section of a gas turbine engine fig2 is an enlarged view of the area a of fig1 showing details of the seal assembly of the present invention fig3 is a perspective view taken along the line 2 2 of fig1 fig4 is a view taken along the line 4 4 of fig2 of the wire rope used in the seal assembly of the present invention as an exemplary embodiment of the present invention consider the portion of a gas turbine engine rotor assembly generally represented by the reference numeral 10 in fig1 the rotor assembly 10 comprises a rotor 12 which includes a disk 14 having a plurality of blades 16 circumferentially spaced about the periphery thereof as best shown in fig3 each blade 16 comprises an airfoil portion 18 having a root portion 20 and platform 21 integral therewith the root portion 20 includes a fir tree shaped end 22 disposed in similarly shaped fir tree slots 24 which extend axially through the disk 14 from the disk front surface 26 through the disk rear surface 28 the slots 24 are formed between what are herein referred to as disk lugs 27 the disk 14 is secured to a shaft not shown by conventional means not shown the axis of the shaft is the axis of the engine about which the rotor assembly 10 rotates the rotor assembly 10 includes an annular plate 30 secured to the front side of the disk 14 the means by which the plate 30 is attached to the disk 14 does not form a part of the present invention in this embodiment the radially inner end 29 of the plate 30 includes an axially extending flange 32 which has a radially outwardly facing cylindrical surface 34 the front side of.