Patent ID: 8578720
Filing Date: 2013-11-12
Classification: F01D,F02C,F05D

Abstract:
1. A gas turbine engine comprising: a supply of cooling fluid; a rotatable shaft; blade disc structure coupled to said shaft and having at least one bore for receiving a first portion of cooling fluid; a plurality of pre-swirl passages that deliver the first portion of cooling fluid from said supply of cooling fluid toward said at least one bore for cooling blades in a turbine section of the engine; a particle separator that separates solid particles from the first portion of cooling fluid after the first portion of cooling fluid passes through said pre-swirl passages and prior to the first portion of cooling fluid entering said at least one bore in said blade disc structure, said particle separator comprising: structure defining a plurality of bypass passages in fluid communication with said supply of cooling fluid for supplying a second portion of cooling fluid from said supply of cooling fluid into an enclosed turbine rim cavity upstream from said blade disc structure, wherein the second portion cooling fluid flowing through said bypass passages does not interact with the first portion of cooling fluid flowing through said pre-swirl passages or with said particle separator, said plurality of bypass passages including a first set of bypass passages and a second set of bypass passages, the first and second sets of bypass passages having inlets that are located respectively in separate chambers of the gas turbine engine and in different radial locations.