Rotor for turbo engines, especially axial flow compressor rotor for gas turbine engines

摘要

In the rotor assembled from individual annular components running coaxially with the longitudinal axis of the rotor, the rotor blades (7) (Figs. 7 and 8) freely suspended in a radial and circumferential direction have blade foot segments (8) aligned one after another in the circumferential direction, which enclose recesses (9) extending in an axial direction between the radially extending opposite faces respectively adjacent in the circumferential direction, a first (1) and a second annular component (S) being respectively fixable by means of centring lugs (10, 11) intermeshing and/or overlapping one another in these recesses (9) and the rotor blades (7) hereby being radially supported on the annular components by way of their blade feet or foot ends. The aim of this, inter alia is essentially to create a lightweight rotor of aerodynamically favourable and easily maintained design, suitable for high speeds.