Heat shield device in gas turbines

1. Field of the Invention A rotor () of a turbomachine comprises a basic rotor element () and a multiplicity of rotor blades (). The rotor blades () are arranged in a distributed manner in at least one row on the circumference of the basic rotor element (). An area for a row of guide vanes is furthermore provided in front of and/or behind the row of rotor blades. A heat shield element () or a plurality of heat shield elements () lined up on the circumference of the rotor () is arranged in such a way between the basis rotor element () and the rotor blades () of the row of rotor blades that the basic rotor element () is completely covered in the areas of the row of rotor blades and the row of guide vanes. In this arrangement, the heat shield elements () each extend at least over the area of one row of rotor blades and at least part of the area of at least one row of guide vanes.