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Thermophysics and Aeromechanics

, Volume 23, Issue 5, pp 713–720 | Cite as

Application of local indentations for film cooling of gas turbine blade leading edge

  • V. Yu. PetelchytsEmail author
  • A. A. Khalatov
  • D. N. Pysmennyi
  • Yu. Ya. Dashevskyy
Article
  • 35 Downloads

Abstract

The paper presents results of computer simulation of the film cooling on the turbine blade leading edge model where the air coolant is supplied through radial holes and row of cylindrical inclined holes placed inside hemispherical dimples or trench. The blowing factor was varied from 0.5 to 2.0. The model size and key initial parameters for simulation were taken as for a real blade of a high-pressure high-performance gas turbine. Simulation was performed using commercial software code ANSYS CFX. The simulation results were compared with reference variant (no dimples or trench) both for the leading edge area and for the flat plate downstream of the leading edge.

Keywords

film cooling blowing parameter leading edge cooling system semi-spherical dimple trench 

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Copyright information

© Pleiades Publishing, Ltd. 2016

Authors and Affiliations

  • V. Yu. Petelchyts
    • 1
    Email author
  • A. A. Khalatov
    • 2
    • 3
  • D. N. Pysmennyi
    • 1
  • Yu. Ya. Dashevskyy
    • 1
  1. 1.Gas Turbine Research and Production Complex «Zorya»-«Mashproekt»MykolaivUkraine
  2. 2.Institute of Engineering ThermophysicsNational Academy of Sciences of UkraineKyivUkraine
  3. 3.National Technical University of Ukraine «I. Sikorskiy Kyiv Polytechnic Institute»KyivUkraine

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