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A turbine section comprises a rotor, blade and rim seal. The rotor comprises a rim defining an outer diameter surface, and a slot in the outer diameter surface. The blade comprises an airfoil, a platform surrounding the airfoil, a shank extending from the platform, a root extending from the shank fo

A turbine section comprises a rotor, blade and rim seal. The rotor comprises a rim defining an outer diameter surface, and a slot in the outer diameter surface. The blade comprises an airfoil, a platform surrounding the airfoil, a shank extending from the platform, a root extending from the shank for connecting to the slot, and a nub extending from the shank beneath the platform. The rim seal is disposed between the outer diameter surface and the nub. A method for cooling an outer diameter of a rotor disk comprises bleeding cooling air in a gas turbine engine, passing the flow of cooling air through a cover plate that retains a seal plate against the rotor disk, leaking the cooing air between a rotor disk rim and the seal plate, and guiding the cooling air across an outer diameter surface of the rotor disk rim utilizing a rim seal.

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1. A turbine section for a gas turbine engine, the turbine section comprising: a rotor comprising: a rim defining an outer diameter surface;a slot through the rim across the outer diameter surface;a blade comprising: an airfoil;a platform surrounding a base of the airfoil;a shank extending from the

1. A turbine section for a gas turbine engine, the turbine section comprising: a rotor comprising: a rim defining an outer diameter surface;a slot through the rim across the outer diameter surface;a blade comprising: an airfoil;a platform surrounding a base of the airfoil;a shank extending from the platform opposite the airfoil;a root extending from the shank for connecting to the slot;a nub extending from the shank beneath the platform; anda rim seal disposed between the outer diameter surface and the nub, the rim seal comprising: an elongate body extending axially across a majority of the outer diameter surface, the elongate body comprising: a leading edge;a trailing edge;a pressure side; anda suction side. 2. The turbine section of claim 1 and further comprising a seal plate retained alongside the rotor adjacent an interface between the root and the slot. 3. The turbine section of claim 2 and further comprising: a cover plate extending across the rotor to connect to the rim; anda hook extending from the shank of the blade;wherein the seal plate is retained alongside the rim by the cover plate and hook. 4. The turbine section of claim 3 and further comprising a cooling path comprising: an opening in the cover plate;a leakage gap between the seal plate and rim; anda passage between the outer diameter surface and the rim seal. 5. The turbine section of claim 2 and further comprising: a cover plate comprising: a disk portion extending across the rotor to connect to the rim; anda seal portion extending from the disk portion and positioned adjacent an interface between the root and the slot;wherein the cover plate forms a cooling path comprising: an opening in the cover plate;a leakage gap between the seal portion and rim; anda passage between the outer diameter surface and the rim seal. 6. The turbine section of claim 1 and further comprising a gap seal disposed between the platform and the nub adjacent a mate face of the platform. 7. The turbine section of claim 1 wherein the rim seal is reversible in the leading-edge-to-trailing-edge direction. 8. The turbine section of claim 1 wherein the rim seal is scalloped at the trailing edge. 9. The turbine section of claim 1 wherein the rim seal further comprises: a first pair of notches extending into the leading edge at the pressure and suction sides; anda second pair of notches extending into the trailing edge at the pressure and suction sides. 10. The turbine section of claim 1 wherein the nub comprises an elongate shelf extending along the shank. 11. The turbine section of claim 1 wherein the nub includes: a wing at the leading edge extending circumferentially toward the rim seal; anda notch at the trailing edge, the notch extending circumferentially away from the rim seal. 12. The turbine section of claim 1 wherein the rim seal is spaced 0.020 inches to 0.080 inches from the outer diameter surface. 13. A method for cooling an outer diameter of a rotor disk in a gas turbine engine, the method comprising: bleeding a flow of cooling air in a gas turbine engine;passing the flow of cooling air through a cover plate that retains a first seal plate against the rotor disk;leaking the flow of cooing air between a rotor disk rim and the first seal plate; andguiding the flow of cooling air across an outer diameter surface of the rotor disk rim utilizing a rim seal; the rim seal comprising: an elongate body extending axially across a majority of the outer diameter surface, the elongate body comprising: a leading edge;a trailing edge;a pressure side; anda suction side. 14. The method of claim 13 and further comprising: inhibiting the flow of cooling air out of the rotor disk rim with a second seal plate. 15. The method of claim 13 and further comprising: sealing the rim seal against a retention nub extending from an adjacent blade shank. 16. The method of claim 13 and further comprising: discharging the flow of cooling air through a window between a trailing edge of the rim seal and a nub that retains the rim seal. 17. The method of claim 13 and further comprising: inhibiting gas path air from contacting the outer diameter surface with the rim seal. 18. A gas turbine engine comprising: a rotor disk comprising: a rim having a plurality of slots in an outer diameter; anda plurality of disk lugs formed in the rim to overhang the plurality of slots;a plurality of blades coupled to the rotor disk, each blade comprising: a shank including: a root disposed at an inner diameter end of the shank and disposed in a slot to be retained by a disk lug belonging to the plurality of disk lugs; anda nub extending from the shank spaced radially outward from the root;a plurality of rim seals, each rim seal disposed between an adjacent pair of disk lugs belonging to the plurality of disk lugs and a pair of adjacent nubs;a cover plate extending across the rotor disk to connect to the rim;a hook extending from the shank of the blade;a seal plate retained alongside the rim by the cover plate and hook; anda cooling path comprising: an opening in the cover plate;a leakage gap between the seal plate and rim; andpassages between the outer diameter surface and the rim seals.