Abstract: A gas turbine combustion liner having a novel and improved system for receiving a peripheral device through a floating collar is disclosed. The retaining collar assembly provides planar movement for receiving the peripheral device while preventing the floating collar from rotational movement through an anti-rotation tab on the collar and a collar cap, resulting in reduced wear to the peripheral device. The collar cap can include different configurations for reducing any vibratory effects caused by an oncoming airflow directly contacting the floating collar.

Abstract: A gas turbine combustion liner having a novel and improved system for receiving a peripheral device through a floating collar is disclosed. The retaining collar assembly provides planar movement for receiving the peripheral device while preventing the floating collar from rotational movement through an anti-rotation tab on the collar and a collar cap, resulting in reduced wear to the peripheral device. The collar cap can include different configurations for reducing any vibratory effects caused by an oncoming airflow directly contacting the floating collar.

Abstract: An ignition system having improved reliability for a gas turbine combustor is disclosed. The ignition system comprises an outer housing having at least one fuel passage and an electrode extending therethrough forming a generally annular passage for cooling air to pass to a mixing chamber. Fuel and air mix in the mixing chamber to form a combustible mixture that is ignited by the electrode. The outer housing further comprises a plurality of air swirl holes to effectively cool the walls of the mixing chamber as well as to provide improved flame stability.

Abstract: An end cover for a gas turbine combustor that eliminates the use of braze joints within the plate portion of the end cover is disclosed. The end cover comprises a plate and a plurality of fluid inlets with the fluid inlets directing fluids to first and second manifolds machined into the end cover. The fluids within the end cover are kept separate proximate each of the plurality of first openings by a wall that is integrally formed from a portion of the end cover plate.

Abstract: A fuel nozzle and gas turbine combustor capable of operating on multiple fuels with reduced carbon build-up to the fuel nozzle and adjacent combustor components is disclosed. The fuel nozzle incorporates a reconfigured gas fuel assembly and mixing tube to eliminate known areas of recirculation. Furthermore, the liquid fuel assembly includes reconfigured spray characteristics to further reduce droplet interaction with the mixing tube.

Abstract: An end cover for a gas turbine combustor that eliminates the use of braze joints within the plate portion of the end cover is disclosed. The end cover comprises a plate and a plurality of fluid inlets with the fluid inlets directing fluids to first and second manifolds machined into the end cover. The fluids within the end cover are kept separate proximate each of the plurality of first openings by a wall that is integrally formed from a portion of the end cover plate.

Abstract: An ignition system having improved reliability for a gas turbine combustor is disclosed. The ignition system comprises an outer housing having at least one fuel passage and an electrode extending therethrough forming a generally annular passage for cooling air to pass to a mixing chamber. Fuel and air mix in the mixing chamber to form a combustible mixture that is ignited by the electrode. The outer housing further comprises a plurality of air swirl holes to effectively cool the walls of the mixing chamber as well as to provide improved flame stability.

Abstract: The present invention discloses a means for restricting a flow of fuel to a fuel nozzle assembly for a gas turbine combustor such that the fuel nozzle assembly can be manufactured to accommodate a variety of engine configurations and flow conditions. Multiple embodiments of the present invention are disclosed with each embodiment generally directed towards a nozzle located generally along the centerline of a two-stage combustor.

Abstract: A fuel nozzle and gas turbine combustor capable of operating on multiple fuels with reduced carbon build-up to the fuel nozzle and adjacent combustor components is disclosed. The fuel nozzle incorporates a reconfigured gas fuel assembly and mixing tube to eliminate known areas of recirculation. Furthermore, the liquid fuel assembly includes reconfigured spray characteristics to further reduce droplet interaction with the mixing tube.