A fuel nozzle (400) configured to channel fluid towards a combustion chamber (128) defined within a gas turbine engine (100) is provided. The fuel nozzle includes a first hollow tube (420) fabricated from a first material that has a first coefficient of thermal expansion and a second tube (410) fabricated from a second material that has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion, wherein the second tube is coupled within the first tube such that the first tube substantially circumscribes the second tube, wherein the second tube thermally expands approximately at a same rate as the first tube during fuel nozzle operation.