Siemens Aktiengesellschaft

Andreas Stihl Ag Co. Kg

Deutsches Zentrum Fur Luft-und Raumfahrt E.v.

Georg Kröger

Christian Cornelius

Cornelius Gindele

Christian Barth

Ulrich Siller

Silke Kaminski

Simon Klingler

Eberhard Nicke

Marcel Aulich

Markus Zauner

Thilo STÜRZEL

A compressor blade for an axially permeated compressor, preferably of a stationary gas turbine is provided. The camber line of the blade tip side profile of the blade of the compressor blade includes at least two inflection points for reducing radial gap losses. By means of two inflection points, there is a concavely designed suction side contour segment in a segment from 35% to 50% for the suction side contour, and a convexly implemented pressure side contour segment for the pressure side contour. It is possible by means of the geometry to generate low-loss gap vortices, in order to increase the overall efficiency of an axial compressor including the compressor blades.

Compressor blade for an axial compressor

An axial turbomachine including a rotor blade cascade is provided. The rotor blade cascade includes rotor blades each including front edge, a radially outer free blade tip and an annular enclosure enclosing the rotor blade cascade with an annulus inner side by means of which the annular enclosure is arranged directly adjacent to the blade tips to give a radial gap between the enveloping ends of the blade tips and the annulus inner side. The rotor blades include a radial projection in the region of the front edge on the blade tip and the annular enclosure has an annular radial recess in the annulus inner side, arranged at a radial distance from the ends of the blade tips, such that in the main flow direction of the axial turbomachine the line of the radial projections on the side facing the radial gap matches the line of the radial recess.

Axial turbo engine with low gap losses

Growing community of inventors

Kö'ln, Germany

Georg Kröger