US Patent 7631504 Methods and apparatus for assembling gas turbine engines

A combustor assembly is provided. The combustor assembly includes a combustion chamber and at least one transition portion extending downstream from the combustion chamber to facilitate channeling combustion gases from the combustor assembly. The assembly also includes at least one air control system coupled to the at least one transition portion. The air control system including at least one biasing mechanism coupled to a controller to facilitate reducing emissions from the combustor assembly operation.