Abstract: A self-induced structure was designed for the trailing edge of the guide vane of a centrifugal compressor to reduce the impact of rotor-stator interaction and the aerodynamic load on the following impeller， which improved the safety of the impeller. Through the effect of pressure differences， the structure of the trailing edge of the guide vane regulated the flow phenomenon and the partial wake of the guide vane was compensated. Based on the numerical simulation， a centrifugal compressor with adjustable inlet guide vane was used as an example. The results showed that the self-induced flow in the guide vane is not remarkable at the 0 degree guide vane angle. With the increase of the guide vane angle， the wall separation flow and the pressure differences on the guide vane are increased， and the internal self-induced flow is strengthened. With small increase of wake intensity near the root， the wakes distribution at the middle and top is improved， i.e. the pure wake reduces to a weak wake， which further decreases the aerodynamic load on the impeller. Meanwhile， without any injection air， the self-induced structure has little influence on the compressor performance.

Key words: centrifugal compressor, adjustable inlet guide vane, self-induced, aerodynamic load, numerical simulation