Combustion apparatus

Claim 1

A combustion apparatus for a gas turbine engine comprising: a combustion chamber having generally annular outer and inner walls joined at their upstream ends, said inner wall being of lesser length than the outer and said chamber having a primary upstream combustion zone located generally between said walls and a secondary combustion zone located generally downstream of said inner wall; a fuel injector having a plurality of primary fuel nozzles and a plurality of secondary fuel nozzles; a plurality of primary duct means arranged to receive fuel from respective ones of said primary fuel nozzles along with compressed air and to direct the resulting primary fuel and air mixture to said primary combustion zone; a plurality of secondary duct means contained within said inner wall and arranged to receive fuel from respective ones of said secondary fuel nozzles along with compressed air and to direct the resulting secondary fuel and air mixture into said secondary combustion zone; tube means extending from adjacent said secondary fuel nozzles to adjacent said secondary combustion zone and spaced from said inner wall, each of said plurality of secondary duct means comprising a longitudinally extending segment of said tube means aligned with a respective one of said secondary fuel nozzles, each said segment having an outlet for the secondary fuel and air mixture which is directed radially outwardly from the axial-center line of the combustion chamber; and air swirling means located between said tube means and said inner wall upstream of said segment outlets.