抄録
Large-scale detached eddy simulations (DES) have been conducted on the K computer, in order to elucidate the flow mechanism of the rotating stall inception in a multi-stage axial compressor for an actual gas turbine. In the present study, the front half stages of the 14-stage axial compressor used for a 30MW class industrial gas turbine were analyzed by taking advantage of data mining techniques, with which vortex structures were identified by the critical point theory and limiting streamlines were visualized by the line integral convolution (LIC) method. This paper describes unsteady flow phenomena in the compressor at stall inception, which were seen on the hub side not the tip side.
