Email this article 3D Investigation of Film Cooling Effectiveness for Nozzle Vane Platform of High Pressure Turbine with “Meridian Constriction” and Laidback Fan-Shaped Film-Cooling Holes
- Authors: Gorelov Y.G.1
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Affiliations:
- Salyut Gas Turbine Engineering Research and Production Center
- Issue: Vol 62, No 3 (2019)
- Pages: 476-483
- Section: Aircraft and Rocket Engine Theory
- URL: https://journal-vniispk.ru/1068-7998/article/view/231067
- DOI: https://doi.org/10.3103/S1068799819030164
- ID: 231067
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Abstract
As the result of ANSYS CFX calculation, a conclusion was drawn about the greater cooling effectiveness of vane platform with laidback fan-shaped perforation holes as compared with cooling effectiveness of vane platform with cylindrical holes.
About the authors
Yu. G. Gorelov
Salyut Gas Turbine Engineering Research and Production Center
Author for correspondence.
Email: Yury.Dina@gmail.com
Russian Federation, pr. Budennogo 16, Moscow, 105118
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