Abstract: A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. When in gas operation, the fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber.

Abstract: A fuel nozzle and gas turbine combustor capable of operating on multiple fuels with reduced carbon build-up to the fuel nozzle and adjacent combustor components is disclosed. The fuel nozzle incorporates a reconfigured gas fuel assembly and mixing tube to eliminate known areas of recirculation. Furthermore, the liquid fuel assembly includes reconfigured spray characteristics to further reduce droplet interaction with the mixing tube.

Abstract: A wear cover for use on a gas turbine transition duct support bracket is disclosed. The wear cover, which is manufactured from a single piece of sheet metal, does not require complex manufacturing processes or tools, thereby reducing component cost. The wear cover comprises first and second leg portions substantially parallel to each other and each generally perpendicular to a third leg portion. Each of the leg portions serve to protect a surface of a support bracket finger from excessive wear associated with frictional contact with mounting blocks of a transition duct. The wear cover is designed to slip onto a support bracket finger through a first opening and is fixed to the finger by a means such as welding.

Abstract: A premix secondary fuel nozzle for use in transferring a flame from a first combustion chamber to a second combustion chamber is disclosed. The secondary fuel nozzle includes multiple fuel circuits, each of which are fully premixed, and neither of which are injected in a manner to directly initiate or support a pilot flame, thereby lowering emissions. Multiple embodiments are disclosed for alternate configurations of a first fuel injector, including an annular manifold and a plurality of radially extending tubes.

Abstract: A premix secondary fuel nozzle for use in transferring a flame from a first combustion chamber to a second combustion chamber is disclosed. The secondary fuel nozzle includes multiple fuel circuits, each of which are fully premixed, and neither of which are injected in a manner to directly initiate or support a pilot flame, thereby lowering emissions. Multiple embodiments are disclosed for alternate configurations of a first fuel injector, including an annular manifold and a plurality of radially extending tubes.

Abstract: A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber. An alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly.

Abstract: A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly. An alternate embodiment includes an additional fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly.

Abstract: A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. When in gas operation, the fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber.

Abstract: A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly. An alternate embodiment includes an additional fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly.

Abstract: A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber. An alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly.

Abstract: A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly.

Abstract: A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly.

Abstract: Interaction between mating gas turbine combustor components due to vibrations and assembly tolerances can cause excessive wear and premature replacement. Typically, wear reduction features, such as hardened materials, are used to minimize the amount of wear or direct such wear to a specific component. The present invention discloses an improved wear reduction device for the interface between a gas turbine combustor transition duct end frame and the turbine inlet. The improved wear reduction device incorporates “L-shaped” wear strip inserts, constructed of a hardened material, and fixed along the sidewalls of the end frame to protect it from wear by the mating turbine inlet seal. The improved wear strip insert provides a cost savings by not requiring costly manufacturing tooling to form the wear strip inserts, unlike previous wear reduction techniques for the same component interface.

Abstract: Interaction between mating gas turbine combustor components due to vibrations and assembly tolerances can cause excessive wear and premature replacement. Typically, wear reduction features, such as hardened materials, are used to minimize the amount of wear or direct such wear to a specific component. The present invention discloses an improved wear reduction device for the interface between a gas turbine combustor transition duct end frame and the turbine inlet. The improved wear reduction device incorporates “L-shaped” wear strip inserts, constructed of a hardened material, and fixed along the sidewalls of the end frame to protect it from wear by the mating turbine inlet seal. The improved wear strip insert provides a cost savings by not requiring costly manufacturing tooling to form the wear strip inserts, unlike previous wear reduction techniques for the same component interface.

Abstract: A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.

Abstract: A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.

Abstract: A method and apparatus for providing air cooling to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes providing an annular air passage surrounding said combustion chamber and venturi where said cooling air enters the combustion chamber/venturi near the aft portion of the combustion chamber passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The structure prevents any channel/passage cooling air from being received into the combustion chamber at the same time introducing the outlet of the cooling air after it has passed over the combustion chamber of the venturi and been heated back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.

Abstract: A fuel nozzle system for use in a combustor utilized in a combustion turbine for reducing nitrogen oxides and other pollutants including an annular fuel distribution manifold separately mounted away from a diffusion nozzle, said annular manifold having a plurality of fuel emitting passages or holes disposed along the downstream side of the manifold, said manifold being mounted in a position away from the diffuser nozzle body to allow air to stream around the manifold on all sides allowing for a thorough mixture of fuel and air around the annular manifold for better premixing in the combustion chamber. In an alternate embodiment, the diffusion nozzle is replaced by a pilot flame nozzle that is supplied with both air and fuel through a premix air and fuel chamber to a pilot flame nozzle which is used to sustain combustion in the secondary chamber. The use of a pilot flame nozzle that has a fuel and air mixture is believed to reduced NOx emissions.

Abstract: A multiple directional axes structural support system for use as the aft end mount for a gas turbine transition duct to a turbine inlet is disclosed. The mounting system is configured to withstand high temperature gradients and mechanical loads associated with gas turbine environments while allowing multiple axes adjustment and interface capability between the transition duct and the turbine inlet casing. A spherical ball joint allows for rotation about multiple (three) axes to compensate for relative thermal growth, manufacturing tolerances, and assembly tolerances between mating surfaces. The ball joint is held in place by fitted spacers, bosses, and a through-bolt, that when torqued will dampen out unwanted vibrations in the multi-axis mounting system.

Abstract: An igniter assembly for a combustor of a gas turbine, the combustor being of a type including a case and a liner within said case, the assembly comprising an igniter including an elongate body having a first end, a second end, and a mounting feature intermediate said first and second ends, and the mounting feature includes a semi-hemispherical surface and an electrode extending through the body, and a base having an internal cavity with a first internal land, a second internal land opposite the first internal land, first seal A means in sealing contact with the first internal land, and biasing means, such as a spring, in contact with the second internal land and said mounting feature. The mounting feature is located within the cavity, the semi-hemispherical surface is proximate the first seal means, and the biasing means urges the semi-hemispherical surface into sealing contact with the first seal means to prevent the leakage of air therethrough.