Patent ID: 8992168
Filing Date: 2015-03-31
Classification: F01D,F02C,F04D,F05D,Y02T

Abstract:
1. A blade and vane assembly for a gas turbine engine, the assembly comprising: an annular casing; a forward bladed rotor assembly configured to rotate within the annular casing about an engine centerline; an aft bladed rotor assembly configured to rotate within the annular casing; a plurality of stator vanes cantilevered from the annular casing so as to remain stationarily disposed between the forward and aft bladed rotor assemblies; and a sealing ring coupled to the forward and aft bladed rotor assemblies so as to be rotatable with the bladed rotor assemblies, the sealing ring comprising: an outer diameter rim for engaging inner diameter ends of the plurality of stator vanes; an inner diameter rim spaced radially from the outer diameter rim; a forward face for engaging with the forward rotor assembly; an aft face for engaging with the aft rotor assembly; an air passage extending from the forward face to the aft face between the inner and outer diameter rims; and sidewalls connecting the inner diameter rim to the outer diameter rim to define a plurality of air passages that are angled relative to the engine centerline.