Abstract: According to one aspect of the invention, a fuel nozzle assembly for a turbine includes an inner conduit and a flange coupled to the inner conduit thereby forming a chamber for flow of a gas fuel. In addition, the flange includes a diaphragm member coupled to the inner conduit, the diaphragm member being configured to flex in response to relative movement between the inner conduit and the flange.

Abstract: An endcover assembly for a turbine combustor adapted to support one or more combustor nozzles includes a substantially flat plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel passage extends through the substantially flat plate. A fuel manifold porting block is secured to the opposite side of the flat plate with at least one port aligned with the at least one passage. A fuel restrictor insert formed with multiple flow orifices is located between the flat plate and the fuel manifold porting block in alignment with the at least one fuel passage and the at least one port.

Abstract: An end cover assembly is provided in combination with a gas turbine combustor for capping a back end of a combustion chamber. The end cover assembly includes an end cover plate securable to the back end of the combustion chamber, and a monolith block secured to the end cover plate. The end cover plate is constructed without welded gas passage plates and without brazed flow passage inserts and includes fuel channels therethrough, where the fuel channels are sized and positioned to interact with fuel nozzle inlet ports. The monolith block includes internal fuel gas passages positioned relative to the fuel channels in the end cover plate to commute fuel gas to the fuel channels of the end cover plate.

Abstract: A cooling circuit for a fuel nozzle in a gas turbine includes an end cap cavity receiving passive purge flow from a compressor of the turbine, and fuel nozzle swozzles disposed in a swozzle shroud that impart swirl to incoming fuel and air. Purge slots are formed in the swozzle shroud and through the fuel nozzle swozzles in fluid communication with the end cap cavity. The purge slots are positioned upstream of a quat fuel injection passage, and the passive purge flow enters fuel nozzle tip cavities of the fuel nozzle to provide tip cooling and tip purge volume without mixing the passive purge flow with quat fuel.

Abstract: A method of assembling a fuel nozzle assembly for a gas turbine engine having a natural operating frequency includes providing a flange and providing a premix tube. The flange is fabricated from a first alloy such that the flange is configured to exhibit a first frequency that is different than the natural operating frequency of the gas turbine engine. The premix tube is fabricated from a second alloy such that the premix tube is configured to exhibit a second frequency that is different from the natural operating frequency of the gas turbine engine. The premix tube is coupled to the flange.

Abstract: A fuel nozzle assembly for a gas turbine engine includes a flange and a pre-mix tube. The flange includes a first end that is configured to couple to an end cover of the combustor, and a second end that is opposite said first end. The pre-mix tube is coupled at a first end to the flange second end. The flange and the pre-mix tube are fabricated to operate at a natural frequency that is different from an operating frequency of the gas turbine engine.

Abstract: In an embodiment, a system includes an end cover and a liquid cartridge. The liquid cartridge is configured to mount in a fuel nozzle of a turbine engine, wherein the liquid cartridge comprises a one piece flange configured to couple to the end cover, wherein the flange comprises a water inlet, an air inlet, and a fuel inlet.

Abstract: A fuel nozzle for use with a combustion chamber defined within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a swirler assembly and a burner tube that is coupled to a support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation.

Abstract: A fuel nozzle configured to channel fluid toward a combustion chamber within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a first hollow tube fabricated from a first material that has a first coefficient of thermal expansion and a second tube fabricated from a second material that has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The second tube is coupled within the first tube such that the first tube substantially circumscribes the second tube, and the second tube thermally expands approximately at a same rate as the first tube during fuel nozzle operation.

Abstract: A system, in one embodiment, includes a fuel nozzle tip retainer that includes a structural member having a geometry that blocks a tip insert from moving axially downstream of a fuel nozzle.