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A gas turbine engine system includes a disk and an airfoil. The disk includes a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending radially outward from the second rail. The airfoil is engaged with the retention slot, and includes a platform

A gas turbine engine system includes a disk and an airfoil. The disk includes a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending radially outward from the second rail. The airfoil is engaged with the retention slot, and includes a platform with an upstream angled portion, a downstream angled portion, and a notch defined in the platform. The ridge of the disk extends at least partially into the notch of the platform.

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1. A gas turbine engine system comprising: a disk having a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending radially outward from the second rail;an airfoil engaged with the retention slot, the airfoil having a platform with an upstream an

1. A gas turbine engine system comprising: a disk having a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending radially outward from the second rail;an airfoil engaged with the retention slot, the airfoil having a platform with an upstream angled portion, a downstream angled portion, and a notch defined in the platform, wherein the ridge of the disk extends at least partially into the notch of the platform;a ladder seal system position at least partially between the platform of the airfoil and the disk, wherein the ladder seal system comprises a plurality of arcuate ladder seal segments; andthe ladder seal is arranged to conform to the platform angled portions, in an uninstalled state. 2. The system of claim 1, wherein the upstream angled portion is arranged at an angle θU that is acute relative to a tangential direction, wherein the downstream angled portion is arranged at an angle θD that is acute relative to a tangential direction, and wherein both the upstream and downstream angled portions angle radially outward toward an adjacent edge. 3. The system of claim 2, wherein the angle θU is in a range of approximately 11.7° to 19.1°, and wherein the angle θD is in the range of approximately 11.3° to 18.5°. 4. The system of claim 2, wherein the angle θU is approximately 15°. 5. The system of claim 2, wherein the angle θD is approximately 15°. 6. The system of claim 1, wherein the first rail is located upstream of the second rail, and wherein the retention slot comprises a circumferential slot. 7. The system of claim 1, wherein the ridge extends circumferentially. 8. The system of claim 7, wherein the ridge extends circumferentially about the entire disk. 9. The system of claim 7, wherein the notch extends circumferentially and is located at or near a trailing edge of the platform. 10. The system of claim 1, wherein the ridge has a substantially rectangular cross-sectional shape. 11. The system of claim 10, wherein the notch has a generally rectangular cross-sectional shape complementary to the substantially rectangular cross-sectional shape of the ridge. 12. The system of claim 1, wherein the notch has a shape that is complementary to a shape of the ridge. 13. The system of claim 1, wherein the ridge is integrally and monolithically formed with the disk. 14. A method for making a gas turbine engine system, the method comprising: defining a circumferentially-extending notch in an airfoil platform;said platform having an upstream angled portion and a downstream angled portion defined in the platform;engaging the airfoil with a slot in a disk;positioning a circumferentially extending ridge at least partially within the notch in the radial direction;preventing engagement of the airfoil with the slot in the disk in an incorrect orientation;positioning an arcuate ladder seal segment partially between the platform of the airfoil and the disk; andsaid aruate ladder seal segment angle to conform to the platform in an uninstalled state. 15. A gas turbine engine system comprising: a rotor disk having an upstream rail, a downstream rail, a circumferential retention slot located between the upstream and downstream rails, and a circumferential ridge extending radially outward from the downstream rail;an airfoil engaged with the circumferential retention slot, the airfoil having a platform with an upstream angled portion, a downstream angled portion and a notch defined in the platform, wherein the circumferential ridge of the rotor disk extends at least partially into the notch, and wherein both the upstream and downstream angled portions angle radially outward toward an adjacent edge; andan arcuate ladder seal segment positioned between the rotor disk and the platform of the airfoil, the ladder seal segment angled to conform to the platform in an uninstalled state. 16. The system of claim 15, wherein the upstream angled portion is arranged at an angle θU in a range of approximately 11.7° to 19.1°, and wherein the downstream angled portion is arranged at an angle θD in a range of approximately 11.3° to 18.5°. 17. The system of claim 15, wherein the ridge has a substantially rectangular cross-sectional shape, and wherein the notch has a generally rectangular cross-sectional shape complementary to the substantially rectangular cross-sectional shape of the ridge. 18. The system of claim 15 and further comprising: said arcuate first ladder seal segment including: a central portion;an upstream flange adjoining the central portion, wherein the upstream flange has a width DU and is arranged at an angle that complement an angle of an upstream portion of the platform of the airfoil; anda downstream flange adjoining the central portion opposite the upstream flange, wherein the downstream flange has a width DD and is arranged at an angle that complement an angle of a downstream portion of the platform of the airfoil, and wherein the width DU is not equal to the width DD.