DIFFUSER AND ASSOCIATED COMPRESSOR SECTION OF AIRCRAFT ENGINE

A compressor section (18) has a centrifugal impeller (40) operable to rotate around an axis (42), the centrifugal impeller (40) having blades (44), a compressor inlet (48) oriented towards the front and axially relative the axis (42), a compressor outlet (50) oriented radially outwardly relative the axis (42), a diffuser (54) having a diffusion flow path (56), a diffuser inlet (58) in fluid flow communication with the compressor outlet (50), a diffusion flow path (56) between a rear wall (62; 262) and a front wall (64); a collector (68) extending circumferentially around the axis (42), having a collector inlet in fluid communication with the diffuser outlet (60), and a collector outlet; and hollow structural members (70; 170; 270) protruding rearwardly from the rear wall (62; 262), the hollow structural members (70; 170; 270) being circumferentially interspaced from one another, each hollow structural member (70; 170; 270) having a length extending radially along the rear wall (62; 262) and having an internal conduit (80) extending radially inwardly along the length.