Compressor rotor configuration

摘要

A gas turbine engine rotor assembly including a rotor (12) having a radially outer rim (18) with an outer surface (204) shaped to reduce circumferential rim stress concentration between each blade (24) and the rim. Additionally, the shape of the outer surface directs air flow away from an interface between a blade and the rim to reduce aerodynamic performance losses between the rim and blades. In an exemplary embodiment, the outer surface of the rim has a concave shape (210) between adjacent blades with apexes located at interfaces between the blades and the rim. <IMAGE> <IMAGE>