Email this article Verification of the Film Cooling Calculations for Nozzle Vane Leading Edges in ANSYS CFX
- Authors: Gorelov Y.G.1, Tyul’kov K.V.1, Anan’ev V.V.1, Byval’tsev P.M.2
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Affiliations:
- Salyut Gas Turbine Engineering Research and Production Center
- OOO Tesis
- Issue: Vol 62, No 1 (2019)
- Pages: 74-80
- Section: Aircraft and Rocket Engine Theory
- URL: https://journal-vniispk.ru/1068-7998/article/view/230836
- DOI: https://doi.org/10.3103/S1068799819010100
- ID: 230836
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Abstract
The verification results are cited of 3D computational investigation of effectiveness of the film cooling for the vane leading edge of the C3X engine high pressure turbine with application of SST and S—A turbulence models, and calculation results are presented for used 1D empirical dependences and 2D calculation with modeling coolant injection within the bounds of two-dimensional boundary layer. The most satisfactory matching of calculation data with experimental ones is demonstrated in case of using S—A turbulence model in 3D calculations.
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
K. V. Tyul’kov
Salyut Gas Turbine Engineering Research and Production Center
Email: Yury.Dina@gmail.com
Russian Federation, pr. Budennogo 16, Moscow, 105118
V. V. Anan’ev
Salyut Gas Turbine Engineering Research and Production Center
Email: Yury.Dina@gmail.com
Russian Federation, pr. Budennogo 16, Moscow, 105118
P. M. Byval’tsev
OOO Tesis
Email: Yury.Dina@gmail.com
Russian Federation, ul. Yunnatov 18, Moscow, 127083
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