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The Effects of Injection Angle and Hole Exit Shape on Turbine Nozzle Pressure Side Film Cooling

[+] Author Affiliations
Luzeng J. Zhang, Ram Pudupatty

Solar Turbines Incorporated, San Diego

Paper No. 2000-GT-0247, pp. V003T01A053; 11 pages
  • ASME Turbo Expo 2000: Power for Land, Sea, and Air
  • Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Munich, Germany, May 8–11, 2000
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7856-9
  • Copyright © 2000 by ASME


Using the pressure sensitive paint (PSP) technique, film cooling effectiveness was measured on a turbine vane pressure surface, with a four-row showerhead cooling hole configuration and a single row of holes on the pressure side. Nitrogen gas was used to simulate film cooling flow providing an oxygen concentration map corresponding to an effectiveness map by the mass transfer analogy. Three showerhead coolant injection angles (45°, 90°, and 135°) were studied and two pressure side injection angles (20° and 40°) for cylindrical holes and a 40° angle for shaped hole were studied. In addition, studies were performed on three combinations of shower head and pressure side injections. Film effectiveness was measured for each of the cases at three blowing ratios. The pressure sensitive paint (PSP) was used to indicate oxygen concentration and was calibrated at various temperatures and pressures to obtain better accuracy before being applied to the airfoil surface. The results indicate that 45° spanwise angle injection provides best film coverage for the shower head injections. For pressure side injections, the 20° cylindrical hole injection results in the highest effectiveness values and the shaped hole improves film effectiveness immediately downstream from the injection point. The film effectiveness for three combined injections and the interaction between showerhead injection and the pressure side injection are also presented and discussed.

Copyright © 2000 by ASME



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