Patent ID: 9739151
Date: 2017-08-22
CPC Classifications: F01D,F02C,F05D,Y02T

Claim:
1. A blade for a turbomachine, comprising: a blade root, wherein the blade root is attached to a base of a rotor base body, wherein the blade root has a concave side wall, wherein the concave side wall merges in a flush manner with a wall of the rotor base body which extends between the base and an adjacent base with an adjacent blade root, and wherein the concave wall defines a passage between the blade root and the adjacent blade root for a first cooling air partial flow; a blade neck associated with the blade root; a blade pan; and a platform disposed between the blade neck and the blade pan, wherein the platform includes a front projection and a rear projection, as viewed in a flow direction of a hot gas flow, and wherein a cool cooling air flow is delimitable from the hot gas flow by the front projection and the rear projection; wherein the blade neck includes at least one cooling channel, wherein a second cooling air partial flow is guidable through the at least one cooling channel, and wherein an inlet of the at least one cooling channel is disposed in a region of the front projection and is disposed radially inwardly and wherein an outlet of the at least one cooling channel is disposed in a region of the rear projection and is disposed radially outwardly such that an axis of the at least one cooling channel is pointed diagonally outwardly; wherein the at least one cooling channel has an expanded section between the inlet and the outlet; wherein a turbulator is disposed in the expanded section of the at least one cooling channel; and wherein the turbulator is spaced apart from a channel axis extending between the inlet and the outlet.