General Electric Company

Roy M Washam

Masayoshi Kuwata

Lewis Berkley Davis, Jr

Jennifer Waslo

William T Bechtel, Ii

Gilbert Otto Kraemer

Baifang Zuo

Hasan Ul Karim

Krishna Kumar Venkataraman

Charles E Steber

Mohan Krishna Bobba

Chunyang Wu

Jason Charles Terry

John Anthony Conchieri

Elias Marquez

Robert A Corr, Ii

Bernard A Thibault, Jr

Luiz C V Fernandes

A system for pre-heating a working fluid within a combustor includes a compressor for providing the working fluid to the combustor. An outer casing is disposed downstream from the compressor. The outer casing at least partially defines a high pressure plenum that at least partially surrounds the combustor. A combustion chamber is defined within the combustor downstream from the high pressure plenum. A catalytic combustor is disposed within the high pressure plenum upstream from the combustion chamber so as to provide thermal energy to the working fluid upstream from the combustion chamber.

Catalytic combustion air heating system

A system includes a turbomachine including a first chamber configured to contain a first fluid and a second chamber configured to contain a second fluid. The turbomachine also includes a barrier disposed between the first and second chambers. The barrier is configured to separate the first fluid and the second fluid. Additionally, the barrier includes a first surface facing the first chamber and a second surface facing the second chamber. The turbomachine also includes an orifice extending from the first chamber to the second chamber. The orifice defines a fluid passageway. Additionally, the turbomachine includes a tube including a first end and a second end. The first end is coupled to the first surface and is disposed about a perimeter of the orifice. The tube is configured to at least partially contain the second fluid.

System and method for separating fluids

A combustor includes an end cap having a perforated downstream plate and a combustion chamber downstream of the downstream plate. A plenum is in fluid communication with the downstream plate and supplies a cooling medium to the combustion chamber through the perforations in the downstream plate. A method for cooling a combustor includes flowing a cooling medium into a combustor end cap and impinging the cooling medium on a downstream plate in the combustor end cap. The method further includes flowing the cooling medium into a combustion chamber through perforations in the downstream plate.

Apparatus and method for cooling a combustor cap

A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.

Late lean injection system configuration

A system includes a fuel nozzle for a turbine engine that includes a tapered central body located at an interior base of the fuel nozzle, an air swirler, and a fuel port in the tapered central body, separate from the air swirler.

System and method for air-fuel mixing in gas turbines

The burner assembly includes a flow body 12 having a central liquid fuel injection nozzle 14, inner and outer concentric passages 24 and 26, respectively, and a flow duct comprising a venturi downstream of the liquid injection nozzle. The inner passage 24 communicates air and gaseous fuel into the flow duct 16. Swirlers 30 and 38 are provided at the exit ends of the inner and outer passages, respectively, to create counterrotating flows which form a shear layer at the exit of the burner assembly body. The extent of the flow duct 16 facilitates liquid fuel atomization and vaporization, while affording sufficient time for gaseous fuel/air pre-mixing. The arrangement creates a recirculation zone 40 and a shear layer 42 at the exhaust of the burner assembly body which affords flame stabilization.

Dual-fuel pre-mixing burner assembly

An improved gas turbine combustor is provided which reduces nitric oxide emissions through premixing of the fuel gas and air and feeding the mixture through a venturi, providing an air cooled passage around the venturi, and extending the passage downstream toward the combustion zone to optimize the stability of the combustion and reduce NO.sub.x and CO emissions.

Low NO.sub.x emission in gas turbine system

A combustor includes inner and outer arrays of generally Vee-shaped, radially extending, circumferentially spaced gutters canted in a circumferential direction relative to one another to produce isolated concentric counter-rotating circumferentially directed flows downstream of the gutters. A lean premixed combustion mode is used at baseload operations. At non-baseload operations, particularly low-load operating conditions, a diffusion combustion mode is employed by direct fuel injection into air supplied to one of the isolated flow fields, preferably the radially inner flow field, to produce a stabilized, locally hotter flame, resulting in higher combustion efficiency and lower emissions than otherwise using a lean premixed combustion mode at the non-baseload operating conditions.

Swirl gutters for isolating flow fields for combustion enhancement at

A gas turbine combustor is provided with a premixer in which an oxidant and fuel is mixed and caused to flow to the combustion zone past two or more arrays of convex members positioned transverse or canted to the flow. The convex members introduce turbulence and include a plurality of openings to introduce one or more additional fuels into the premixed oxidant and fuel flow. Parallel, annular and radial arrays, or combinations thereof, may be provided. The downstream array is V-shaped in cross section and provides flame holding capability while the upstream array principally provides additional mixing of fuel and oxidant.

Two stage V-gutter fuel injection mixer

It has been found that in a dry low NOx combustor of the type having an upstream combustion chamber and a downstream combustion chamber interconnected by a venturi section, the fuel-air ratio and uniform fuel-air mixing can be improved by providing an annular shield upstream of the venturi region. The shield is impingement cooled through the venturi and provision is made for dumping cooling air farther downsteam in the downstream combustion chamber. With the aforesaid improvements in mind, the upstream combustion chamber is provided with first and second inner liners which are also impringement cooled an which provide combustion air farther upstream into the upstream combustion chamber to further improve fuel-air mixing and to maintain the desired fuel-air ratio.

Impingement cooled liner for dry low NOx venturi combustor

A dual mode, dual stage low NOx combustor, includes a primary combustion chamber and a secondary combustion chamber separated by a throat region of reduced diameter. Fuel is input into the primary combustors by an annular array of diffusion type nozzles whereas in accordance with the invention fuel is input into the secondary combustor by a central combination premix and diffusion nozzle.

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Schenectady, NY, United States of America

Roy M Washam