Patent ID: 8613199
Filing Date: 2013-12-24
Classification: F01D,F02C,F05D

Abstract:
1. A gas turbine engine comprising: a supply of cooling fluid; a rotatable shaft; a plurality of passages that deliver a first portion of cooling fluid from said supply of cooling fluid to a cooling circuit defined at least partially within blade disc structure associated with a first row of blades in a turbine section of the engine; 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, 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; and metering structure located at outlets of said bypass passages, said metering structure comprising a plurality of flow passageways extending therethrough at an angle to a central axis of the engine for permitting the second portion of cooling fluid in said bypass passages to pass into an enclosed turbine rim cavity upstream from the blade disc structure, wherein the cooling fluid flowing out of said flow passageways has a velocity component in a direction tangential to the circumferential direction in the same direction as a rotation direction of said shaft; wherein the second portion cooling fluid flowing from said supply of cooling fluid through said bypass passages does not interact with the first portion of cooling fluid flowing to the cooling circuit in the blade disc structure of the engine after the second portion of cooling fluid reaches said bypass passages.