PIV(particle image velocimetry) was utilized to measure the flow field of the blade passage in a rotor of multistage turbomachinery

and was successfully applied to a four-stage large-scale low-speed compressor facility.In order to apply the PIV to compressor facilities

a light sheet periscope probe and a phase-lock system have been developed.The flow field of the third stage rotor blade passage has been measured at the design condition.Compared with the 3-D (three-dimentional) steady Navier-Stokes(N-S) solution

the measurements at the compressor design point show that the PIV measurement results reflect the flow structure of the third stage rotor blade passage reasonably.There is a big tip leakage vortex

which occupies the tip region of the rotor blade passage.There is no abnormal velocity filed and no obvious flow separation phenomenon at the other region of the rotor blade passage.