Abstract: A protector for attachment to and protection of a leading edge of a protective liner of an aircraft engine component includes a clip portion including a channel for receiving a portion of the protective liner including the leading edge of the protective liner. The clip portion includes at least one spacer extending therefrom to create at least one air flow gap between the clip portion of the protector and an upstream liner of the aircraft engine when the upstream liner is positioned in abutment with the at least one spacer of the clip portion. The protector includes a flange portion extending from the clip portion and including a through aperture configured to receive a portion of a fastener passing through both the aperture and at least a portion of the protective liner to attach the protector to the protective liner.

Abstract: Systems and methods for attaching a protective liner to a an aircraft engine component having a different coefficient of thermal expansion in comparison to the protective liner include a mounting member configured to be mounted to the aircraft engine component and an attachment member configured to be attached to the protective liner. The mounting member and the attachment member are coupled to each other such that a portion of the mounting member is received within a portion of the attachment member and such that the mounting member is permitted to move with both radial and rotational freedom relative to the attachment member.