Patent ID: 11098593

Abstract:
A rotor blade for disposition in a hot gas duct of a turbomachine, the rotor blade having an airfoil and an inner platform radially inwardly thereof, the inner platform having a chamber formed therein which is radially outwardly bounded by an inner shroud of the inner platform and is axially bounded between a forward chamber wall and a rearward chamber wall of the inner platform. A forward sealing plate is disposed at the forward chamber wall and extends axially forwardly away from the chamber, and a rearward sealing plate is disposed at the rearward chamber wall and extends axially rearwardly away from the chamber. Furthermore, an axial partition is disposed in the chamber, which axial partition divides the chamber into a radially inner chamber wall region and a radially outer chamber wall region and which, when viewed in an axial cross section, extends into the forward chamber wall at the level of the forward sealing plate and into the rearward chamber wall at the level of the rearward sealing plate.