The present application and the resultant patent provide a turbine nozzle for a gas turbine engine. The turbine nozzle may include a first nozzle vane, a second nozzle vane, and a platform connecting the first nozzle vane and the second nozzle vane. The platform may include a first cooling passage and a separate second cooling passage defined therein. The first cooling passage may be configured to direct a first flow of cooling fluid in a first direction, and the second cooling passage may be configured to direct a second flow of cooling fluid in a second direction substantially opposite the first direction. The present application and the resultant patent further provide a method for cooling a turbine nozzle of a gas turbine engine.