Patent ID: 11927108
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 14:
15. A monolithic bladed rotor of an axial compressor of a gas turbine engine, the monolithic bladed rotor comprising:
a hub having a rotation axis and a radially outer platform relative to the rotation axis; and
a blade integral with the hub and extending radially outwardly from the platform of the hub, the blade including:
an airfoil including a groove formed in an outer surface of the airfoil; and
a root fillet providing a transition between the outer platform of the hub and the outer surface of the airfoil,
wherein:
the root fillet extends from the outer platform to the outer surface of the airfoil;
the groove is disposed radially outward of a runout of the root fillet at an intersection of the root fillet with the airfoil;
the root fillet and the outer surface of the airfoil have a tangent surface continuity at the intersection of the root fillet with the outer surface of the airfoil; and
the outer surface of the airfoil is devoid of another groove disposed radially inwardly of the groove and another groove disposed radially outwardly of the groove.