Detailed flowfield measurements were made in the end-wall region of a four-stage low-speed large-scare axial compressor test rig. Two ten-hole survey boundary layer probes, one four-hole pneumatic probe, and several dynamic pressure probes each bedded with a high-frequency response Kulite sensor, were designed and manufactured to aid the test. Boundary layer region and mainflow region could be clearly distinguished from the boundary layer measurement results. A few parameters, including boundary layer thickness, displace thickness, momentum loss thickness, energy loss thickness and blockage coefficient were calculated based on the measurements. Results from turbulent boundary layer empirical formula of plate are in good agreement with the measurements, which indicates an excellent way of boundary layer effect estimation. Outlet flowfield of the third-stage rotor, measured by the displacement mechanism driven four-hole probe, shows that the lower end-wall boundary layer thickness is clearly smaller than that of the upper region, which can be contributed to the hub rotation. The evolution trajectory of TLV is identified evidently by dynamic pressure measurements. The maximum aerodynamic load point on the blade moves from the trailing to the leading edge as flowrate decreases, which leads to the forward movement of the tip leakage vortex inception point.
