Abstract: A combustion system is provided having a liner, a flow sleeve, a flow-obstructing element, and a venturi. The liner is disposed around a combustion region. The flow sleeve is disposed around the liner. The liner and the flow sleeve cooperate to create an air passage having an airflow located between the liner and the flow sleeve. The flow-obstructing element is disposed within the air passage, and generally obstructs the airflow in the air passage to create wakes in the airflow. The venturi is disposed downstream from the flow-obstructing element, and generally restricts and diffuses the airflow in the air passage to reduce wakes in the airflow.

Abstract: Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.

Abstract: A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane.

Abstract: A system includes a fuel nozzle. The fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple first fuel outlets disposed on the hub, and multiple swirl vanes disposed in the airflow path downstream from the multiple first fuel outlets.

Abstract: A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sleeve. The structure obstructs an airflow path through the air passage. The gas turbine combustor also includes an aerodynamic wake reducer configured to redirect an airflow around the structure to reduce a wake region downstream of the structure.

Abstract: Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.

Abstract: A combustion system is provided having a liner, a flow sleeve, a flow-obstructing element, and a venturi. The liner is disposed around a combustion region. The flow sleeve is disposed around the liner. The liner and the flow sleeve cooperate to create an air passage having an airflow located between the liner and the flow sleeve. The flow-obstructing element is disposed within the air passage, and generally obstructs the airflow in the air passage to create wakes in the airflow. The venturi is disposed downstream from the flow-obstructing element, and generally restricts and diffuses the airflow in the air passage to reduce wakes in the airflow.

Abstract: A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane.

Abstract: A system includes a fuel nozzle. The fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple first fuel outlets disposed on the hub, and multiple swirl vanes disposed in the airflow path downstream from the multiple first fuel outlets.

Abstract: A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, a fuel injector disposed downstream of the combustion liner and the flow sleeve, a liner mount extending between the combustion liner and the flow sleeve, and a crossfire tube extending between the combustion liner and the flow sleeve. The fuel injector, the liner mount, and the crossfire tube are aligned with one another in a flow enhancing arrangement along a common axis in an axial direction relative to an axis of the gas turbine combustor. The flow enhancing arrangement reduces an air flow disturbance caused by the fuel injector, the liner mount, and the crossfire tube.

Abstract: An injector apparatus is provided and includes an annular inlet in which a first fluid traveling in a first direction is mixable with a second fluid to form a mixture, an annular outlet disposed downstream from the inlet from which the mixture is injectable into a main flow in a third direction and an annular intermediate section fluidly interposed between the inlet and the outlet and along which the mixture is re-directable from the inlet to the outlet.

Abstract: A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sleeve. The structure obstructs an airflow path through the air passage. The gas turbine combustor also includes an aerodynamic wake reducer configured to redirect an airflow around the structure to reduce a wake region downstream of the structure.

Abstract: A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, a fuel injector disposed downstream of the combustion liner and the flow sleeve, a liner mount extending between the combustion liner and the flow sleeve, and a crossfire tube extending between the combustion liner and the flow sleeve. The fuel injector, the liner mount, and the crossfire tube are aligned with one another in a flow enhancing arrangement along a common axis in an axial direction relative to an axis of the gas turbine combustor. The flow enhancing arrangement reduces an air flow disturbance caused by the fuel injector, the liner mount, and the crossfire tube.

Abstract: A low-emission method for producing power using a gas turbine includes premixing a plurality of fuel and air mixtures, injecting the fuel and air mixtures into a combustion chamber using a plurality of fuel nozzles, and adjusting a ratio of fuel and air injected by at least one of the nozzles to control a fuel/air concentration distribution within the combustion chamber.

Abstract: A low-emission method for producing power using a gas turbine includes premixing a plurality of fuel and air mixtures, injecting the fuel and air mixtures into a combustion chamber using a plurality of fuel nozzles, and adjusting a ratio of fuel and air injected by at least one of the nozzles to control a fuel/air concentration distribution within the combustion chamber.

Abstract: A low-emission method for producing power using a gas turbine includes premixing a plurality of fuel and air mixtures, injecting the fuel and air mixtures into a combustion chamber using a plurality of fuel nozzles, and adjusting a ratio of fuel and air injected by at least one of the nozzles to control a fuel/air concentration distribution within the combustion chamber.

Abstract: The endcover assembly for a combustor includes an endcover having an aperture, an insert disposed in the stepped bore opening through an internal face of the endcover, a fuel cartridge extending through the insert and aperture and a seal cover on the external face of the endcover. Seal cover/endcover annular seals are disposed in registering axial cavities to seal against fluid leakage externally of the endcover assembly. Generally C-shaped and W-shaped seals are disposed in the cavities between the stepped shoulders of the insert and aperture to seal against leakage through the internal face of the endcover. The seals maintain sealing engagement during assembly and thermal distortion during turbine usage.

Abstract: A combustion liner cap assembly includes a cylindrical outer sleeve supporting internal structure therein and a plurality of fuel nozzle openings formed through the internal structure. A first set of circumferentially spaced cooling holes is formed through the cylindrical outer sleeve, and a second set of circumferentially spaced cooling holes is formed through the cylindrical outer sleeve. The second set of cooling holes is axially spaced from the first set of cooling holes. The resulting construction serves to decrease combustion dynamics in a simplified manner that is retrofittable to current designs and reversible without impacting the original configuration. The reduction in combustion dynamics improves hardware life, which leads to reduced repair and replacement costs.