Blade structure for a gas turbine engine

The invention relates to a blade ring or blade structure for a gas turbine engine, especially an aircraft engine. A ring or disk forms a carrier for at least one blade, that forms an airfoil with its surface and is fixed to the carrier. A blade ring for a gas turbine engine, especially an aircraft engine, may be a rotor ring or disk or a stator ring. At least one blade () forming an airfoil () is secured to at least one carrier ring (). The blade () is fixed to the carrier ring or disk or shroud (), either through a platform () forming a foot portion of the blade or through a neighboring transitional section () forming part of the carrier ring or disk or shroud. The mechanical stress and the overall axial length of the blade ring are reduced by a transition fillet () between the surfaces () of the airfoil () and the platform () or the peripheral section (). The transition fillet () has a curve () that narrows toward the platform () or peripheral section () with radii (R, R, R) that have different centers and are largest close to the blade surface () and smallest close to the ring surface. This fillet construction extends all around the blade and relative to an inner ring or disk and/or an outer ring.