Patent ID: 7862294

Claim:
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, the inner ring includes an axially extending arm, the free end of the arm including an integrally formed radially inward extending projection; a rotationally stationary element that includes a projection, wherein the inner ring projection and the rotationally stationary element projection are secured together forming a hook engagement; a side wall of the rotor shaft shoulder arranged opposite an end side of the inner ring and extended in the radial direction; a securing ring which inhibits axial displacement of the inner ring; and an upper labyrinth seal portion formed by the inner ring and a lower labyrinth seal portion formed by the radially extended side wall of the shaft shoulder, the lower labyrinth seal portion composed of a plurality of radially stacked labyrinth seals.