Patent ID: 8186162
Filing Date: 2012-05-29
Classification: F23R

Abstract:
1. A fuel nozzle for a turbine engine having a compressor section and a combustion chamber, the fuel nozzle comprising: a central body comprising a pilot fuel injector injecting a pilot stream of fuel through a tip end of central body and into the combustion chamber; an air inlet duct and a mixing duct positioned about the central body helping to define an annular flow passageway between the air inlet duct and the mixing duct and the central body that in use communicates a flow of compressed air from the compressor section through the fuel nozzle out through the exit of the mixing duct and into the combustion chamber; a swirler positioned between the air inlet duct and the mixing duct that swirls the compressed air passing in the annular flow passageway between the air inlet duct and the mixing duct; a plurality of fuel jets to inject fuel into the compressed air passing though the annular flow passageway; and a plurality of circumferentially spaced air jets formed through the fuel nozzle between the swirler and the exit of the mixing duct, the air jets communicating additional compressed air from the compressor section into the annular flow passageway.