STUDIES ON DOWNSTREAM STATOR WITH ROTOR RE-STAGGERING AND FORWARD SWEEPING IN A SUBSONIC AXIAL COMPRESSOR STAGE

The present numerical work studies the flow field in subsonic axial compressor stator passages for: (a) preceding sotor sweep (b) preceding rotor re-staggering (three stagger ngle changes: 0 degrees, +3 degrees and +5 degrees); and (c) stator sweeping (two 20 degrees forward sweep schemes). The following are the motives for the study: at the off-design conditions, compressor rotors are -e-staggered to alleviate the stage mismatching by adjusting the -ows to the operating flow incidence. Fundamental to this is the understanding of the effects of rotor re-staggering on the downstream component. Secondly, sweeping the rotor stages titers the axial distance between the successive rotor-stator;tages and necessitates that the stator vanes must also be swept. To the best of the author's knowledge, stator sweeping to suit;uch scenarios has not been reported. The computational model for the study utilizes well resolved hexahedral grids. A commercial CFD package kNSYS(R) CFX 11.0 was used with standard k-omega turbulence model for the simulations. CFD results were well validated with experiments. The following observations were made: (1) When the rotor passage is closed by re-staggering, with the same mass flow rate and the same stator passage area, stators were subjected to negative incidences. (2) Effect of stator aweeping on the upstream rotor flow field is insignificant Comparison of total pressure rise carried by the downstream stators suggests that an appropriate redesign of stator is zssential to match with the swept rotors. (3) While sweeping the stator is not recommended, axial sweeping is preferable over true sweeping when it is necessary.