Patent ID: 7033138
Filing Date: 2006-04-25
Classification: F01D,F05D

Abstract:
1. A ring segment of a gas turbine which comprises a blade ring, a main shaft and moving blades, comprising a plurality of individual units which define an annular form by being arranged around a peripheral direction of the main shaft, and disposed so that its inner peripheral surface is maintained at a constant distance from tips of the moving blades, each individual unit comprising: grooves which extend along an axial direction of the main shaft, each groove facing a groove formed in an adjacent individual unit; a seal plate for connecting together each adjacent pair of individual units, said seal plate being inserted into the grooves of adjacent units; a convex side edge which is formed to be convex on a radially inward side of the seal plate so as to project a convex portion into a concave side edge of a first adjacent individual unit; a concave side edge which is formed to be concave on the radially inward side of the seal plate so as to receive a convex side edge of a second adjacent individual unit; contact surfaces defined on the radially inward side of the seal plate when the convex side edge of the individual unit and the concave side edge of the first adjacent individual unit are fitted together, beveled portions of the convex side edge and concave side edge on both radially inward peripheral side surfaces of said individual unit, each beveled portion facing a beveled portion of the adjacent individual unit, both beveled portions covered by a thermal barrier coating; and ejection apertures of a plurality of conduits including a first conduit which is open toward upstream, a second conduit which is open toward downstream, and a third conduit which is open toward the adjacent individual unit.