Patent ID: 9482094
Filing Date: 2016-11-01
CPC Classification: F01D,F05B

Claim Text:
1. A gas turbine, comprising: a rotor; a casing concentrically surrounding the rotor; an annular hot gas channel axially extending between the rotor and the casing; a plurality of blades, arranged on the rotor in an annular fashion, each of the blades including a root mounted in a respective axial slot on a rim of the rotor, and an airfoil extending radially into the hot gas channel, and adjoining with an axially oriented root surface to an annular rim cavity; and a scoop provided in the root of each of the blades to receive cooling air being injected into the rim cavity through stationary injectors, wherein the root surface is an essentially planar surface and the scoop is configured for capturing and redirecting at least part of the injected cooling air, the scoop being recessed from the root surface.