Experimental investigation of wake-induced transition in a highly loaded linear compressor cascade

The effects of wake passing on boundary layer transition in a highly loaded linear compressor cascade were investigated using different measurement techniques, such as fast-response Kulite sensors, hot-film array and hot-wire measurements. The experiments were performed in a high speed cascade wind tunnel with an inlet Mach number of 0.67 and Reynolds number 450000. Cylindrical bars moving parallel to the cascade inlet plane simulate the wakes of an upstream blade row. These basic investigations of unsteady transition also contribute to a database for numerical code validation at Mach and Reynolds numbers representative for real turbomachinery conditions.