Abstract: A fuel injector for a gas turbine conbustor, the injector operating on gas and liquid fuels selectively. The injector has a central liquid fuel duct and jets, an annular gas duct and gas jets, and an outer annular combustion air duct. Operation on the liquid fuel tends to cause combustion products to be ingested into the gas orifices so impeding efficient gas combustion. The invention provides apertures (17) between the outer air duct and the intermediate gas duct whereby during operation on liquid fuel air bleeds into the gas duct and purges the gas orifices. As an added advantage, in a transition from liquid fuel to gas, the gas pressure is increased to a point where the air bleed is reversed and gas bleeds into the air duct. The pre-mixed gas/air is then emitted from swirlers surrounding the ring of gas jets. More efficient gas combustion results.

Abstract: Fuel injection equipment for an internal combustion engine is modified by connecting a closed chamber (28) via a permanently open flow restriction (29) either to the working chamber (11) of a fuel pump (1), or to a high pressure fuel supply connection (36) between the output of the working chamber (11) and a fuel injector (39), or to a pressurized fuel supply passage (55) in the injector upstream of an injector valve (48). The volume of the closed chamber (28) and the cross sectional flow area of the restriction (29) are selected to allow a predetermined volume of pressurized fuel to flow into the closed chamber (28) when the equipment is operating, thereby reducing the flow of fuel through the injector valve (48) during the initial period of injection.