Abstract: A system includes a gas turbine transition piece. The gas turbine transition piece includes a duct body having a forward end portion and an aft end portion. The duct body defines an enclosure for routing a flow of combustion products from a combustor to a turbine first stage nozzle, and the forward end portion includes a straight portion extending in a downstream direction of the flow. The gas turbine transition piece also includes a first set of dilution holes formed in the forward end portion and arranged in a first pattern configured to reduce emissions. In certain embodiments, the gas turbine transition piece includes a second set of dilution holes formed in the aft end portion and arranged in a second pattern configured to alter the thermal gradient of the combustion gases.

Abstract: According to various embodiments, a system includes a turbine fuel nozzle. The turbine fuel nozzle includes a first fuel passage extending to a downstream mixing region, a first air passage extending from an exterior of the turbine fuel nozzle to the downstream mixing region, and a second fuel passage extending into the first air passage upstream of the downstream mixing region.