Abstract: A swirl cup for a gas turbine engine combustor includes a tubular body having an inlet at one end for receiving a fuel injection nozzle, an outlet at an opposite end for discharging the fuel, and an annular septum therebetween. A row of first swirl vanes is attached to the septum adjacent the body inlet, and a row of second swirl vanes is attached to the septum adjacent the first swirl vanes and spaced upstream from the body outlet. Air from the first and second swirl vanes is swirled directly around the injected fuel without a flow barrier or venturi therebetween.

Abstract: A swirl cup for a gas turbine engine combustor includes a tubular body having an inlet at one end for receiving a fuel injection nozzle, an outlet at an opposite end for discharging the fuel, and an annular septum therebetween. A row of first swirl vanes is attached to the septum adjacent the body inlet, and a row of second swirl vanes is attached to the septum adjacent the first swirl vanes and spaced upstream from the body outlet. Air from the first and second swirl vanes is swirled directly around the injected fuel without a flow barrier or venturi therebetween.

Abstract: A swirl cup for a gas turbine engine combustor includes a tubular body having an inlet at one end for receiving a fuel injection nozzle, an outlet at an opposite end for discharging the fuel, and an annular septum therebetween. A row of first swirl vanes is attached to the septum adjacent the body inlet, and a row of second swirl vanes is attached to the septum adjacent the first swirl vanes and spaced upstream from the body outlet. Air from the first and second swirl vanes is swirled directly around the injected fuel without a flow barrier or venturi therebetween.

Abstract: A flare comprising an oxygen reservoir section, a fuel reservoir section and a nozzle section; the oxygen reservoir section having a reservoir capable of containing oxygen at high pressure, and a valve operable by an actuator to selectively permit transmission of pressurized oxygen from the reservoir; the fuel reservoir section including a collapsible fuel bag having a fuel orifice at one end and a plug normally positioned over the orifice; and the nozzle section having a oxygen flow deflector, a fuel atomizing region and an ignition region.

Abstract: A infrared flare is used as a military decoy for infrared heat seeking missiles. The flare burns a pyrophoric fuel to provide a good simulation of an aircraft spectral signature. To minimize blow-out under extreme wind and high altitude conditions, the flare has an oxygen injector arranged concentrically around the fuel ejector and a shroud sheltering an ignition space just downstream of the fuel ejector. The injected oxygen reacts with a small amount of the fuel to produce a pilot flame in the shroud.