A rotor system for a gas turbine engine may comprise a shrouded blade assembly. The shrouded blade assembly may include a blade configured to rotate about a central longitudinal axis of the gas turbine engine, an inner diameter shroud located at a proximal end of the blade, and a blade tip shroud located at a distal end of the blade. A radial seal assembly may be located radially outward of a distal surface of the blade tip shroud.