Gas turbine blade damper

A gas turbine engine having an axis, an upstream direction, a downstream direction, a disk, and a plurality of blades;

• each blade having a airfoil, a blade platform, a neck a root, and each blade platform having an underside;
• the root of each blade secured in said disk;
• the neck of each blade having a cross-sectional area substantially a continuation in the shape of the airfoil;
• the platform of each blade having a cantilevered upstream portion with a radius underblade filet having a surface thereunder fairing into the neck, and having a concave blade side platform edge and a convex blade side platform edge parallel to each other;
• an integrated damper and windage cover comprising:
• an elongated damper having a contact portion and a windage cover portion having a surface;
• said contact portion contacting the underside of two adjacent blade platforms;
• said windage cover portion cantilevered from an upstream end of said contact portion, shaped with the same curvature as said underblade filet, located between adjacent blades with the windage cover portion surface in alignment with the surface of said underblade filet on adjacent blades, and with said windage cover portion free of contact with said platforms.