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A method enables a rotor assembly for a gas turbine engine to be designed. The method comprises providing a plurality of rotor blades that each include a dovetail that includes a pair of blade pressure faces and a dovetail bottom that extends arcuately between the pair of blade pressure faces, provi

A method enables a rotor assembly for a gas turbine engine to be designed. The method comprises providing a plurality of rotor blades that each include a dovetail that includes a pair of blade pressure faces and a dovetail bottom that extends arcuately between the pair of blade pressure faces, providing at least one of a rotor disk and a rotor spool that includes a circumferential dovetail slot that is sized to receive the plurality of rotor blades therein, and coupling the plurality of rotor blades to the at least one of a rotor disk and a rotor spool using each respective rotor blade dovetail.

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1. A method for designing a rotor assembly for a gas turbine engine, said method comprising:providing a plurality of rotor blades that each include a dovetail that includes a pair of blade pressure faces and a dovetail bottom that extends arcuately between the pair of blade pressure faces, wherein e

1. A method for designing a rotor assembly for a gas turbine engine, said method comprising:providing a plurality of rotor blades that each include a dovetail that includes a pair of blade pressure faces and a dovetail bottom that extends arcuately between the pair of blade pressure faces, wherein each dovetail bottom is funicular-shaped;providing at least one of a rotor disk and a rotor spool that includes a circumferential dovetail slot that is sized to receive the plurality of rotor blades therein; andcoupling the plurality of rotor blades to the at least one of a rotor disk and a rotor spool using each respective rotor blade dovetail.2. A method in accordance with claim 1 wherein coupling the plurality of rotor blades to the at least one of a rotor disk and a rotor spool using each respective rotor blade dovetail further comprises coupling the plurality of rotor blades to the at least one of a rotor disk and a rotor spool to facilitate minimizing bending stresses induced to each respective rotor blade during engine operation.3. A method in accordance with claim 1 wherein coupling the plurality of rotor blades to the at least one of a rotor disk and a rotor spool using each respective rotor blade dovetail further comprises coupling the plurality of rotor blades to the at least one of a rotor disk and a rotor spool to facilitate extending a useful life of the at least one of a rotor disk and a rotor spool.4. A method in accordance with claim 1 wherein providing a plurality of rotor blades that each include a dovetail that includes a pair of blade pressure faces further comprises providing a plurality of rotor blades that include a pair of symmetrically opposed dovetail blade pressure faces.5. A dovetail assembly for a gas turbine engine, said dovetail assembly comprising:a plurality of rotor blades, each said rotor blade comprising a dovetail comprising a dovetail bottom and at least a pair of blade pressure faces, said dovetail bottom extends arcuately between said at least a pair of blade pressure faces, wherein said rotor blade dovetail bottom is funicular-shaped; anda disk comprising a circumferential dovetail slot sized to receive said plurality of rotor blade dovetails, said dovetail slot defined by at least one pair of opposing disk tangs.6. A dovetail assembly in accordance with claim 5 wherein each said rotor blade comprises a pressure side and a suction side, said dovetail bottom extends between said rotor blade pressure and suction sides.7. A dovetail assembly in accordance with claim 5 wherein each said rotor blade dovetail bottom facilitates minimizing bending stresses induced to each said respective rotor blade during engine operation.8. A dovetail assembly in accordance with claim 5 wherein each said rotor blade dovetail bottom facilitates reducing an overall weight of the gas turbine engine.9. A dovetail assembly in accordance with claim 5 wherein each said rotor blade dovetail bottom facilitates extending a useful life of said disk.10. A dovetail assembly in accordance with claim 5 wherein said rotor blade at least a pair of blade pressure faces are symmetrically opposed.11. A gas turbine engine comprising a rotor assembly comprising a plurality of rotor blades coupled to a rotor disk, said plurality of rotor blades each comprising an airfoil, a dovetail, and a platform extending therebetween, each said dovetail comprises at least a pair of blade pressure faces and a dovetail bottom extending arcuately therebetween, wherein each said rotor blade dovetail bottom is funicular-shaped, said rotor disk comprising a circumferential dovetail slot sized to receive said plurality of rotor blade dovetails.12. A gas turbine engine in accordance with claim 11 wherein each said rotor blade comprises a pressure side and a suction side, said dovetail bottom extends between said rotor blade pressure and suction sides.13. A gas turbine engine in accordance with claim 12 wherein each said rotor blade at least a pair of blade pressure faces are symmetrically opposed.14. A gas turbine engine in accordance with claim 12 wherein each said rotor blade dovetail bottom is configured to facilitate minimizing stresses induced to each said rotor blade during engine operation.15. A gas turbine engine in accordance with claim 12 wherein each said rotor blade dovetail bottom facilitates extending a useful life of said disk.16. A gas turbine engine in accordance with claim 12 wherein each said rotor blade dovetail bottom facilitates reducing an overall weight of said gas turbine engine.17. A gas turbine engine in accordance with claim 12 wherein said rotor assembly is a compressor rotor assembly.