Transition piece for a gas turbine system

A system, comprising:

• a gas turbine transition piece, comprising:
• a duct body having a forward end portion and an aft end portion, wherein the duct body defines an enclosure for routing a flow of combustion products from a combustor to a turbine first stage nozzle;
• a first set of dilution holes formed in the forward end portion and arranged in a first pattern configured to reduce emissions;
• and
• a second set of dilution holes formed in the aft end portion and arranged in a second pattern configured to alter a thermal gradient of the flow,
• wherein at least some of the dilution holes of both the first and second sets of dilution holes are formed in the duct body at locations defined by selected X, Y, and Z coordinate sets listed in Table 1, wherein the coordinate sets are measured from a zero reference point at a center of an exit plane of the gas turbine transition piece.

A system, comprising:

• a gas turbine transition piece, comprising:
• a duct body having a forward end portion and an aft end portion, wherein the duct body defines an enclosure for routing a flow of combustion products from a combustor to a turbine first stage nozzle;
• a first set of dilution holes formed in the forward end portion and arranged in a first pattern configured to reduce emissions;
• and
• a second set of dilution holes formed in the aft end portion and arranged in a second pattern configured to alter a thermal gradient of the flow,
• wherein the first set of dilution holes comprises 3 dilution holes and the second set of dilution holes comprises 6 dilution holes, and the first and second sets of dilution holes are formed in the duct body at locations defined by selected X, Y, and Z coordinate sets listed in Table 1, wherein the coordinate sets are measured from a zero reference point at a center of an exit plane of the gas turbine transition piece.