General Electric Company

Exxonmobil Upstream Research Company

Sergey Anatolievich Meshkov

Willy Steve Ziminsky

Almaz Kamilevich Valeev

Sergey Adolfovich Oskin

Lewis Berkley Davis, Jr

Christopher Edward Wolfe

Kevin Weston McMahan

Ronald James Chila

Vitali Victor Lissianski

Mark Allan Hadley

Joseph Vincent Citeno

Borys Shershnyov

Joel Meador Hall

Igor Petrovich Sidko

Leonid Yul'evich Ginesin

Mathilde Bieber

Vitaly Vladimirovich Kuzminov

Sergey Konstantinovich Yerokhin

Dmitry Alexandrovitch Lysenko

Valery Alexandrovich Mitrofanov

Joseph Citeno

Almaz Valeev

A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine combustor also includes a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and an end plate having at least one port coupled to the exhaust gas path or the oxidant path. The head end chamber is disposed axially between the cap and the end plate.

System and method for a turbine combustor

A system and method for generating an exhaust syngas are disclosed. The system includes a mixing unit, a heat exchanger, and an engine. The mixing unit is configured to mix a hydrocarbon fuel, an oxidant, and water to generate a fuel mixture. The heat exchanger is coupled to the mixing unit and is configured to receive the fuel mixture from the mixing unit, evaporate the water by heating the fuel mixture using a hot fluid, and generate a heated fuel mixture. The engine is coupled to the heat exchanger and is configured to receive the heated fuel mixture from the heat exchanger and generate an exhaust syngas by partially combusting the heated fuel mixture.

System for generating syngas and an associated method thereof

An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.

Integrated combustor and stage 1 nozzle in a gas turbine and method

A turbomachine combustor portion includes a combustion chamber. A center injection nozzle is arranged within the combustion chamber and includes a center nozzle inlet and a center nozzle outlet. An outer premixed injection nozzle is positioned radially outward of the center injection nozzle and includes an outer nozzle inlet and an outer nozzle outlet that is arranged upstream of the center nozzle outlet. A late lean injector is positioned downstream of the center nozzle and the outer premixed nozzle. The combustor portion includes a first combustion zone arranged downstream of the outer nozzle outlet, a second combustion zone arranged downstream of the center nozzle outlet, and a third combustion zone arranged further downstream of the center nozzle outlet. The center injection nozzle, outer premixed injection nozzle, and late lean injector are selectively operated to establish a combustion flame front in the first, second, and third combustion zones.

Combustor portion for a turbomachine and method of operating a turbomachine

A combustor includes an end cover and a combustion chamber downstream of the end cover. The combustor further includes nozzles disposed radially in the end cover and a shroud surrounding at least one of the nozzles and extending downstream into the combustion chamber. The shroud includes an inner wall surface and an outer wall surface. A method for operating a combustor includes flowing compressed working fluid through nozzles into a combustion chamber, flowing fuel through each nozzle in a first subset of the nozzles into the combustion chamber, and igniting the fuel from each nozzle in the first subset of nozzles in the combustion chamber. In addition, the method includes extending into the combustion chamber a separate shroud around each nozzle in a second subset of the nozzles and isolating fuel to each nozzle in the second subset of nozzles.

Apparatus and method for a combustor

A fuel nozzle for a turbine is disclosed. The fuel nozzle includes a housing, a plurality of fuel passages disposed within the housing, and a plurality of air passages disposed within the housing. A total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages.

Turbine fuel delivery apparatus and system

Growing community of inventors

Moscow, Russia

Sergey Anatolievich Meshkov