Patent ID: 8348615
Filing Date: 2013-01-08
Classification: F01D,F05D

Abstract:
1. A gas turbine engine rotor disc, comprising: a rotor disc surface; a plurality of passages having an essentially radial orientation relative to an axis of rotation of the rotor disc, each of the plurality of passages having an inlet and an outlet and being inclined relative to the rotor disc surface wherein the outlet is arranged in the rotor disc surface; and a cut-out in the form of a notch or indention in the rotor disc surface arranged at the outlet end of at least one of the plurality of passages and having a depth, wherein the at least one of the plurality of passages is inclined in an axially downstream direction relative to a hot gas stream so that the respective cut-out is arranged at an upstream edge of the outlet, and wherein the diameter of each passage gradually increases from the end of the cut-out closest to the inlet to the outlet due to the cut-out.