Simulation of Supersonic Flow Through the Tip-Section Turbine Blade Cascade with a Strong Shock-Wave/Boundary Layer Interaction
The result's identifiers
Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F18%3A00495984" target="_blank" >RIV/61388998:_____/18:00495984 - isvavai.cz</a>
Result on the web
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DOI - Digital Object Identifier
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Alternative languages
Result language
angličtina
Original language name
Simulation of Supersonic Flow Through the Tip-Section Turbine Blade Cascade with a Strong Shock-Wave/Boundary Layer Interaction
Original language description
The contribution deals with the numerical simulation of 2D compressible flow though the tip-section turbine blade cascade with the supersonic inlet boundary conditions. The simulation was carried out by the in-house computational programme using the explicit algebraic Reynolds stress model completed by the bypass transition model with the algebraic equation for the intermittency coefficient. Predictions carried out for the nominal conditions were focused on the adequate simulation of the shock-wave/boundary-layer interaction. The outlet boundary condition given the outlet isentropic Mach number was optimised according to angle of the exit shock wave and the blade chord. Numerical results were compared with experimental data.
Czech name
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Czech description
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Classification
Type
O - Miscellaneous
CEP classification
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OECD FORD branch
20302 - Applied mechanics
Result continuities
Project
<a href="/en/project/TH02020057" target="_blank" >TH02020057: Turbine profile cascades for supersonic flow fields</a><br>
Continuities
I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace
Others
Publication year
2018
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů