Patent ID: 9631508
Date: 2017-04-25
CPC Classifications: F01D,F05D

Claim:
1. A contact seal assembly for a shaft of a gas turbine engine, comprising: one or more carbon ring segments mounted in a fixed position within a housing; and an annular seal runner adapted to be connected to the shaft of the gas turbine engine and rotatable relative to the carbon ring segments, the seal runner being disposed adjacent to and radially inwardly from the carbon ring segments and abutting thereagainst during rotation of the seal runner to form a contact interface between the seal runner and the carbon ring segments which forms a substantially fluid tight seal; the seal runner comprising concentric inner and outer annular portions which are radially spaced apart to define therebetween at least one internal fluid passage, said fluid passage formed by a plurality of serially interconnected passage segments which intersect each other to create a tortuous fluid flow path through the fluid passage, the plurality of serially interconnected passage segments defining the tortuous fluid flow path being adapted to receiving cooling fluid therein for cooling the seal runner from within, and the seal runner having multiple oil scoops integrally formed in the inner annular portion and disposed in fluid flow communication with the internal fluid passage, the multiple oil scoops being circumferentially spaced apart about the inner annular portion and feeding cooling oil into said fluid passage.