Abstract: An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

Abstract: A gas turbine engine operable using either one of a first fuel and a second fuel includes a water supply and a diffusion flame burner including an innermost spray cone, a plurality of spray cones positioned around the innermost spray cone and grouped into a plurality of stages, and a plurality of outlets positioned around the innermost spray cone. A plurality of valves is arranged to connect the first fuel, the second fuel, and the water supply to the diffusion flame burner and a controller is operable to configure the plurality of valves at least in part in response to which of the first fuel and the second fuel is being consumed. When consuming the first fuel, the valves are configured to deliver a mixture of the first fuel and a quantity of water to the plurality of outlets, and to deliver a quantity of water to the plurality of spray cones, and to selectively activate one or more of the stages to allow passage through only the spray cones of the activated stages.

Abstract: An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

Abstract: A multi-functional fuel nozzle (10) for a combustion turbine engine is provided. An annular fuel-injecting lance (12) may include a first fluid circuit (14) and a second fluid circuit (16). One of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine may convey a liquid fuel. The other of the first and second fluid circuits may convey a selectable non-fuel fluid. An atomizer (30) is disposed at the downstream end of the lance. The atomizer may have a first ejection orifice (32) responsive to the first fluid circuit to form a first atomized ejection cone (34), and a second ejection orifice (36) responsive to the second fluid circuit to form a second atomized ejection cone (38). The first and second ejection cones (34, 38) formed with the atomizer may be concentric cones that intersect with one another over a predefined angular range.

Abstract: A nozzle cap (82) is disposed at a downstream end of the nozzle. The nozzle cap includes a bore arranged to accommodate a downstream portion of a fluid-injecting lance that extends along a longitudinal axis (18) of the nozzle. The downstream portion of the fluid-injecting lance includes a centrally-located atomizer (80) to form a first atomized ejection cone. An array of atomizers (84) is disposed in the nozzle cap. The array of atomizers is circumferentially disposed about the longitudinal axis of the lance. The array of atomizers may be positioned radially outwardly relative to the centrally-located atomizer to form an array of respective second atomized ejection cones.

Abstract: A fuel burner system (10) for a turbine engine (12) configured to operate with syngas fuel, whereby the fuel burner system (10) is configured to reduce nozzle and combustor basket temperatures is disclosed. The fuel burner system (10) may include a plurality of first and second fuel injection ports (16) positioned within a combustor (18), whereby the first fuel injection ports (14) are larger than the second fuel injection ports (16). One or more air injection ports (20) may be aligned with the first fuel injection ports (14). During operation, fuel injected into the combustor (18) from the first fuel injection ports (14) mixes better with the incoming air, causing reduced NOx emissions and lower flame temperatures. Also, the regions between adjacent air injection ports (20), which typically run the hottest, are cooler than conventional combustion system due, in part, to the smaller, second fuel injection ports (16) aligned with regions (22) between adjacent air injection ports (20).

Abstract: A nozzle cap (82) is disposed at a downstream end of the nozzle. The nozzle cap includes a bore arranged to accommodate a downstream portion of a fluid-injecting lance that extends along a longitudinal axis (18) of the nozzle. The downstream portion of the fluid-injecting lance includes a centrally-located atomizer (80) to form a first atomized ejection cone. An array of atomizers (84) is disposed in the nozzle cap. The array of atomizers is circumferentially disposed about the longitudinal axis of the lance. The array of atomizers may be positioned radially outwardly relative to the centrally-located atomizer to form an array of respective second atomized ejection cones.

Abstract: A multi-functional fuel nozzle (10) for a combustion turbine engine is provided. An annular fuel-injecting lance (12) may include a first fluid circuit (14) and a second fluid circuit (16). One of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine may convey a liquid fuel. The other of the first and second fluid circuits may convey a selectable non-fuel fluid. An atomizer (30) is disposed at the downstream end of the lance. The atomizer may have a first ejection orifice (32) responsive to the first fluid circuit to form a first atomized ejection cone (34), and a second ejection orifice (36) responsive to the second fluid circuit to form a second atomized ejection cone (38). The first and second ejection cones (34, 38) formed with the atomizer may be concentric cones that intersect with one another over a predefined angular range.

Abstract: An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

Abstract: A diffusion flame burner (110) is provided for a gas turbine engine (136). The diffusion flame burner includes concentrically oriented spray cones (112) staged in a plurality of stages (114, 116, 118, 120) and attached to a water supply (122) during a gas mode and attached to an oil supply (124) during an oil mode. The diffusion flame burner also includes a central spray cone (130) positioned at a center (132) of the concentrically oriented spray cones and attached to the water supply during the oil mode. The diffusion flame burner also includes a plurality of concentrically oriented outlets (134) positioned outside the plurality of concentrically oriented spray cones and attached to a combined water and natural gas supply (122, 128) during the gas mode.