second rims 112 and 114 by first forward and aft blade retainers 120 and second forward and aft blade retainers 122 respectively first and second disks 108 and 110 include first and second webs 124 and 126 extending radially inwardly from first and second rims 112 and 114 to first and second hubs 128 and 130 respectively first stage disk assembly 102 includes a cooling air deswirler 132 located radially outward from a conical shaft connection 134 to a substantially cylindrical shaft 136 extending axially forwardly from first hub 128 of disk 108 a flow of cooling air 138 is channeled from a high pressure compressor discharge not shown through a cavity 140 deswirler 132 and through at least one of a plurality of air passages 142 that channels cooling air onboard disk assemblies 102 and 104 at least a portion of the flow of cooling air 138 is channeled to slots 144 and 146 in first and second rims 112 and 114 the flow of cooling air 138 is further channeled to blades 116 and 118 from slots 144 and 146 because slots 144 and 146 form a portion of the cooling air circuit for cooling air to blades 116 and 118 a dimension of slots 144 and 146 is at least partially determinant of a head loss through the cooling circuit for example if a cross sectional area of slots 144 and or 146 is reduced in size the flow of cooling air 138 to blades 116 and or 118 may be reduced in the exemplary embodiment the cross sectional area of slots 144 and or 146 is reduced in size to facilitate reducing stress damage.