电邮这篇文章 The 3D Computational Investigation of Film Cooling Effectiveness for Turbine Nozzle Vanes with “Meridian Constriction” and Shaped Film-Cooling Holes
- 作者: Gorelov Y.G.1, Tyul’kov K.V.1
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隶属关系:
- Salyut Gas Turbine Engineering Research and Production Centre
- 期: 卷 61, 编号 1 (2018)
- 页面: 49-55
- 栏目: Aircraft and Rocket Engine Design and Development
- URL: https://journals.rcsi.science/1068-7998/article/view/230398
- DOI: https://doi.org/10.3103/S1068799818010087
- ID: 230398
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详细
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.
作者简介
Yu. Gorelov
Salyut Gas Turbine Engineering Research and Production Centre
编辑信件的主要联系方式.
Email: Yury.Dina@gmail.com
俄罗斯联邦, prospect Budennogo 16, Moscow, 105118
K. Tyul’kov
Salyut Gas Turbine Engineering Research and Production Centre
Email: Yury.Dina@gmail.com
俄罗斯联邦, prospect Budennogo 16, Moscow, 105118
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