The showerhead region of a film-cooled turbine vane in a gas turbine engine involves a complex interaction between mainstream flow and coolant jets. This flow field was studied using three component laser Doppler velocimeter measurements in a simulated turbine vane test facility. Measurements were focused around the stagnation row of holes. Low and high mainstream turbulence conditions were used. The spanwise orientation of the coolant jets, typical for showerhead coolant holes, had a dominating effect. Very high levels of turbulence were generated by the mainstream interaction with the coolant jets. Furthermore, this turbulence was highly anisotropic, with the spanwise component of the turbulent fluctuations being twice as large as the other components. Finally, there was an interaction of the high mainstream turbulence with the coolant injection resulting in increased turbulence levels for the spanwise velocity component, but had little effect on the other velocity components.
Three Component Velocity Field Measurements in the Stagnation Region of a Film Cooled Turbine Vane
Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, New Orleans, Louisiana, June 4–7, 2001. Manuscript received by the IGTI, October 28, 2000. Paper No. 2001-GT-402. Review Chair: R. A. Natole.
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Polanka, M. D., Cutbirth, J. M., and Bogard, D. G. (July 10, 2002). "Three Component Velocity Field Measurements in the Stagnation Region of a Film Cooled Turbine Vane ." ASME. J. Turbomach. July 2002; 124(3): 445–452. https://doi.org/10.1115/1.1459733
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