Fuel burners for gas turbine engines

Claim 1

A fuel injector suitable for a gas turbine engine comprising: a hollow, open-ended circular section duct defining a cylindrical wall, said circular section duct having an upstream end arranged to receive a flow of compressed air and a downstream end to discharge a mixture of compressed air and fuel; swirl means positioned at the upstream end of said circular duct, said swirl means comprising a plurality of spaced vanes extending inwardly from said cylindrical wall; a centrally positioned, hollow, open-ended hub at the upstream end of said circular section duct, said inner ends of said vanes being supported by said hub; a first set of fuel orifices in the wall of said cylindrical section duct adjacent the downstream end thereof for providing a low fuel flow rate at low power conditions of said engine; a second set of fuel orifices in the wall of said circular section duct positioned upstream of said first set and downstream of said swirl means for providing a higher fuel flow rate at high power conditions of said engine; fuel manifolds arranged to communicate respectively to said first and second sets of fuel orifices for supplying fuel thereto; and a cylindrical wall spaced outwardly of the cylindrical wall of said circular section duct to define an annular air flow passage having an open, upstream end and an open, downstream end, said annular air flow passage being coaxial with said circular section duct and having its upstream end also coaxial with the upstream end of said circular section duct; and a further swirl means in said annular air flow passage, said further swirl means including a plurality of spaced vanes.