Grid division method used for inner flow passage of blade part of turbo-machinery

The invention discloses a grid division method used for an inner flow passage of a blade part of a turbo-machinery. The method comprises the following specific steps of obtaining a three-dimensional geometric model of the blade part of the turbo-machinery; inserting a group of mutually disjoint revolution surfaces between a blade root and a blade tip, wherein a revolution axis of each surface is coincided with a rotary shaft of the turbo-machinery; according to a blade number, dividing each revolution surface into multiple single-channel surfaces; converting the single-channel surfaces to a two-dimensional plane, thereby obtaining a planar geometric region; dividing the planar region into multiple sub-regions, and dividing a two-dimensional structured grid in each sub-region; converting planar grids into surface grids; and superposing the surface grids of all layers together, and connecting corresponding grid nodes in adjacent layers to generate a three-dimensional grid. The method hasthe advantages of conven