Heat localising segment for a turbine with grooves formed in segment wall

摘要

Casing of a gas turbine is protected form heat effects by a heat localising segment (1) in which grooves (9) are provided on a segment wall (2) in an area opposite the blade head (29) of turbine blades (22) and/or guide vanes. Preferably the grooves are opposite guide vane heads and a coating (11) of zirconium oxide containing yttrium oxide is applied to the surface of the grooves. Grooves are preferably formed parallel to a perpendicular plane through an axis of the rotor. Cooling channels may open into the grooves.