Patent ID: 7117679

Claim:
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.