Labyrinth Seal in a Stationary Gas Turbine

Abstract

A segmented inner ring for holding guide blades is provided. A lateral wall opposing the front side of the inner ring and pertaining to a shaft shoulder formed on the rotor shaft extends radially. Also a stationary gas turbine comprising a segmented inner ring is provided.

1 . A stationary gas turbine engine, comprising:
 a compressor arranged within the engine that provides a compressed airstream flow;   a combustion chamber located downstream of the compressor;   a turbine located downstream of the combustion chamber;   a lower housing portion and an upper housing portion defining a parting plane between the housing portions;   a rotor having a centerline located along the parting plane, the rotor having a shaft shoulder;   a guide vane ring which supports a plurality of guide vane segments at an outermost radial end of the segments, the guide vane segments arranged coaxially around the rotor at angular intervals;   a segmented inner ring which supports a radial innermost edge of the guide vanes; and   a securing ring which inhibits axial displacement of the inner ring.   
     
     
         2 . The gas turbine engine as claimed in  claim 2 , wherein the guide vane segments are arranged around the rotor at equal angular intervals. 
     
     
         3 . The gas turbine engine as claimed in  claim 2 , wherein the inner ring is secured to a rotationally stationary element. 
     
     
         4 . The gas turbine engine as claimed in  claim 2 , wherein the inner ring is secured to the guide vanes. 
     
     
         5 . A split u-ring for use in a turbo machine, comprising:
 a rotationally stationary first ring portion arranged concentric with a rotational centerline of the turbomachine, where the first ring portion   supports a radially innermost portion of a stationary guide vane of the turbomachine, and   has a radially inward facing hook arrangement; and   a rotationally stationary second ring portion arranged downstream of and immediately adjacent to the stationary first ring portion, where the second ring portion further supports the radially innermost portion of a stationary guide vane of the turbomachine.