Patent ID: 11939880
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 13:
14. An airfoil assembly for a turbine engine, comprising:
an airfoil having an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge; and
a platform extending along an axial direction between a forward edge and an aft edge, the airfoil extending radially from the platform, and with the platform having a contoured flow surface comprising:
a trough extending along at least a portion of the pressure side and having a local minimum proximate the leading edge; and
a bulge having a local maximum spaced from the outer wall and extending along at least a portion of the suction side;

wherein each of the bulge and the trough are positioned aft of the forward edge of the platform.