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Impact of Flowfield Unsteadiness on Film Cooling of a High Pressure Turbine Blade

[+] Author Affiliations
Paul Vitt, Chad Iverson

QuEST Global Services – North America, LLC, Cincinnati, OH

Malak F. Malak, Jong S. Liu

Honeywell Aerospace, Phoenix, AZ

Paper No. GT2010-22773, pp. 1369-1380; 12 pages
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME


A key factor in gas turbine blade operation is flow unsteadiness generated by the vane as the blade passes behind it, and the impact of this variation on the aerodynamic performance of the blade has been well studied. The objective of the current study was to examine the impact of this flow unsteadiness on film cooling effectiveness on the airfoil. A Honeywell research single-stage high-pressure cooled turbine was selected as an engine-representative geometry. Both steady-state and transient stage calculations were completed using fully cooled vane and blade models. One area of interest was the impact of the vane passing on the local film hole flow rates, so the blade model included the leading edge impingement chamber as well as detailed film cooling holes in the analysis. Results from the calculations showed a dramatic change in the predicted film cooling on the blade surface in two primary areas. At the leading edge, the steady-state model predicted low local film effectiveness due to the stagnation line falling between showerhead film rows, whereas the time-averaged unsteady analysis showed an even distribution of film at the leading edge. On the pressure side, the steady model predicted effective film coverage downstream of the gill holes. In the unsteady analysis, the low momentum mixed gas and film stream along the forward portion of the pressure side was highly disturbed by the vane unsteadiness, and time-averaging the results indicated a significant reduction in overall film cooling effectiveness. The results show that considering the unsteady operating environment of the blade is very important during design and optimization of the blade thermal protection system.

Copyright © 2010 by ASME



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