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Russian Aeronautics

, Volume 61, Issue 1, pp 49–55 | Cite as

The 3D Computational Investigation of Film Cooling Effectiveness for Turbine Nozzle Vanes with “Meridian Constriction” and Shaped Film-Cooling Holes

  • Yu. G. Gorelov
  • K. V. Tyul’kov
Aircraft and Rocket Engine Design and Development
  • 6 Downloads

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.

Keywords

rocket engine nozzle chemical kinetics mathematical modeling eigenvalue Jacobian matrix 

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References

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Copyright information

© Allerton Press, Inc. 2018

Authors and Affiliations

  1. 1.Salyut Gas Turbine Engineering Research and Production CentreMoscowRussia

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