Abstract: A damper for a turbine blade in a gas turbine engine includes a main body and may include at least one extended end which is adapted to clear radially inner surfaces of two adjacent blade platforms, to enhance the damping profile of the damper and radial support for a seal. An associated seal for the turbine blade includes supported and sealing portions and may further include a locator that interfaces with a catch structure on the blade to maintain the seal in the proper axial position with respect to the radially inner surfaces of the adjacent platforms. The seal may further include a projection adapted to provide interference with the blade in the event that the damper and seal are installed improperly with respect to each other to prevent such improper assembly.