General Electric Company

Stephen Robert Thomas

Geoffrey David Myers

Scott Robert Simmons

Wei A Chen

Donald Mark Bailey

Vijay Kumar Turaga

David Martin Johnson

Scott Arthur Day

Mahesh Bathina

Gerardo F Varillas

Stephen Kent Fulcher

Madanmohan Manoharan

Mustafa Ahmed Abdullah

In one or more of the inventive aspects, when a gas turbine system of a power plant operates at part load, a moisture content of fuel gas provided to the gas turbine system may be controlled so as to minimize combustion dynamics and/or to comply with emission requirements. The fuel gas moisture content may be controlled by modulating a flow of heated water to a fuel moisturizer. By using heated water from a heat recovery steam generator to moisturize the fuel gas, heat energy from the water may be transferred to the fuel gas, and the overall mass flow may be enhanced to thereby increase overall combined cycle efficiency.

Variable fuel gas moisture control for gas turbine combustor

A gas turbine system includes a fuel nozzle. The fuel nozzle includes a first fluid conduit defining a first fuel passage, a second fluid conduit defining a second fuel passage, and a third fluid conduit defining an oxidant passage. A first plurality of orifices is disposed along the first fluid conduit and is configured to fluidly couple the first fuel passage to the oxidant passage. A second plurality of orifices is disposed on the third fluid conduit and is configured to fluidly couple the second fuel passage to the oxidant passage. A first diameter of the first plurality of orifices is less than a second diameter of the second plurality of orifices.

Fuel nozzle for gas turbine

A turbomachine is provided and includes a compressor to compress inlet gas to produce compressed gas, a combustor coupled to the compressor in which the compressed gas is combusted along with a first fuel and/or a second fuel to produce a fluid flow, a turbine coupled to the combustor through which the fluid flow is directed for power and/or electricity generation and first and second supply circuits to supply the first fuel and the second fuel to the combustor, respectively. The first and second supply circuits are operable to enable transfers between operations associated with the first fuel and the second fuel being respectively supplied to the combustor at a high load.

Turbomachine and method of operating a turbomachine to perform a fuel change over at a high load

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.

Fuel nozzle assembly for use with a gas turbine engine and method of assembling same

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.

Fuel nozzle detachable burner tube with baffle plate assembly

A method for assembling a combustor assembly is provided. The method includes providing at least one sleeve having a plurality of inlets, and coupling at least one airfoil to at least one of the plurality of inlets defined in the at least one sleeve. The airfoil includes a pair of opposing sidewalls coupled together at a leading edge and at a trailing edge and at least one channel is formed between the airfoil sidewalls for channeling cooling air. The cooling air is directed to flow substantially perpendicularly to a direction of air flowing around the airfoil in a portion of the combustor assembly that is to be cooled. The method also includes coupling the at least one sleeve around the portion of the combustor assembly to be cooled. Also provided are a sleeve and an airfoil for use in a combustor assembly.

Airfoil, sleeve, and method for assembling a combustor assembly

A method for cooling a combustor assembly having a cooling passage. The method includes providing at least one thimble including an inner surface that defines a first opening, a second opening that is downstream from the first opening, and a flow channel that extends between the first opening and the second opening. The flow channel has a converging portion and a recovery portion that is downstream from the converging portion. The method also includes inserting the at least one thimble into at least one inlet that is defined in at least one sleeve such that cooling air is discharged from the flow channel into the cooling passage.

Thimble, sleeve, and method for cooling a combustor assembly

A turbomachine includes a compressor, a turbine, and a combustor operatively connected to the turbine. The turbomachine further includes a cap member mounted to the combustor. The cap member includes a first surface and a second surface. A combustion chamber is defined within the combustor. An injection nozzle is supported at the second surface of the cap member. The injection nozzle includes a first end that extends through an inner flow path to a second end. The first end is configured to receive an amount of a first fluid and the second end is configured to receive an amount of a second fluid. A mixture of the first and second fluids is discharged from the second end of the injection nozzle.

Fuel nozzle for a turbomachine

A fuel nozzle having a dedicated circuit to cool the diffusion tip with lower part count and reduced complexity. More specifically, the proposed design uses an independent circuit to cool the tip with diffusion fuel or purge air. An impingement plate may be provided to augment the cooling effect.

Growing community of inventors

Simpsonville, SC, United States of America

Stephen Robert Thomas