The Study on Flow Characteristics of Inlet Flow Field of Compressor Experiment

Abstract

The main function of the intake system of the compressor test rig is to ensure that the air flow into a compressor is uniform and consistent. Firstly, the dimensionless total pressure on the experimental measurement section from the numerical is almost agreed with that from the experimental, except that there is only 5% deviation at 10% channel height. Therefore, the numerical simulation method is correct and the result is reliable. Secondly, the characteristics of pressure field, velocity field and boundary layer thickness before the variable inlet guide vanes (VIGV) and the first stage rotor (R1) are studied. The results show that the closed area formed by the intake stabilizing chamber and the inlet bell mouth of the test article has not affected the flow around the bell-mouth, especially the evolution and development of boundary layer. Two vortices directly behind the support plate wake are observed at the hub, which is caused by the flow channel falls. These two vortices have opposite rotational directions and axial vorticity direction. Throttle does not affect the dimensionless velocity and dimensionless pressure distribution at the inlet of the test article, nor does it affect the thickness of the boundary layer. With the increase of rotational speed and mass flow, the radial distribution becomes increasingly uniform. Meanwhile, the thickness of boundary layer at the hub and shroud decreases slightly, but the range of variation is within 1% of the channel height.