AXIAL TURBOMACHINE WITH LOW TIP CLEARANCE LOSSES

摘要

An axial turbo engine (1), comprises an impeller blade array, made up of impeller blades (3) each with a front edge (8), a radially outer free blade tip (15) and an annular enclosure (13) enclosing the impeller blade array with an annulus inner side (14) by means of which the annular enclosure (13) is arranged directly adjacent to the blade tips (15) to give a radial gap (16) between the enveloping ends of the blade tips (15) and the annulus inner side (14), wherein the impeller blades (3) have a radial projection (18) in the region of the front edge (8) thereof on the blade tip (15) and the annular enclosure (13) has an annular radial recess (17) in the annulus inner side (14) thereof, arranged at a radial distance (16) from the enveloping ends of the blade tips (15), such that in the main flow direction of the axial turbo engine (1) the line of the radial projections on the side thereof facing the radial gap (16) matches the line of the radial recess.