Patent ID: 8572981

Claim:
A fuel injector for use in a combustor section of a gas turbine engine, comprising: a body having a hub that extends circumferentially around a central axis; a plurality of angled vanes for pre-mixing the air and fuel, each vane extending from the hub to an outer annular shroud and are arranged in a circumferential direction on the hub around the central axis, each vane having a root portion located radially near the hub and a tip portion located radially near the outer annular shroud, each vane having a leading edge and a trailing edge extending between the root portion and the tip portion, each vane being angled relative to the central axis to impart a rotational component of motion to incoming air that enters the fuel injector; and at least one concavity disposed on at least one of the plurality of angled vanes, the at least one concavity having a substantially spherical cross-sectional shape and including a discrete fuel hole disposed in an upstream base region of the at least one concavity for injection of fuel into a mainstream of air flowing within the at least one concavity, wherein the at least one concavity provides enhanced fuel-air mixing.