Abstract: A sealing bar is provided for each gap between adjacent shroud plates to form part of the coolant recovery system of an open-circuit, liquid-cooled gas turbine. The undersides of the edges of the shroud plates at each gap are chamfered and a small cylindrical bar is supported in the recess provided thereby. Centrifugal force urges the bar into sealing engagement with the chamfered surfaces.

Abstract: A liquid cooled turbine bucket is provided with a plurality of generally radially extending subsurface coolant channels which are supplied with liquid coolant from a manifold in the bucket tip portion. Liquid coolant is delivered directly and solely to the bucket tip manifold via conduit means extending through the root and core portions of the bucket. The liquid coolant in the coolant channels removes heat from the turbine bucket by pool boiling, the resulting vapor being collected in vapor manifolds disposed radially inwardly from the channels and exhausted from the bucket.

Abstract: An annular composite joint of wire and braze alloy fluid-tightly seals the bucket of a gas turbine to the root sidewall piece bridging the space provided between the two parts to eliminate the necessity for close tolerance fit.