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

Claim 17:
18. A gas turbine engine comprising:
an axial compressor for compressing air, the compressor defining a gas path for conveying the air, the compressor including a monolithic integrated bladed rotor including:
a hub having a rotation axis and a radially outer platform defining part of the gas path; and
a plurality of blades extending radially outwardly from the platform of the hub and into the gas path, the blades being integrally formed with the hub, two or more of the blades each including:
an airfoil including a groove formed in an outer surface of the airfoil, a majority of the groove being parallel to an expected flow direction of the air interacting with 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;

a combustor in which the air compressed by the compressor is mixed with fuel and ignited to generate a stream of combustion gas; and
a turbine operatively connected to the combustor for extracting energy from the combustion gas.