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Effects of a Groove Patterned Cooling Tube on the Film Cooling Performance of a Gas Turbine Blade

[+] Author Affiliations
Yeon-Ho Lee, Youn-Jea Kim

Sungkyunkwan University, Suwon, Korea

Paper No. FEDSM2017-69263, pp. V01AT02A010; 7 pages
doi:10.1115/FEDSM2017-69263
From:
  • ASME 2017 Fluids Engineering Division Summer Meeting
  • Volume 1A, Symposia: Keynotes; Advances in Numerical Modeling for Turbomachinery Flow Optimization; Fluid Machinery; Industrial and Environmental Applications of Fluid Mechanics; Pumping Machinery
  • Waikoloa, Hawaii, USA, July 30–August 3, 2017
  • Conference Sponsors: Fluids Engineering Division
  • ISBN: 978-0-7918-5804-2
  • Copyright © 2017 by ASME

abstract

A high working fluid temperature in a gas turbine is required to improve its efficiency. However, high temperatures also reduce turbine blade durability. Film-cooling is one blade cooling method to control gas turbine blade temperature. In this study, film cooling performance was numerically investigated with various configurations of a groove patterned cooling tube. The CO2 blowing ratio of the cooling fluid was varied from 0.6 to 1.4 with 0.2 intervals. The numerical analysis was conducted using the ANSYS CFX ver. 16.1 commercial code. The film cooling efficiency and pressure distribution were graphically depicted and analyzed to derive the groove configuration with the highest film cooling efficiency. In particular, the flow field on the turbine blade with the circular groove configuration showed more uniform distribution compared to the reference model.

Copyright © 2017 by ASME

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