A system for a gas turbine engine, comprising: a turbine, comprising: a turbine rotor comprising a blade mounting region having a plurality of blade mounts disposed circumferentially about a rotational axis of the turbine rotor, first grooves and second grooves, where the second grooves are axially disposed between the turbine rotor and a second rim, said first and second grooves (64, 66) extending circumferentially along the blade mounting region at a radial offset from one another relative to the rotational axis; a plurality of blades disposed in the plurality of blade mounts; and a segmented cover assembly comprising a plurality of cover segments, each cover segment configured to mount in first and second grooves (64,66) circumferentially along the blade mounting region, wherein each cover segment comprises: a cover body comprising first and second lips (94,98) extending along first and second circumferential portions (96,98) of the cover body at an offset from one another, wherein the first lip is configured to mount circumferentially along the first groove, the second lip is configured to mount circumferentially along the second groove; and at least one fastener configured to retain the cover body to the turbine rotor or at least one blade mounted in the blade mounting region, wherein the first lip comprises a protrusive portion having a fastener receptacle configured to receive the at least one fastener, and the second lip comprises a hook portion configured to mount circumferentially along the second groove, said hook portion configured to mount around the second rim and into the second groove. a turbine rotor comprising a blade mounting region having a plurality of blade mounts disposed circumferentially about a rotational axis of the turbine rotor, first grooves and second grooves, where the second grooves are axially disposed between the turbine rotor and a second rim, said first and second grooves (64, 66) extending circumferentially along the blade mounting region at a radial offset from one another relative to the rotational axis; a plurality of blades disposed in the plurality of blade mounts; and a segmented cover assembly comprising a plurality of cover segments, each cover segment configured to mount in first and second grooves (64,66) circumferentially along the blade mounting region, wherein each cover segment comprises: a cover body comprising first and second lips (94,98) extending along first and second circumferential portions (96,98) of the cover body at an offset from one another, wherein the first lip is configured to mount circumferentially along the first groove, the second lip is configured to mount circumferentially along the second groove; and at least one fastener configured to retain the cover body to the turbine rotor or at least one blade mounted in the blade mounting region, wherein the first lip comprises a protrusive portion having a fastener receptacle configured to receive the at least one fastener, and the second lip comprises a hook portion configured to mount circumferentially along the second groove, said hook portion configured to mount around the second rim and into the second groove. a cover body comprising first and second lips (94,98) extending along first and second circumferential portions (96,98) of the cover body at an offset from one another, wherein the first lip is configured to mount circumferentially along the first groove, the second lip is configured to mount circumferentially along the second groove; and at least one fastener configured to retain the cover body to the turbine rotor or at least one blade mounted in the blade mounting region, wherein the first lip comprises a protrusive portion having a fastener receptacle configured to receive the at least one fastener, and the second lip comprises a hook portion configured to mount circumferentially along the second groove, said hook portion configured to mount around the second rim and into the second groove.