Patent ID: 7413610

Claim:
An apparatus for elevated-temperature hard-material coating/heat treatment of blade airfoils of a blisk for a gas turbine, comprising: at least two axially separable and joinable cooling plates that, when axially joined, form at least one internal cooling chamber that encloses, isolates and insulates portions of the blisk against a furnace atmosphere, while simultaneously exposing the blade airfoils to the furnace atmosphere for the elevated-temperature coating/heat treatment, the cooling plates including insulated outer surfaces, the cooling plates also including supporting flanges for heat-conductively locating front faces of blade platforms of the blisk, the cooling plates further including radial cooling medium channels connected to a cooling medium source to supply a flow of cooling medium to the at least one internal cooling chamber for direct contact with and cooling of surfaces of the supporting flanges and the blade platforms exposed within the at least one internal cooling chamber.