In the present paper, the influence of inlet flow incidence on the aerodynamic and thermal performance of a film cooled linear nozzle vane cascade is fully assessed. Tests have been carried out on a solid and a cooled cascade. In the cooled cascade, coolant is ejected at the end wall through a slot located upstream of the leading edge plane. Moreover, a vane showerhead cooling system is also realized through 4 rows of cylindrical holes. The cascade was tested at a high inlet turbulence intensity level (Tu1 = 9%) and at a constant inlet Mach number of 0.12 and nominal cooling condition, varying the inlet flow angle in the range ±20°. The aero-thermal characterization of vane platform was obtained through 5-hole probe and end wall adiabatic film cooling effectiveness measurements. Vane load distributions and surface flow visualizations supported the discussion of the results. A relevant negative impact of positive inlet flow incidence on the cooled cascade aerodynamic and thermal performance was detected. A negligible influence was instead observed at negative incidence, even at the lowest tested value of −20°.
Incidence Effect on the Aero-Thermal Performance of a Film Cooled Nozzle Vane Cascade
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Abdeh, H, Barigozzi, G, Perdichizzi, A, Henze, M, & Krueckels, J. "Incidence Effect on the Aero-Thermal Performance of a Film Cooled Nozzle Vane Cascade." Proceedings of the ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. Volume 5C: Heat Transfer. Oslo, Norway. June 11–15, 2018. V05CT19A001. ASME. https://doi.org/10.1115/GT2018-75037
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