Patent ID: 8444375
Filing Date: 2013-05-21
Classification: F01D,F05D,Y10T

Abstract:
1. A blade for a gas turbine, comprising: a platform; a blade tip; a leading edge; a trailing edge; and an airfoil extending between the platform and the blade tip, the airfoil being bounded in at least one direction, by the leading edge and the trailing edge and having a suction side and a pressure side, wherein in a region of the trailing edge and in a direction running parallel to the trailing edge from the platform up to the blade tip, in an interior of the airfoil, there is a first cooling duct for feeding a coolant flow from the platform and from which coolant is guided to an outside of the airfoil via a multiplicity of holes arranged distributed on the blade, wherein a flow cross section of the first cooling duct tapers toward the blade tip from the platform, the taper being between 35% and 59%, wherein the holes arranged distributed on the blade are elongated cooling bores produced with low geometric tolerance by at least one of Electro-Discharge Machining and laser drilling; the elongated cooling bores including first cooling bores arranged distributed along the trailing edge; and second cooling bores arranged distributed on the blade tip, wherein the first and second cooling bores open into an exterior on the pressure side of the blade or have been introduced into the blade from the pressure side, wherein the first cooling bores have a cylindrical shape, a ratio of a length to a diameter of the first cooling bores is between 20 and 35, a spacing of neighboring first cooling bores in a radial direction is 2 to 5 times their diameter, the first cooling bores enclose with a horizontal an angle of 20°-40°, and an angle of the first cooling bores to a surface of the blade is between 8° and 15°.