Turbo machine and gas turbine

Abstract

A gas turbine () includes a rotor () which has two rotor blade rows () with a plurality of rotor blades (), and also a rotor heat shield (), which is arranged between them, with a plurality of heat shield elements (), and with a stator () which has a stator blade row (), with a plurality of stator blades (), which is arranged axially between the two adjacent rotor blade rows (). The stator blades () have a stator sealing structure () radially on the inside. The heat shield elements () have a rotor sealing structure () radially on the outside which interacts with the stator sealing structure () for forming an axial seal (). Furthermore, a blade radial seal () is formed between two adjacent rotor blades (), and also a heat shield radial seal () is formed between two adjacent heat shield elements (), and in each case separates a gas path () from the rotor (). For increasing efficiency, the heat shield elements () and the rotor blades () are matched to each other so that the heat shield radial seal () merges without interruption into the blade radial seals () of the two axially adjacent rotor blades () in such a way that a continuous radial seal () is formed from the one rotor blade (), via the heat shield element (), to the other rotor blade ().