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Tubercles are modifications to the leading edge of an airfoil in the form ofblunt wave-like serrations. Several studies on the effect of tubercles onisolated airfoils have shown a beneficial effect in the post-stall regime, asreduced drag and increased lift, leading to a delay of stall. The prospect ofdelaying stall is particularly attractive to designers of axial compressors ingas turbines, as this leads to designs with higher loading and therefore higherpressure rise with fewer number of stages. In the present study, experimentswere performed on a cascade of airfoils with NACA 65209 profile with differenttubercle geometries. The measurements were made over an exit plane using afive-hole probe to compare the cascade performance parameters. Additionally,hot-wire measurements were taken near the blade surface to understand thenature of the flow in the region close to the tubercles. Oil-flow visualizationon the cascade end wall reveal the flow through the passage of blades with andwithout tubercles. For the cascade considered, the estimated stall angle forthe best performing set of blades is found to increase up to 8.6{\deg} fromthat of the unmodified blade of 6.0{\deg}. Application of such structures inaxial compressor blades may well lead to suppression of stall in axialcompressors and extend the operating range.

Effect of Leading Edge Tubercles on Compressor Cascade Performance