TY - GEN
T1 - 3D velocity and scalar field measurements of an airfoil trailing edge with slot film cooling
T2 - ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012
AU - Ling, Julia
AU - Yapa, Sayuri D.
AU - Benson, Michael J.
AU - Elkins, Christopher J.
AU - Eaton, John K.
PY - 2012
Y1 - 2012
N2 - Measurements of the 3D velocity and concentration fields were obtained using magnetic resonance imaging for a pressure side cutback film cooling experiment. The cutback geometry consisted of rectangular slots separated by straight lands; inside each of the slots was an airfoil-shaped blockage. The results from this trailing edge configuration, the "island airfoil," are compared to the results obtained with the "generic airfoil," a geometry with narrower slots, wider, tapered lands, and no block- Ages. The objective was to determine how the narrower lands and internal blockages affected the average film cooling effectiveness and the spanwise uniformity. Velocimetry data revealed that strong horseshoe vortices formed around the blockages in the slots, which resulted in greater coolant non-uniformity on the airfoil breakout surface and in the wake. The thinner lands of the island airfoil allowed the coolant to cover a larger fraction of the trailing edge span, giving a much higher spanwise-averaged surface effectiveness, especially near the slot exit where the generic airfoil lands are widest.
AB - Measurements of the 3D velocity and concentration fields were obtained using magnetic resonance imaging for a pressure side cutback film cooling experiment. The cutback geometry consisted of rectangular slots separated by straight lands; inside each of the slots was an airfoil-shaped blockage. The results from this trailing edge configuration, the "island airfoil," are compared to the results obtained with the "generic airfoil," a geometry with narrower slots, wider, tapered lands, and no block- Ages. The objective was to determine how the narrower lands and internal blockages affected the average film cooling effectiveness and the spanwise uniformity. Velocimetry data revealed that strong horseshoe vortices formed around the blockages in the slots, which resulted in greater coolant non-uniformity on the airfoil breakout surface and in the wake. The thinner lands of the island airfoil allowed the coolant to cover a larger fraction of the trailing edge span, giving a much higher spanwise-averaged surface effectiveness, especially near the slot exit where the generic airfoil lands are widest.
UR - http://www.scopus.com/inward/record.url?scp=84881165843&partnerID=8YFLogxK
U2 - 10.1115/GT2012-68364
DO - 10.1115/GT2012-68364
M3 - Conference contribution
AN - SCOPUS:84881165843
SN - 9780791844700
T3 - Proceedings of the ASME Turbo Expo
SP - 1279
EP - 1288
BT - ASME Turbo Expo 2012
Y2 - 11 June 2012 through 15 June 2012
ER -