Cooled turbine rim seal

A rim seal assembly comprising:

• an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform,
• an annular platform flange extending radially inwardly from the platform,
• the platform flange disposed between and connected to forward and aft flanges at distal ends of forward and aft annular elements respectively of a high pressure rotor or a low pressure rotor,
• annular forward and aft outer rim cavities radially disposed between the forward and aft annular elements and the platform are axially separated by the platform flange, and
• cooling slots extending radially across axially facing forward and aft surfaces of the forward and aft flanges.

A gas turbine engine turbine disk assembly comprising:

• at least one pair of adjacent first and second rotor disks connected by disk forward and aft spacer arms attached to the adjacent first and second rotor disks respectively,
• at least one rim seal assembly including an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform,
• an annular platform flange extending radially inwardly from the platform,
• the platform flange disposed between and connected to forward and aft flanges at distal ends of the forward and aft spacer arms respectively,
• annular forward and aft outer rim cavities radially disposed between the forward and aft spacer arms and the platform are axially separated by the platform flange, and
• cooling slots extending radially across axially facing forward and aft surfaces of the forward and aft flanges.

A gas turbine engine turbine disk assembly comprising:

• a plurality of rotor disks,
• each of the rotor disks including a web extending radially outwardly from a hub to a disk rim,
• the plurality of rotor disks including at least one pair of adjacent first and second rotor disks connected by disk forward and aft spacer arms attached to the adjacent first and second rotor disks respectively,
• turbine blades extending radially outwardly from the disk rim of the adjacent first and second rotor disks,
• a row of vanes extending radially inwardly from a case and disposed axially between the turbine blades of the adjacent first and second rotor disks,
• an annular seal land mounted to a radially inner end of the row of vanes,
• at least one rim seal assembly including an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform,
• the annular seal element in sealing relationship with the annular seal land,
• an annular platform flange extending radially inwardly from the platform,
• the platform flange disposed between and connected to forward and aft flanges at distal ends of the forward and aft spacer arms respectively,
• annular forward and aft outer rim cavities radially disposed between the forward and aft spacer arms and the platform are axially separated by the platform flange, and
• cooling slots extending radially across axially facing forward and aft surfaces of the forward and aft flanges.

A gas turbine engine comprising:

• in downstream serial flow relationship, a fan, a compressor, a combustor, a high pressure turbine, and a low pressure turbine,
• a plurality of rotor disks in the low pressure turbine,
• each of the rotor disks including a web extending radially outwardly from a hub to a disk rim,
• the plurality of rotor disks including at least one pair of adjacent first and second rotor disks connected by disk forward and aft spacer arms attached to the adjacent first and second rotor disks respectively,
• turbine blades extending radially outwardly from the disk rim of the adjacent first and second rotor disks,
• a row of vanes extending radially inwardly from a case and disposed axially between the turbine blades of the adjacent first and second rotor disks,
• an annular seal land mounted to a radially inner end of the row of vanes,
• at least one rim seal assembly including an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform,
• the annular seal element in sealing relationship with the annular seal land,
• an annular platform flange extending radially inwardly from the platform,
• the platform flange disposed between and connected to forward and aft flanges at distal ends of the forward and aft spacer arms respectively,
• annular forward and aft outer rim cavities radially disposed between the forward and aft spacer arms and the platform are axially separated by the platform flange, and
• cooling slots extending radially across axially facing forward and aft surfaces of the forward and aft flanges.