Bi-centrifugal compressor assembly for turbine engine of helicopter, has compression stage, and diffuser joint that is coupled to compressor stage of centrifugal compressor via air return channel that is inclined upstream

摘要

The assembly (1) has a set of air inlet channels (3, 4) that is coupled to two air compression stages (13, 15) via diffusers (5, 6). A pre-rotation grid (12) is positioned in another set of air inlet channels (4a, 4r), where the grid is coupled to one compression stage comprising a compressor wheel (31) that is associated with a diffuser joint. The joint is coupled to a compression stage of a centrifugal compressor via an air return channel (14) that is inclined upstream (A).