Email this article The 3D Computational Investigation of Film Cooling Effectiveness for Turbine Nozzle Vanes with “Meridian Constriction” and Shaped Film-Cooling Holes
- Authors: Gorelov Y.G.1, Tyul’kov K.V.1
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Affiliations:
- Salyut Gas Turbine Engineering Research and Production Centre
- Issue: Vol 61, No 1 (2018)
- Pages: 49-55
- Section: Aircraft and Rocket Engine Design and Development
- URL: https://journal-vniispk.ru/1068-7998/article/view/230398
- DOI: https://doi.org/10.3103/S1068799818010087
- ID: 230398
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Abstract
Active influence dimension of film cooling along the blade profile is investigated with using the Spalart–Allmaras turbulence model. The cooling effectiveness of vane platforms and vane fillets is studied with the use of perforation holes on the leading edge.
About the authors
Yu. G. Gorelov
Salyut Gas Turbine Engineering Research and Production Centre
Author for correspondence.
Email: Yury.Dina@gmail.com
Russian Federation, prospect Budennogo 16, Moscow, 105118
K. V. Tyul’kov
Salyut Gas Turbine Engineering Research and Production Centre
Email: Yury.Dina@gmail.com
Russian Federation, prospect Budennogo 16, Moscow, 105118
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