Patent ID: 6572329
Filing Date: 2003-06-03
Classification: F01D,F05D

Abstract:
A gas turbine blade directed along a blade axis, comprising:a profile portion, including a suction side, a delivery side, an inlet edge and an outlet edge, wherein the profile portion includes an inner cavity for the guidance of a cooling fluid, the inner cavity including an inlet edge cavity adjacent to the inlet edge and a first part cavity adjoining the inlet edge cavity in the direction of the outlet edge, the first part cavity being divided into a first subspace and a second subspace by a partition extending in a direction from the inlet edge to the outlet edge, and wherein a cooling fluid is capable of being introduced from the first subspace via impact-cooling orifices into the inlet edge cavity and into the second subspace with an impact-cooling effect on the inlet edge, wherein the first part cavity includes adjoining in the direction of the outlet edge, a second part cavity separated from the first part cavity by a rib extending from the suction side to the delivery side, the cooling fluid being capable of being introduced through ducts in the rib from the second subspace into the second part cavity.