Patent ID: 8136359

Claim:
A fuel nozzle for a gas turbine engine comprising: an inner tubular member coaxial with a centerline, the inner tubular member having a centermost passage; an intermediate tubular member surrounding the inner tubular member and having a corrugated bellows portion, the intermediate tubular member and inner tubular member forming a secondary passage therebetween; an outer tubular member surrounding the intermediate tubular member such that the outer tubular member and the intermediate tubular member form an outer passage therebetween; a plurality of injectors extending radially outward from the outer passage; and, a base coupled to at least the outer tubular member and the intermediate tubular member, the base comprises a plurality of feed holes oriented at an angle relative to the centerline and extending to a surface of the base within the gas turbine combustor for directing compressed air received from within a gas turbine combustor directly to the secondary passage so as to elevate a temperature of the intermediate tubular member to reduce thermal gradients in the fuel nozzle.