An airseal for sealing between a rotating component and a stationary component of a turbine engine includes a sealing surface defining a spacing between the airseal and a rotating component of the turbine engine and a mounting flange to secure the airseal to a stationary component of the turbine engine. An airseal body extends between the sealing surface and the mounting flange. The airseal body includes a cavity configured to absorb thermal energy transferred into the airseal from a flowpath of the turbine engine. A gas turbine engine includes a rotating component and a stationary component located radially outboard of the rotating component. An airseal is located therebetween and includes a sealing surface and a mounting flange to secure the airseal to the stationary component. An airseal body extends between the sealing surface and the mounting flange and includes a cavity to absorb thermal energy transferred into the airseal.