A fuel nozzle for a combustor of a gas turbine engine

A fuel nozzle (70) for a gas turbine (10) generally includes a main body (72) having an upstream end (78) axially separated from a downstream end (80). The main body at least partially defines a fuel supply passage (86) that extends through the upstream end and at least partially through the main body. A fuel distribution manifold (74) is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages (92) that extend through the fuel distribution manifold. A plurality of fuel injection ports (96) defines a flow path (98) between the fuel supply passage and each of the plurality of axially extending passages.