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In order to allow dual fuel operation, that is to say gas and liquid fuel, a fuel injection arrangement and an assembly are provided in which an injection conduit provides constriction to an airflow towards an outlet. In an assembly a plurality of arrangements including liquid fuel jets are arranged

In order to allow dual fuel operation, that is to say gas and liquid fuel, a fuel injection arrangement and an assembly are provided in which an injection conduit provides constriction to an airflow towards an outlet. In an assembly a plurality of arrangements including liquid fuel jets are arranged to such that through high angle incidents by the airflow appropriate vaporization and droplet formation is achieved for a fuel/air mixture combustible in a combustor of a turbine engine. At low liquid fuel flow rates below a pre-determined level the liquid fuel is atomized and entrained by the airflow. At high liquid fuel flow rates the fuel splash impinges upon a wash surface to develop a wash film which is again vaporized and atomized about an edge for a fuel/air mixture capable of combustion.

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We claim: 1. A fuel injection arrangement for a turbine engine, the arrangement including gas fuel injection means to present gaseous fuel and liquid fuel injection means to present liquid fuel to a combustor, the arrangement characterised in that the liquid fuel injection means incorporates an inj

We claim: 1. A fuel injection arrangement for a turbine engine, the arrangement including gas fuel injection means to present gaseous fuel and liquid fuel injection means to present liquid fuel to a combustor, the arrangement characterised in that the liquid fuel injection means incorporates an injection conduit for an airflow and a liquid fuel jet presented at a high angle relative to the air flow such that at low fuel injection rates the air flow entrains and atomises the liquid fuel expelled by the liquid fuel jet without impingement upon the injection conduit whilst at high fuel injection rates the liquid fuel expelled by the liquid fuel jet impinges upon the injection conduit to form a wash film predictably atomised by the air flow, so that entrained and/or said atomised liquid fuel is interchangeable with gas fuel presented through the gas fuel injection means wherein the injection conduit includes an outlet which is approximately 1 mm wide whilst the injection conduit is significantly wider upstream of said outlet. 2. An arrangement as claimed in claim 1 wherein the injection conduit is progressively constrictive towards an outlet in order to approximate a flat flow velocity profile for the air flow across the conduit at the fuel jet. 3. An arrangement as claimed in claim 2 wherein the constriction reduces conduit area by a factor of typically 2 towards the outlet. 4. An arrangement as claimed in claim 1 wherein the liquid fuel jet is inclined relative to the injection conduit for greater distance before splash impingement with the conduit. 5. An arrangement as claimed in claim 1 wherein the injection conduit has an angle of at least fifteen degrees to the fuel jet centreline. 6. An arrangement as claimed in claim 1 wherein the jets are round or oval or square. 7. An arrangement as claimed in claim 1 wherein the wash film develops upon the injection conduit wall opposite the wall containing jet orifice creating a thin fuel film. 8. A fuel injection assembly for a turbine engine comprising a plurality of fuel injection arrangements as claimed in claim 1. 9. An assembly as claimed in claim 8 wherein the wash films of adjacent arrangements extend to present a uniform wash film about the assembly at the highest fuel flow required. 10. An assembly as claimed in claim 8 wherein the injection conduit and/or injection conduit outlet of the assembly, are presented relative to a common longitudinal axis of the assembly with an exit angle determined for appropriate fuel distribution into the combustor. 11. An assembly as claimed in claim 10 wherein the exit angle is in the range of 90째 to 180째. 12. An assembly as claimed in claim 8 wherein the airflow in the arrangements is radial from a common root conduit. 13. An assembly as claimed in claim 8 wherein the assembly is configured with a trumpet outlet periphery incorporating the fuel injection arrangements. 14. A turbine engine incorporating a fuel injection assembly as claimed in claims 8. 15. A turbine engine incorporating a fuel injection arrangement as claimed in claim 1. 16. A fuel injection arrangement for a turbine engine, the arrangement including gas fuel injection means to present gaseous fuel and liquid fuel injection means to present liquid fuel to a combustor, the arrangement characterised in that the liquid fuel injection means incorporates an injection conduit for an airflow and a liquid fuel jet presented at a high angle relative to the air flow such that at low fuel injection rates the air flow entrains and atomises the liquid fuel expelled by the liquid fuel jet without impingement upon the injection conduit whilst at high fuel injection rates the liquid fuel expelled by the liquid fuel jet impinges upon the injection conduit to form a wash film predictably atomised by the air flow, so that entrained and/or said atomised liquid fuel is interchangeable with gas fuel presented through the gas fuel injection means wherein the liquid fuel jet comprises an orifice with sharp corners at its outlet to prevent liquid fuel wetting the conduit surface from which the liquid fuel emanates. 