Patent ID: 9447975
Filing Date: 2016-09-20
CPC Classification: F23C,F23R

Claim Text:
1. A combustor for use with a gas turbine engine, comprising: a plurality of micro-mixer fuel nozzles; and a fuel injection system comprising: a center hub, a plurality of support struts, and a plurality of aerodynamic fuel flanges; wherein the center hub is in communication with the plurality of support struts for providing a flow of fuel through the center hub and through the plurality of support struts to the plurality of micro-mixer fuel nozzles; wherein the plurality of support struts extend radially outward from the center hub, supporting the plurality of fuel nozzles and providing the flow of fuel therethrough; and wherein the plurality of aerodynamic fuel flanges connect and provide an aerodynamic transition between the plurality of micro-mixer fuel nozzles and the plurality of support struts.