Abstract
Multi-holed film cooling systems are the most effective and widely used cooling techniques applied to gas turbine blades and combustor liners to obtain resistance in extremely high temperature operating conditions. This paper reports on measurements in flows generated by jets issuing from a 10:1 scaled multi-holed plate for a blowing ratio varying from 0.2 to 11. The plate geometry is similar to geometries encountered within current combustion chamber walls. The test section has 138 holes arranged on 12 staggered rows. The holes are spaced 6.74 diameters apart in the spanwise direction and 5.84 diameters apart in the downstream direction. The holes angle inclination is 30 degrees with respect to the plate surface. Mean velocity vectors and turbulent Reynolds shear stresses are measured using a two-component Laser Doppler Anemometry system. An investigation is performed to study the effects of adjacent jets flow interactions and jet-to-cross-flow combinations on the film cooling coverage, downstream from the end of the perforated zone. Results obtained are intended to help improve the aerodynamic and thermodynamic heat-transfer laws for multi-holed and near wall flows. The acquired experimental database is useful to validate different physical models and numerical codes in multi-holed flow cooling techniques.
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