Abstract: A gas turbine engine includes a turbine section that has a disk rotatable about an axis. The disk has circumferentially-spaced blade mounting features and radially outer rim surfaces extending circumferentially between the blade mounting features. Turbine blades are mounted circumcumferentially around the disk in the blade mounting features. Seals are arranged radially outwards of the disk adjacent the radially outer rim surfaces such that there are respective passages between the seals and the radially outer rim surfaces. The radially outer rim surfaces include radially-extending protrusions that extend into the respective passages.

Abstract: A turbine blade damper seal assembly includes a seal and a damper that both abut a radially outermost non-gas path surface. The seal is fabricated from a plastically deformable material and nests within a recess of the damper. The damper is fabricated from a rigid material that absorbs vibrational energy generated during operation. The recess within the damper provides for both the damper and the seal to be positioned at the radially outermost non-gas path surface.

Abstract: A turbine blade damper seal assembly includes a seal and a damper that both abut a radially outermost non-gas path surface. The seal is fabricated from a plastically deformable material and nests within a recess of the damper. The damper is fabricated from a rigid material that absorbs vibrational energy generated during operation. The recess within the damper provides for both the damper and the seal to be positioned at the radially outermost non-gas path surface.