The present invention provides a gas turbine combustor that has a fuel injection nozzle using a fluid other than liquid fuel to atomize the liquid fuel and that can suppress a reduction in power generation efficiency resulting from a heat loss while promoting the atomization of the liquid fuel. The gas turbine combustor is adapted to mix liquid fuel with combustion air led from a compressor, burn the mixture, and supply combustion gas generated to a gas turbine. The gas turbine combustor includes a fuel injection nozzle that atomizes the liquid fuel into fine liquid droplets. The fuel injection nozzle includes a first system adapted to supply the liquid fuel and a second system adapted to supply a fluid for atomizing the liquid fuel. Low-boiling liquid fuel is supplied to the second system as the fluid. The second system is adapted to heat and supply the low-boiling liquid fuel.

Gas turbine combustor

A hybrid structure that combines characteristics of the DACRS and Swozzle burners to provide the high mixing ability of an axial flowing counter rotating vane swirler with good dynamic flame stability characteristics of a bluff center body.

Burner tube and method for mixing air and gas in a gas turbine engine

An annular combustor (100) for a gas turbine has a combustion chamber having an interior volume that, in longitudinal section, includes a forward volume (V 1 ), an intermediate volume (V 2 ) and an aft volume (V 3 ). The forward volume (V 1 ) represents from about 30% to about 40% of the combustor interior volume, the intermediate volume (V 2 ) represents from about 10% to about 20% of the combustor interior volume, and the aft volume (V 3 ) represents from about 40% to about 60% of the combustor interior volume.

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A mixer for use in a combustion chamber of a gas turbine engine. The mixer includes a first fuel injector adapted for dispensing droplets of fuel during ignition and low power settings of the engine and a pilot swirler positioned upstream from the first fuel injector. The pilot swirler has a plurality of vanes for swirling air to mix air and the droplets of fuel. The mixer also includes a second fuel injector adapted for dispensing droplets of fuel during high power settings of the engine and a main swirler adjacent the pilot swirler and upstream from the second fuel injector. The main swirler has a plurality of vanes for swirling air traveling through the main swirler to mix air and the droplets of fuel dispensed by the second fuel injector. The mixer also includes a barrier positioned between the pilot swirler and main swirler for separating the first fuel injector from the second fuel injector.

Multiple annular swirler

A mixer assembly for use in a combustion chamber of a gas turbine engine. The assembly includes a pilot mixer and a main mixer. The pilot mixer includes an annular pilot housing having a hollow interior, a pilot fuel nozzle mounted in the housing adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, and a plurality of concentrically mounted axial swirlers positioned upstream from the pilot fuel nozzle. Each of the swirlers has a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the pilot fuel nozzle. The main mixer includes a main housing surrounding the pilot housing defining an annular cavity, a plurality of fuel injection ports for introducing fuel into the cavity, and a swirler positioned upstream from the plurality of fuel injection ports having a plurality of vanes for swirling air traveling through the swirler to mix air and the droplets of fuel dispensed by the fuel injection ports.

Multiple annular combustion chamber swirler having atomizing pilot

A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages for pre-mixing primary fuel and air to be supplied to the primary combustion zone. Each of the pre-mixing passages has a circumferential array of swirl vanes. A plurality of primary fuel tube assemblies extend through both pre-mixing passages, with each primary fuel tube assembly located between a pair of swirl vanes. Each primary fuel tube assembly is comprised of two tubular members. The first member supplies fuel to the first pre-mixing passage, while the second member, which extends through the first member, supplies fuel to the second pre-mixing passage. An annular fuel manifold is divided into first and second chambers by a circumferentially extending baffle. The proximal end of the first member is attached to the manifold itself while the proximal end of the second member is attached to the baffle. The distal end of the first member is attached directly to the second member at around its mid-point. The inlets of the first and second members are in flow communication with the first and second manifold chambers, respectively. Control valves separately regulate the flow of fuel to the two chambers and, therefore, to the two members of the fuel tube assemblies, thereby allowing the flow of fuel to the first and second pre-mixing passages to be separately controlled.

Combustor with two stage primary fuel tube with concentric members and flow regulating

A combustor for a gas turbine having first and second passages for pre-mixing primary fuel and air supplied to a primary combustion zone. The flow of fuel to the first and second pre-mixing passages is separately regulated using a single annular fuel distribution ring having first and second row of fuel discharge ports. The interior portion of the fuel distribution ring is divided by a baffle into first and second fuel distribution manifolds and is located upstream of the inlets to the two pre-mixing passages. The annular fuel distribution ring is supplied with fuel by an annular fuel supply manifold, the interior portion of which is divided by a baffle into first and second fuel supply manifolds. A first flow of fuel is regulated by a first control valve and directed to the first fuel supply manifold, from which the fuel is distributed to first fuel supply tubes that direct it to the first fuel distribution manifold. From the first fuel distribution manifold, the first flow of fuel is distributed to the first row of fuel discharge ports, which direct it into the first pre-mixing passage. A second flow of fuel is regulated by a second control valve and directed to the second fuel supply manifold, from which the fuel is distributed to second fuel supply tubes that direct it to the second fuel distribution manifold. From the second fuel distribution manifold, the second flow of fuel is distributed to the second row of fuel discharge ports, which direct it into the second pre-mixing passage.

Combustor with two stage primary fuel assembly

A method of converting a steam cooled transition (22) to an air cooled transition in a gas turbine having a compressor (13) in fluid communication with a combustor (12), a turbine section in fluid communication with the combustor (12), the transition (22) disposed in a combustor shell (24) and having a cooling circuit (38) connecting a steam outlet and a steam inlet and wherein hot gas flows form the combustor (12) through the transition (22) and to the turbine section, includes forming an air outlet (44) in the transition (22) in fluid communication with the cooling circuit (38) and providing for an air inlet in the transition (22) in fluid communication with the cooling circuit.

Gas turbine combustor transition

Combustor with independently controllable fuel flow to different stages

A combustor for a combustion turbine system that minimizes the amount of compressed air needed for cooling, and a method for such cooling, is disclosed. The combustor has a primary liner that is in direct contact with hot gas within the combustion zone. A cooling air passage surrounds and removes heat from the primary liner in three ways. First, a portion of the cooling air flows through effusion cooling holes in a portion of the liner. Second, another portion of the cooling air flows across cooling fins disposed on an outer surface of the liner. Third, yet another portion of the cooling air is directed to impinge against the liner by a baffle assembly that is disposed within the cooling air passage.

Graydon Lane Whidden

Papers

Combustor with two stage primary fuel tube with concentric members and flow regulating

Combustor with two stage primary fuel assembly

Gas turbine combustor transition

Combustor with independently controllable fuel flow to different stages

An apparatus for cooling a combuster, and a method of same