extends downstream from a diffuser not shown combustion chamber 46 is generally annular in shape and is defined between liners 40 and 42 inner liner 42 and inner nozzle support 44 define an inner passageway 50 outer and inner liners 40 and 42 each extend to a turbine nozzle 52 positioned downstream from combustor 16 high pressure turbine 18 is coupled substantially coaxially with compressor 14 shown in fig1 and downstream from combustor 16 turbine 18 includes a rotor assembly 62 that includes at least one rotor 64 that may be formed by one or more disks 66 in the exemplary embodiment disk 66 includes a radially outer rim 68 a radially inner hub 70 and an integral web 72 extending generally radially therebetween and radially inward from a respective blade dovetail slot 73 each disk 66 also includes a plurality of blades 74 extending radially outward from outer rim 68 disk 66 extends circumferentially around rotor assembly 62 and each row of blades 74 is sometimes referred to as a turbine stage an annular forward disk retainer 80 and an annular aft disk retainer 82 extend along dovetail slot 73 to facilitate retaining rotor blades 74 within dovetail slot 73 specifically forward disk retainer 80 extends along an.