Fuel burners and combustion equipment for use in gas turbine engines

Claim 1

Combustion equipment for a gas turbine engine comprising: an annular casing having a plurality of circumferentially arranged equi-spaced holes; an annular flame tube coaxially positioned within and spaced from said annular casing, said annular flame tube having a corresponding number of circumferentially equi-spaced holes coaxially aligned with the holes of said casing: a plurality of tubes extending radially across said annular flame tube, each tube being coaxial with the corresponding hole in the annular flame tube and the corresponding hole in the annular casing, each tube extending normal to an axis of said annular flame tube, each tube having a duct extending therethrough with an axis normal to the axis of the tube and parallel to the axis of said annular flame tube; a plurality of fuel burners, each fuel burner comprising a cylindrical fuel feed arm having a fuel passage therethrough, a fuel injector having a cylindrical body coaxial with and joined in end-to-end relationship with said cylindrical fuel feed arm, said fuel injector having a first passage in said cylindrical body communicating with said fuel feed passage in said fuel feed arm, said fuel injector having an air duct extending through said cylindrical body thereof, said air duct having an axis normal to the axes of said cylindrical body of the fuel injector and said fuel feed arm, said fuel injector having at least a second passage in said cylindrical body communicating with said first passage therein and with said air duct for injecting fuel into said air duct, each fuel burner extending coaxially through aligned holes in said annular casing and said annular flame tube and through the radial tube in said flame tube, said fuel injector of said fuel burner being positioned in said duct in said radial tube, the axis of said air duct in said cylindrical body being coincident with the axis of the duct in said radial tube.