Patent ID: 11885236
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. An airfoil for a turbine engine, comprising:
an outer wall bounding an interior;
at least one cooling conduit formed in the interior of the airfoil;
a tip rail projecting from the outer wall; and
a three-dimensional plexus of fluidly interconnected cooling passages provided at least partially within the tip rail, the three-dimensional plexus comprising:
an impingement zone fluidly coupled to the at least one cooling conduit;
a lattice portion located radially outward of the impingement zone and at least partially within the tip rail, with the lattice portion fluidly coupled to the impingement zone; and
a set of elongated ejection holes fluidly coupling the lattice portion to at least one outlet on the tip rail.