GAS TURBINE BLADE FOR A TURBOMACHINE

摘要

The invention relates to a gas turbine blade (10), in particular a compressor blade and/or turbine blade, for a turbomachine, wherein the gas turbine blade (10) comprises at least one receptacle (18) for arranging a connecting element in a form-closed manner, by means of which connecting element a mechanical load can be applied to the gas turbine blade (10). The invention further relates to an shrouding band segment (16) for arrangement on a gas turbine blade (10), a connection system having a gas turbine blade (10) and having a connecting element, a method for connecting a gas turbine blade (10) to a connecting element, and a rotor for a turbomachine having a rotor disk (12) joined to a blade ring or having a rotor ring joined to a blade ring.