Schwerpunktsfädelung of blades

The invention relates to a rotor blade for a gas turbine, in particular an aircraft gas turbine, connects with a Schaufelfuselement and a beam deflection portion in the blade longitudinal direction (RR) to the Schaufelfuselement (12), wherein respective centers of gravity (24) of blade cross-sectional surfaces of the beam deflection portion on a common thread axis ( 26) lie. According to the invention it is proposed that the thread axis (26) starting subsequent from one at the Schaufelfuselement (12) first center of gravity (24) of a first blade cross-sectional area is located within a cone (28) whose apex in the first focus (24) and the cone height ( KH) extends perpendicular to the plane of the blade cross-sectional area, wherein the opening angle (β) of the cone (28) is greater than 0 ° and less than or equal to 4 °, preferably greater than or equal to 0.5 ° and less than or equal to 2 °.