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

Claim 0:
1. An integrated bladed rotor of a gas turbine engine, the integrated bladed rotor comprising:
a hub having a rotation axis and a radially outer platform relative to the rotation axis; and
a plurality of blades extending radially outwardly from the platform of the hub, the blades being integrally formed with the hub to define a monolithic component with the hub, each 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, the root fillet defining a concave surface extending from the outer platform of the hub to the outer surface of the airfoil,
wherein:
the groove is disposed radially outward of the root fillet;
the groove is radially spaced apart from 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.