| 摘要 |
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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