Patent ID: 9051847
Filing Date: 2015-06-09
Classification: F01D

Abstract:
1. A gas turbine engine rotor section comprising: a rotor body, said rotor body having a ledge extending axially from a location on said rotor body; said ledge defining a radially inner surface radially inwardly of said ledge, and a hub extending axially from said rotor, said hub extending to a downstream rotor body, and beyond said ledge, said hub having a radially outer surface spaced from said ledge radially inner surface, and a first distance defined between said radially inner surface of said ledge and said radially outer surface of said hub; and a knife edge seal, said knife edge seal having at least one pointed knife seal portion at a radially outer end, a radially inwardly extending arm, and an axially inwardly extending portion extending axially inwardly from said radially inwardly extending arm, said axially inwardly extending portion having a radially outer face and a radially inner face, and said radially inner and radially outer faces of said knife edge seal being spaced by a second distance, with said second distance being less than said first distance, and said axially inwardly extending portion being received between said radially inner surface of said rotor and said radially outer surface of said hub, such that said knife edge seal is free floating between said ledge and said hub.