Experimental investigation of the influence of density ratio and vane exit mach number on platform cooling

The present paper reports the results of an experimental investigation influence coolant to mainstream density ratio (DR) on thermal and aerodynamic behavior a nozzle vane cascade with platform cooling through slot or discrete holes. Measurements were carried out 6 at low (1.6%) high (9%) inlet turbulence intensity level, blowing ratios (BR) varied in range 1-2. Tests performed injecting carbon dioxide (DR = 1.5) as flow. Aerodynamic investigations by means miniaturized 5-hole pressure probe traversed downstream plane assess impact aforementioned parameters secondary flows structure related losses. Concerning measurements, binary PSP technique was employed measure adiabatic film effectiveness. Three schemes have been investigated: first one features located upstream leading edge, second makes use cylindrical holes distributed both inside passage last is based standard 10-10-10 shaped These will be compared previous data [1] obtained testing same level air 1). are representative real engine configurations allow critically performance for variable injection conditions.[1] G. Barigozzi, A. Perdichizzi, L. Abba, Pestelli, 2020, “Platform Film Cooling Investigation Hp Nozzle Vane Cascade Discrete Shaped Holes Slot Cooling” ASME Paper GT2020-2849.