Numerical simulation analysis of the influence of a blade profile probe on the performance of a transonic compressor

To reveal the physical mechanism controlling the influence of a blade profile probe on the aerodynamic performance of a transonic compressor, studied in detail was the variation law of the performance characteristics and the inner flow field of a compressor at its design speed before and after a probe is installed by using a 3-D numerical simulation method and through establishing a calculation model for a 1.5-stage compressor with a multi-point-real-entity probe. The research results show that after a probe is locally installed on a stator blade between stages, the flow rate of the compressor at the lower choke point decreases by 0.1%, the maximal efficiency drops by 0.4% and the flow rate at the stall point increases by 0.15%. A change of the attack angle of the stator blade caused by a change of the working point of the compressor constitutes an important factor influencing the area of the flow going around the probe at both sides of the blade surface and a relatively high correlation degree exists between the probe-going-around flow influencing extent and the aerodynamic load of the stator blade. A large area probe-around-going flow will exacerbate the radial migration and separation of the boundary layer at the root on the back of the blade at the downstreams of the rotor constitutues the root cause of the aerodynamic stall of the compressor at an earlier time.