Enviar artigo por via de e-mail 3D Investigation of Film Cooling Effectiveness for Nozzle Vane Platform of High Pressure Turbine with “Meridian Constriction” and Laidback Fan-Shaped Film-Cooling Holes
- Autores: Gorelov Y.G.1
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Afiliações:
- Salyut Gas Turbine Engineering Research and Production Center
- Edição: Volume 62, Nº 3 (2019)
- Páginas: 476-483
- Seção: Aircraft and Rocket Engine Theory
- URL: https://journals.rcsi.science/1068-7998/article/view/231067
- DOI: https://doi.org/10.3103/S1068799819030164
- ID: 231067
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Resumo
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.
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Sobre autores
Yu. Gorelov
Salyut Gas Turbine Engineering Research and Production Center
Autor responsável pela correspondência
Email: Yury.Dina@gmail.com
Rússia, pr. Budennogo 16, Moscow, 105118
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