AXIAL TURBO ENGINE WITH LOW GAP LOSSES

摘要

The machine i.e. axial compressor (1), has rotor blades (2) comprising a front edge (8), a radially outer free blade tip (15) and an annular enclosure (13). Rotor blades have a radial projection (18) in a region of the front edge on the blade tip. The annular enclosure has an annular radial recess (17) at an annulus inner side (14). The recess is arranged at a radial distance from enveloping ends of the blade tip such that a gradient of the radial projections on the side facing the radial gap (16) emulates a gradient of the radial recess along a main flow direction of the engine.