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

Methods and systems for low emission power generation in hydrocarbon recovery processes are provided. One system includes integrated pressure maintenance and miscible flood systems with low emission power generation. An alternative system provides for low emission power generation, carbon sequestration, enhanced oil recovery (EOR), or carbon dioxide sales using a hot gas expander and external combustor. Another alternative system provides for low emission power generation using a gas power turbine to compress air in the inlet compressor and generate power using hot carbon dioxide laden gas in the expander. Other efficiencies may be gained by incorporating heat cross-exchange, a desalination plant, co-generation, and other features.

Low emission power generation and hydrocarbon recovery systems and methods

An assembly for providing a seal at an aft end of a combustor liner for a gas turbine engine including a longitudinal centerline axis extending therethrough. The sealing assembly includes a substantially annular first sealing member positioned between an aft portion of a support member and the liner aft end so as to seat on a designated surface portion of the liner aft end and a substantially annular second sealing member positioned between the support member aft portion and a turbine nozzle located downstream of the liner aft end so as to seat on a designated surface portion of the support member aft portion. Accordingly, the first sealing member is maintained in its seated position as the support member aft portion moves radially with respect to the liner aft end and the second sealing member is maintained in its seated position as the support member aft portion moves axially with respect to the turbine nozzle. The first and second sealing members are also maintained in their respective seating positions as the support member aft portion moves axially with respect to the liner aft end and radially with respect to the turbine nozzle.

Sealing assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor

The present invention relates to methods and systems for controlling a combustion reaction and the products there-of. One embodiment includes a combustion control system having an oxygenation stream substantially comprising oxygen and CO2 and having an oxygen to CO2 ratio, then mixing the oxygenation stream with a combustion fuel stream and combusting in a combustor to generate a combustion products stream having a temperature and a composition detected by a temperature sensor and an oxygen analyzer, respectively, the data from which are used to control the flow and composition of the oxygenation and combustion fuel streams. The system may also include a gas turbine with an expander and having a load and a load controller in a feedback arrangement.

Methods and systems for controlling the products of combustion

Methods and systems for low emission power generation in hydrocarbon recovery processes are provided. One system includes a gas turbine system configured to stoichiometrically combust a compressed oxidant derived from enriched air and a fuel in the presence of a compressed recycle exhaust gas and expand the discharge in an expander to generate a recycle exhaust stream and drive a main compressor. A boost compressor receives and increases the pressure of the recycle exhaust stream and prior to being compressed in a compressor configured to generate the compressed recycle exhaust gas. To promote the stoichiometric combustion of the fuel and increase the CO2 content in the recycle exhaust gas, the enriched air can have an increased oxygen concentration.

Stoichiometric combustion of enriched air with exhaust gas recirculation

A double dome combustor for a gas turbine engine includes first and second domes joined to outer and inner liners. The first and second domes are joined together by two load transmitting structural paths for providing increased rigidity of the first and second domes for accommodating pressure loading from compressed airflow. In one exemplary embodiment, a dome cowl having first and second cowls is used to additionally join together the first and second domes.

Double dome combustor

A fuel injector nozzle support includes a support plate joinable to a combustor dome and a ferrule slidably joined to the support plate. The ferrule includes a base, and a bore for slidably receiving a fuel injector nozzle. The ferrule base has a noncircular perimeter and the support plate includes a receptacle for receiving the ferrule base which has an inner circumference being complementary to the ferrule base perimeter for preventing rotation of the ferrule base greater than a predetermined maximum rotation while allowing radial translation of the ferrule base for accommodating differential radial thermal movement of the fuel injector nozzle and the support plate. In an exemplary embodiment, the base perimeter and the receptacle have complementary straight and arcuate profiles, and the support plate is formed with counterrotational swirler vanes of a swirler fixedly supported to a combustor dome. The noncircular perimeter assembly eliminates the use of conventional antirotational lugs and stops.

Fuel injector nozzle support

A combustor for a gas turbine engine that facilitates reducing combustor chamber dump pressure losses to improve combustor and engine performance is described. The combustor includes a diffuser that diffuses airflow directed into the combustor. The diffuser includes an outer wall, an inner wall, and a plurality of splitter vanes between the outer wall and the inner wall. The splitter vanes are spaced radially apart, and each is spaced radially from a respective diffuser wall such that an outer passage, an inner passage, and a central passage are defined by the splitter vanes.

Methods and apparatus for supplying air to turbine engine combustors

A double annular combustor having concentrically disposed inner and outer annular combustors is provided with inner and outer domes. A centerbody is disposed between the inner and outer domes and is constructed of a plurality of annular segments. Each segment includes an upper wall, a lower wall, an upstream wall and a downstream end. The upper and lower walls include flanges extending therefrom to form cavities, within which are cooling holes. Pins are also provided which extend between the upper and lower walls of the centerbody to augment the cooling and structural connection thereof.

Segmented centerbody for a double annular combustor

A gas turbine engine combustor includes radially spaced outer and inner liners disposed coaxially about an engine longitudinal centerline axis with each liner having forward and aft ends. An annular dome is fixedly joined to the forward ends of the outer and inner liners. The outer liner has a substantially uniform thickness and is arcuate in a longitudinal plane from the forward to aft ends for providing buckling resistance of the outer liner.

Hubert Smith Roberts

Papers

Double dome combustor

Fuel injector nozzle support

Methods and apparatus for supplying air to turbine engine combustors

Segmented centerbody for a double annular combustor

Double dome arched combustor