W501 D5/D5A DF42 COMBUSTION SYSTEM

摘要

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.

主权项

1. A gas turbine engine comprising;
a compressor section; a plurality of fuel nozzles in a combustion section, said fuel nozzles providing fuel for combustion, where each of said fuel nozzles includes one or more fluid atomizing device with orifices configured to dispense liquid fuel and water in different atomized spray patterns and an integral heat shielding device; a plurality of combustors in the combustion section, each of said combustors receiving the fuel from one of the fuel nozzles and burning the fuel, where each of said combustors includes a plurality of air-splitting cooling systems, and a slip-joint cross-flame duct for connecting adjacent combustors; a plurality of transition components in the combustion section, each of said transition components receiving combustion gases from one of the combustors and delivering the combustion gases to a turbine section, where each of said transition components includes a reverse bulk flow effusion cooling system, and transition cylinder cooling system; and a turbine section including a plurality of rotor assemblies, where each rotor assembly includes a rotor disk and a plurality of turbine blades.