J. Heat Mass Transfer,2008

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