Blade crown ring for gas turbine aircraft engine has each blade provided with transition region between blade surface and blade platform having successively decreasing curvature radii

摘要

The blade crown ring has a carrier (1) provided with equidistant openings (5), each used for reception of a platform (4) formed at the end of a respective blade (9). The transition region (6) between the platform and the blade surface (2) of each blade has at least 2 different curvature radii with respective centres of curvature, the greatest radius of curvature lying next to the blade surface, with progressive reduction in the curvature radius in the direction of the platform.