To develop quality computational codes for the film cooling of a turbine vane, a detailed understanding is needed of the physical mechanisms of the mainstream-coolant interactions. In this study flow visualization, thermal profiles, and laser Doppler velocimetry measurements were used to define the thermal and velocity fields of the film cooled showerhead region of a turbine vane. The showerhead consisted of six rows of spanwise oriented coolant holes, and blowing ratios ranged from 0.5 to 2.0. Performances with low and high mainstream turbulence levels were tested. Coolant jets from the showerhead were completely separated from the surface even at relatively low blowing ratios. However, the interaction of the coolant jets from laterally adjacent holes created a barrier to the mainstream flow, resulting in relatively high adiabatic effectiveness.

1.
Polanka, M. D., 1999, “Detailed Film Cooling Effectiveness and Three Component Velocity Field Measurements on a First Stage Turbine Vane Subject to High Freestream Turbulence,” Ph.D. dissertation, The University of Texas at Austin, Austin, TX.
2.
Drost, U., and Bo¨lcs, A., 1999, “Performance of a Turbine Airfoil with Multiple Film Cooling Stations Part 1: Heat Transfer and Film Cooling Effectiveness,” ASME Paper No. 99-GT-171.
3.
Du, H., Han, J.-C., and Ekkad, S. V., 1997, “Effect of Unsteady Wake on Detailed Heat Transfer Coefficient and Film Effectiveness Distributions for a Gas Turbine Blade,” ASME Paper No. 97-GT-166.
4.
Takeishi
,
K.
,
Aoki
,
S.
,
Sato
,
T.
, and
Tsukagoshi
,
K.
,
1992
, “
Film Cooling on a Gas Turbine Rotor Blade
,”
ASME J. Turbomach.
,
114
, pp.
828
834
.
5.
Thole, K. A., Sinha, A. K., Bogard, D. G., and Crawford, M. E., 1992, “Mean Temperature Measurements if Jets With a Crossflow for Gas Turbine Film Cooling Application,” Rotating Machinery Transport Phenomena, J. H. Kim and W. J. Yang, eds., Hemisphere Pub. Corp., New York, NY, pp. 65–81.
6.
Oke, R. A., and Simon, I. W., 2000, “Measurements in Film Cooling with Lateral Injection: Adiabatic Effectiveness Values and Temperature Fields,” ASME Paper No. 2000-GT-597.
7.
Pietryzk
,
J. R.
,
Bogar
,
D. G.
, and
Crawford
,
M. E.
,
1990
, “
Effect of Density Ratio on the Hydrodynamics of Film Cooling
,”
ASME J. Turbomach.
,
112
, pp.
437
450
.
8.
Sinha
,
A. K.
,
Bogard
,
D. G.
, and
Crawford
,
M. E.
,
1991
, “
Gas Turbine Film Cooling: Flowfield due to a Second Row of Holes
,”
ASME J. Turbomach.
,
113
, pp.
450
456
.
9.
Wang
,
H. P.
,
Olson
,
S. J.
,
Goldstein
,
R. J.
, and
Eckert
,
E. R. G.
,
1997
, “
Flow Visualization in a Linear Turbine Cascade of High Performance Turbine Blades
,”
ASME J. Turbomach.
,
119
, pp.
1
8
.
10.
Roy, R. P., Squires, K. D., Gerendas, M., Song, S., Howe, W. J., and Ansari, A., 2000, “Flow and Heat Transfer at the Hub Endwall of Inlet Vane Passages—Experiments and Simulations,” ASME Paper No. 2000-GT-198.
11.
Schwarz, S. G., Goldstein, R. J., and Eckert, E. R. G., 1990, “The Influence of Curvature on Film Cooling Performance,” ASME Paper No. 90-GT-10.
12.
Polanka, M. D., Cutbirth, J. M., and Bogard, D. G., 2001, “Three Component Velocity Field Measurements in the Stagnation Region of a Film Cooled Turbine Vane,” ASME Paper No. 2001-GT-0402.
13.
Polanka, M. D., Witteveld, V. C., and Bogard, D. G., 1999, “Film Cooling Effectiveness in the Showerhead Region of a Gas Turbine Vane Part I: Stagnation Region and Near-Pressure Side,” ASME Paper No. 99-GT-48.
14.
Cutbirth, J. M., 2000, “Turbulence and Three-Dimensional Effects on the Film Cooling of a Turbine Vane,” Ph.D. dissertation, The University of Texas at Austin, Austin, TX.
15.
Witteveld, V. C., Polanka, M. D., and Bogard, D. G., 1999, “Film Cooling Effectiveness in the Showerhead Region of a Gas Turbine Vane Part II: Stagnation Region and Near-Suction Side,” ASME Paper No. 99-GT-49
16.
Ethridge, M. I., Cutbirth, J. M., and Bogard, D. G., 2000, “Effects of Showerhead Cooling on Turbine Vane Suction Side Film Cooling Effectiveness,” ASME IMECE Conference, Orlando, FL.
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