17. A fuel injection arrangement for a turbine engine, the arrangement including gas fuel injection means to present gaseous fuel and liquid fuel injection means to present liquid fuel to a combustor, the arrangement characterised in that the liquid fuel injection means incorporates an injection conduit for an airflow and a liquid fuel jet presented at a high angle relative to the air flow such that at low fuel injection rates the air flow entrains and atomises the liquid fuel expelled by the liquid fuel jet without impingement upon the injection conduit whilst at high fuel injection rates the liquid fuel expelled by the liquid fuel jet impinges upon the injection conduit to form a wash film predictably atomised by the air flow, so that entrained and/or said atomised liquid fuel is interchangeable with gas fuel presented through the gas fuel injection means wherein the liquid fuel to air mass flow ratios within the injection conduit vary between 0.5 and 1.5 to 1 dependant on engine power level. 18. A fuel injection arrangement for a turbine engine, the arrangement including gas fuel injection means to present gaseous fuel and liquid fuel injection means to present liquid fuel to a combustor, the arrangement characterised in that the liquid fuel injection means incorporates an injection conduit for an airflow and a liquid fuel jet presented at a high angle relative to the air flow such that at low fuel injection rates the air flow entrains and atomises the liquid fuel expelled by the liquid fuel jet without impingement upon the injection conduit whilst at high fuel injection rates the liquid fuel expelled by the liquid fuel jet impinges upon the injection conduit to form a wash film predictably atomised by the air flow, so that entrained and/or said atomised liquid fuel is interchangeable with gas fuel presented through the gas fuel injection means wherein the liquid fuel jet has a width of 1 mm or less. 19. A fuel injection arrangement for a turbine engine, the arrangement including gas fuel injection means to present gaseous fuel and liquid fuel injection means to present liquid fuel to a combustor, the arrangement characterised in that the liquid fuel injection means incorporates an injection conduit for an airflow and a liquid fuel jet presented at a high angle relative to the air flow such that at low fuel injection rates the air flow entrains and atomises the liquid fuel expelled by the liquid fuel jet without impingement upon the injection conduit whilst at high fuel injection rates the liquid fuel expelled by the liquid fuel jet impinges upon the injection conduit to form a wash film predictably atomised by the air flow, so that entrained and/or said atomised liquid fuel is interchangeable with gas fuel presented through the gas fuel injection means wherein the liquid fuel injection means includes a liquid fuel manifold and the gap between the injection conduit wall and a portion of said manifold is a continuous annulus. 20. A fuel injection arrangement for a turbine engine, the arrangement including gas fuel injection means to present gaseous fuel and liquid fuel injection means to present liquid fuel to a combustor, the arrangement characterised in that the liquid fuel injection means incorporates an injection conduit for an airflow and a liquid fuel jet presented at a high angle relative to the air flow such that at low fuel injection rates the air flow entrains and atomises the liquid fuel expelled by the liquid fuel jet without impingement upon the injection conduit whilst at high fuel injection rates the liquid fuel expelled by the liquid fuel jet impinges upon the injection conduit to form a wash film predictably atomised by the air flow, so that entrained and/or said atomised liquid fuel is interchangeable with gas fuel presented through the gas fuel injection means wherein the wash film develops by spread divergence to form a wedge wake extending towards a conduit edge. 21. An arrangement as claimed in claim 20 wherein the wash film has a thickness of about 30 microns at the conduit edge. 22. A fuel injection arrangement for a turbine engine, the arrangement including gas fuel injection means to present gaseous fuel and liquid fuel injection means to present liquid fuel to a combustor, the arrangement characterised in that the liquid fuel injection means incorporates an injection conduit including an outlet for an airflow and a liquid fuel jet presented at a high angle relative to the air flow such that at low fuel injection rates the air flow entrains and atomises the liquid fuel expelled by the liquid fuel jet without impingement upon the injection conduit whilst at high fuel injection rates the liquid fuel expelled by the liquid fuel jet impinges upon the injection conduit to form a wash film predictably atomised by the air flow, so that entrained and/or said atomised liquid fuel is interchangeable with gas fuel presented through the gas fuel injection means wherein the liquid fuel jet is arranged to be variable in terms of angle and/or displacement distance from the injection conduit outlet for alteration in predictable liquid fuel atomisation and/or entrainment.