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A gas fuel nozzle for mounting in a combustor wall of a gas turbine engine, with an at least partially radially-directed array of gas fuel outlets extending beyond an air flow head having an array of compressed air jet apertures around the gas fuel outlets. The air flow head also has a deflector for

A gas fuel nozzle for mounting in a combustor wall of a gas turbine engine, with an at least partially radially-directed array of gas fuel outlets extending beyond an air flow head having an array of compressed air jet apertures around the gas fuel outlets. The air flow head also has a deflector for creating an axial flow of air for deflecting in an axial direction the radially-injected gas fuel.

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1. A gas fuel nozzle for mounting in a combustor end wall of a gas turbine engine, the engine having a combustor defined with inner and outer walls extending from the combustor end wall, the gas fuel nozzle comprising:a gas fuel delivery member having a gas fuel supply duct with a plurality of gas f

1. A gas fuel nozzle for mounting in a combustor end wall of a gas turbine engine, the engine having a combustor defined with inner and outer walls extending from the combustor end wall, the gas fuel nozzle comprising:a gas fuel delivery member having a gas fuel supply duct with a plurality of gas fuel outlets; an air flow head about the gas fuel delivery member with a plurality of compressed air jet apertures; wherein: the fuel outlets are oriented to eject gas fuel with a radial component from the gas fuel delivery member; and at least one deflector aperture disposed on the air flow head adjacent at least one of the inner combustor wall and the outer combustor wall for deflecting the gas fuel ejected from the gas fuel delivery member in an axial direction with a flow of compressed air. 2. A gas fuel nozzle according to claim 1 wherein the deflector aperture comprises a planar surface.3. A gas fuel nozzle according to claim 2 wherein the planar surface is disposed on a radially outer edge of the air flow head.4. A gas fuel nozzle according to claim 1 wherein the compressed air jet apertures comprise axially directed bores.5. A gas fuel nozzle according to claim 1 wherein the compressed air jet apertures comprise radially directed bores open to an upstream portion of the gas fuel delivery member.6. A gas fuel nozzle according to claim 1 wherein the gas fuel delivery member has a side wall with radially open ports.7. A gas fuel nozzle according to claim 6 wherein the ports are rectangular.8. A gas fuel nozzle according to claim 1 wherein the downstream end of the gas fuel delivery member is capped.9. An air blast gas fuel nozzle for a gas turbine engine having a combustor, the gas fuel nozzle comprising:a nozzle head adapted for mounting in a wall of the combustor and protruding therethrough, the nozzle head having a plurality of air flow apertures there through in communication with a source of pressurized air; and a gas fuel delivery member disposed on the head centrally of said plurality of air flow apertures and adapted to extend into the combustor, the delivery member having a gas fuel inlet supply duct communicating with a plurality of gas fuel outlets, the gas fuel outlets oriented to eject gas fuel in the combustor with a radial component relative to the head; wherein the head further comprises at least one deflector aperture disposed in the head, the aperture in communication with a source of pressurized air, the deflector aperture positioned on the head so that an air flow therethrough intersects a gas fuel stream ejected with a radial component from the delivery member. 10. The air blast gas fuel nozzle of claim 9 wherein the at least a portion of the air flow apertures in the nozzle head are positioned in the nozzle to deliver a pressurized air flow therethrough which intersects and deflects a gas fuel stream ejected with a radial component from the delivery member.11. The air blast gas fuel nozzle of claim 9 gas fuel stream ejected from the delivery member is directed only in the radial direction relative to the nozzle head.12. An air blast gas fuel nozzle for a gas turbine engine having a combustor, the gas fuel nozzle comprising:a nozzle head adapted for mounting in a wall of the combustor and protruding therethrough, the nozzle head having a plurality of air flow apertures there through in communication with a source of pressurized air; and a gas fuel delivery member disposed on the head centrally of said plurality of air flow apertures and adapted to extend into the combustor, the delivery member having a gas fuel inlet supply duct communicating with a plurality of gas fuel outlets, the gas fuel outlets oriented to eject gas fuel in the combustor with a radial component relative to the head, wherein at least a portion of the air flow apertures are directed radially towards an upstream portion of the fuel delivery member. 13. The air blast gas fuel nozzle of claim 12 wherein the at least a portion of the air flow apertures in the nozzle head are positioned in the nozzle to deliver a pressurized air flow therethrough which intersects and deflects a gas fuel stream ejected with a radial component from the delivery member.14. The air blast gas fuel nozzle of claim 12 wherein the head further comprises at least one deflector aperture disposed in the head, the aperture in communication with a source of pressurized air, the deflector aperture positioned on the head so that an air flow therethrough intersects a gas fuel stream ejected with a radial component from the delivery member.15. The air blast gas fuel nozzle of claim 12 gas fuel stream ejected from the delivery member is directed only in the radial direction relative to the nozzle head.