Patent ID: 6832891
Filing Date: 2004-12-21
Classification: F01D

Abstract:
A device for sealing between guide vanes and a rotor of a gas turbine turbomachine, the device comprising:a cavity within each guide vane, said cavity being blown through by cooling air, each guide vane having a footing; an inner ring with a recess on an outer rim of said inner ring, wherein said inner ring is suspended on said vane footing in a thermally elastic manner; an attachment connected to said footing of each said guide vanes; a centering pin coupling, said attachment to said recess; a honeycomb seal soldiered to said footing; labyrinth tips arranged on the rotor and being located opposite said honeycomb seal; a first flow channel connected to said cavity of said guide vane, said first flow channel comprising a hole passing through said vane footing of said guide vane; and a second flow channel connected to said first flow channel, said second flow channel comprising a second hole passing through said inner ring into the vicinity of said honeycomb seal and having at least one connection leading to the outside of the inner ring.